TWM604685U - Repair system for near-wall center hole of component - Google Patents

Abstract

The authoring department provides a repair system for the hole in the near wall of the component. The repair system includes determining the updated hole information of the first hole in the near wall of the component; including the updated position; the method also includes the update position of the first hole The restricted laser beam of the restricted laser drill is directed toward the proximal wall of the component to drill through the coating of the component extending above and in the first hole; the method further includes sensing the updated position from the first hole The characteristic of the reflected light, and it is determined that the restricted laser beam of the restricted laser drill has been drilled and extended to a part of the part coating on the part, and then it is positioned in the first hole according to the characteristic of the detected light.

Description

Repair system for near-wall middle holes of components

This creative department relates to a system for repairing parts using restricted laser drills.

Turbines are widely used in industrial and commercial operations. Typical commercial steam or gas turbines used to generate electricity include alternating stages of fixed and rotating airfoils. For example, fixed blades can be attached to fixed parts, such as a casing surrounding the turbine, and Rotating blades may be attached to a rotor positioned along the axial centerline of the turbine, compressed working fluid (such as but not limited to steam, combustion gas or air) flows through the turbine, and the fixed blades accelerate and direct the compressed working fluid to On the subsequent stage of the rotating blade, movement is applied to the rotating blade, thereby turning the rotor and performing work.

The efficiency of the turbine usually increases as the temperature of the compressed working fluid increases. However, excessively high temperatures in the turbine will reduce the life of the wing in the turbine, thereby increasing turbine-related repairs, such as maintenance and shutdown, so it will be developed Various designs and methods to provide cooling of the airfoil. For example, a cooling medium can be supplied to the cavity inside the airfoil to remove heat from the airfoil convectively or conductively. In certain embodiments, the cooling medium The cavity may flow out of the airfoil through cooling channels in the airfoil to provide film cooling on the outer surface of the airfoil.

With the continuous improvement of temperature or performance standards, the materials used for airfoils have become thinner and thinner, making it more and more difficult to reliably manufacture airfoils. For example, some airfoils are made of high-alloy metals. Cast, coated with a layer of thermal insulation coating on the outer surface of this airfoil to Enhanced thermal protection performance. However, through continuous use, the cooling holes in the wing may be blocked by debris or other contaminants, and the thermal insulation coating may be worn or chipped. In addition, in some cases, the wing The profile may undergo plastic deformation, so that the position or direction of the hole may be different from the original position or direction.

Some airfoils can be repaired to solve the above problems. However, it is usually an expensive and time-consuming process to properly remove each cooling hole and reapply the thermal barrier coating, for example, some are used to reapply the thermal barrier coating The system needs to cover every cooling hole of the airfoil, so a system and method for determining which cooling holes (if any) are blocked and for removing any debris will be particularly beneficial. In addition, for recoating Systems and methods for applying thermal barrier coatings without covering or otherwise protecting each cooling hole during coating are also particularly beneficial.

The practice and advantages of this creation are clarified in the following description, or can become obvious from the description, or can be learned by implementing this creation.

In an exemplary embodiment of the present creation, a repair system for a hole in the near wall of a component is provided. The repair system includes a limited laser drill using a limited laser beam, positioned to sense the first hole in the near wall of the component. The updated position of a hole is characterized by a sensor that reflects light, and a controller operably connected to the restricted laser drill, and the sensor, the controller is configured to determine the updated hole information of the first hole in the near wall of the component, the first hole The updated hole information includes the updated position of the first hole in the near wall, and the controller is also configured to guide the restricted laser beam toward the near wall of the component at the updated position of the first hole to drill through above the first hole And a part of the coating of the extension member located in the first hole, the controller is also configured to receive characteristic information indicating the sensed light from the sensor, and determine that the restricted laser beam of the restricted laser drill has passed through the coating in the first hole Extending above and located in the first hole Partially drilled out, and is based on the characteristics of light sensed by the sensor.

10: Turbo part

12: Rotor

14: shell

16: gas path

18: Centerline

20: rotor wheel

22: Rotor spacer

24: Bolt

26: working fluid

30: Rotating blade

32: fixed blade

34: outer surface

36: Thermal insulation coating

38: airfoil

40: Metal part

42: pressure side

44: suction side

46: Cavity

48: leading edge

50: trailing edge

52: hole

54: opening

60: System

62: Restricted Laser Drill

64: Limited laser beam

66: Near Wall

68: Controller

70: Laser beam

72: Liquid column

74: recoil protection mechanism

76: Gas

78: Far Wall

80: sensor

82: Toward the lens

84: processor

86: memory

88: Logic

90: Debris

92: first hole

94: second hole

Figure 1: is a simplified cross-sectional view of the turbine portion of an exemplary gas turbine, which can incorporate various embodiments of the present creation.

Figure 2: is a perspective view of an exemplary airfoil according to an embodiment of the present creation.

Fig. 3 is a schematic diagram of a system for repairing an airfoil according to an exemplary embodiment of the present disclosure.

Figure 4: is another schematic diagram of the exemplary system of the third figure.

Figure 5: is another schematic diagram of the exemplary system of the third figure.

Figure 6: is a flowchart of a method for repairing an airfoil according to an exemplary aspect of the present creation.

Fig. 7: is a schematic diagram of a system for repairing an airfoil according to another exemplary embodiment of the present creation.

Fig. 8 is another schematic diagram of the exemplary system of Fig. 7;

Fig. 9 is a flowchart of a method for repairing an airfoil according to another exemplary aspect of the present disclosure.

FIG. 10: is a flowchart of a method for repairing an airfoil according to another exemplary aspect of the present disclosure.

The following will illustrate the spirit and method of this creation with illustrations and detailed explanations. Anyone with ordinary knowledge in the technical field can change and modify the techniques taught in this creation after understanding the best embodiment of this creation. It does not deviate from the spirit and scope of this creation.

Referring to FIG. 1, a simplified side sectional view of an exemplary turbine section 10 of a gas turbine according to various embodiments of the present creation is provided, the turbine section 10 generally includes a rotor 12 And a housing 14, which at least partially defines a gas path 16 through the turbine section 10. The rotor 12 is generally aligned with the axial centerline 18 of the turbine section 10 and may be connected to a generator, compressor or another A machine to generate work, the rotor 12 may include alternating parts of a rotor wheel 20 and a rotor spacer 22 connected together by bolts 24 to rotate together, and a housing 14 circumferentially surrounds at least a part of the rotor 12 to accommodate the gas path 16 flowing through. The compressed working fluid 26 may include, for example, combustion gas, compressed air, saturated steam, unsaturated steam, or a combination thereof.

Please refer to Fig. 1, the turbine part 10 also includes alternating stages of rotating blades 30 and fixed blades 32, which extend radially between the rotor 12 and the casing 14. The rotating blades 30 are arranged circumferentially around the rotor 12 and can Various devices are used to connect to the rotor wheel 20. On the contrary, the fixed blades 32 can be arranged around the inner periphery of the housing 14 opposite to the rotor spacer 22. The rotating blades 30 and the fixed blades 32 generally have the shape of an airfoil 38, as in the present invention. As is known in the art, there is a concave pressure side, a convex suction side and a leading edge and a trailing edge as shown in Figure 1. The compressed working fluid 26 flows along the turbine section 10 from left to right along the gas path 16, when When the compressed working fluid 26 passes through the first stage of the rotating blade 30, the compressed working fluid expands, causing the rotating blade 30, the rotor wheel 20, the rotor spacer 22, the bolt 24 and the rotor 12 to rotate, and then the compressed working fluid 26 Flow through the next stage of the stationary blade 32, which accelerates and redirects the compressed working fluid 26 to the next stage of the rotating blade 30, and the process is repeated for the subsequent stages, as shown in the exemplary In the embodiment, the turbine part 10 has two stages of fixed blades 32 between the three stages of rotating blades 30; the second stage of fixed blades 32 is between the three stages of rotating blades 30, however, those of ordinary skill in the art will easily understand that, Unless specifically stated in the claims, the number of stages of the rotating blade 30 and the fixed blade 32 is not a limitation of the present disclosure.

Figure 2 provides a perspective of an exemplary airfoil 38 according to an embodiment of the present disclosure Figure, such as can be incorporated into the rotating blade 30 or the stationary blade 32, as shown in Figure 2, the airfoil 38 generally includes a pressure side 42 having a concave curvature and a suction side 44 opposite to the pressure side 42 having a convex curvature. The side 42 and the suction side 44 are separated from each other to form a cavity 46 between the pressure side 42 and the suction side 44 within the airfoil 38. The cavity 46 can provide a curved or tortuous path for the cooling medium to keep the cooling medium in the airfoil. Flow inside the airfoil 38 to remove heat conductively and convectively from the airfoil 38. In addition, the pressure side 42 and the suction side 44 are further joined to form a leading edge 48 at the upstream portion of the airfoil 38, and in the airfoil 38 is formed at the downstream portion of the trailing edge 50, the pressure side 42, the suction side 44, the leading edge 48 and the multiple cooling holes 52 in the trailing edge 50 through the airfoil 38 to provide fluid communication with the cavity 46, so as to The cooling medium is supplied on the outer surface 34 of the chamber, as shown in FIG. 2, for example, the cooling holes 52 may be located at the front edge 48 and the rear edge 50, and along one or both of the pressure side 42 and the suction side 44, exemplary The airfoil 38 further defines openings 54 at the bottom and the bottom of the airfoil 38 where a cooling medium (such as compressed air from the compressor section of the gas turbine) may be provided to the cavity 46.

Those of ordinary skill in the art will readily realize from the teachings herein that the number and positions of the cooling holes 52 can be changed according to specific embodiments, and the design of the cavity 46 and the design of the cooling holes 52 can also be changed according to the specific embodiment. Variations; therefore, unless explicitly stated in the claims, the present invention is not limited to any specific number or location of cooling holes 52, nor is it limited to any specific cooling hole 52 or cavity 46 design.

In certain exemplary embodiments, the wall of the airfoil 38 may include a thermal barrier coating 36 that is coated on at least a portion of the outer surface 34 of the metal portion 40 of the airfoil 38 (see FIG. 3), the airfoil 38 covering the metal part 40 below; if the thermal insulation coating 36 is applied, it can include low heat emissivity or high heat reflectivity, smooth finish and a good effect on the outer surface 34 below Good adhesion.

Referring now to FIG. 3, a schematic diagram of an exemplary system 60 of the present disclosure is provided. The system 60 can be used, for example, to repair components of a gas turbine; more particularly, for the depicted embodiment, the system 60 is used to repair one or more holes or cooling holes 52 in the airfoil 38 of the gas turbine, such as the above referenced figure 2 discussed airfoil 38; however, it should be understood that although the system 60 is described herein in the context of repairing airfoil 38, in other exemplary embodiments, system 60 may be used to repair any other gas turbine Suitable components; for example, the system 60 can be used to repair transition pieces, nozzles, combustion liners, effusion or impingement plates, blades, shrouds, or any other suitable components.

The exemplary system 60 generally includes a restricted laser drill 62 configured to direct the restricted laser beam 64 toward the proximal wall 66 of the airfoil 38; the restricted laser beam 64 defines the beam axis A; and the proximal wall 66 of the airfoil 38 is positioned Into a cavity 46 adjacent to the airfoil; various embodiments of the restricted laser drill 62 may generally include a laser mechanism and a collimator (not shown); as discussed in more detail below, the system 60 also includes a restricted laser drill 62 operatively communicating controller 68; the laser mechanism may include any device capable of generating the laser beam 70, and the collimator may be configured to reshape the diameter of the laser beam 70 when focusing the beam into a different medium to achieve Any device with better focusing characteristics, such as glass fiber or water; therefore, as used herein, a collimator includes any device that narrows and aligns a beam of particles or waves to make the spatial cross section of the beam smaller; For example, in certain embodiments, the collimator may receive the laser beam 70 and a fluid such as deionized water or filtered water. The holes or nozzles can then direct the laser beam 70 in the liquid column 72 toward the airfoil 38; the liquid column 72 can have a pressure of about 2,000 to 3,000 pounds per square inch; however, unless specifically stated in the claims, otherwise The present creation is not limited to any specific pressure of the liquid column 72; in addition, it should be understood that, as used herein, approximate terms, such as "approximately" or "approximately", mean within ten percent of the error.

The liquid column 72 may be surrounded by a protective gas such as air and used as the laser beam 70 Therefore, the liquid column 72 and the laser beam 70 can together form a restricted laser beam 64 that is utilized by the restricted laser drill 62 and directed to the airfoil 38; as discussed in more detail below, the restricted laser drill 62 may utilize a restricted laser beam 64 to repair one or more cooling holes 52 in the proximal wall 66 of the airfoil 38.

3, the system 60 also includes an exemplary recoil protection mechanism 74; the depicted exemplary recoil protection mechanism 74 includes gas 76 flowing inside the airfoil 38; as used herein, the term "gas" can include any Gaseous medium. For example, the gas 76 may be an inert gas, vacuum, saturated steam, superheated steam, or any other suitable gas that can form a gas flow in the cavity 46 of the airfoil 38; the gas 76 flowing inside the airfoil 38 may have the same The pressure of the liquid in the liquid column 72 is approximately the same pressure, or any other pressure sufficient to destroy the restricted laser beam 64; more specifically, the gas 76 may have sufficient dynamic torque or velocity to destroy the airfoil 38 Any other pressure of the liquid column 72 within the cavity 46; for example, in certain exemplary embodiments, the gas 76 flowing inside the airfoil 38 may have a pressure greater than about twenty-five pounds per square inch, although unless In particular, the present creation is not limited to any specific pressure of the gas 76; in this way, the gas 76 prevents the restricted laser beam 64 from hitting the inner surface of the cavity 46 of the airfoil 38, which interacts with the cooling in the proximal wall 66 The holes 52 are opposite; more specifically, the gas 76 prevents the restricted laser beam 64 from hitting the far wall 78 of the airfoil 38 after passing through the near wall of the airfoil.

As used herein, the terms "breakthrough", "breakthrough" and their meanings refer to when the restricted laser beam 64 extends continuously and uninterruptedly through the proximal wall 66 of the airfoil 38 along the beam axis A of the restricted laser beam 64 After any penetration of the restricted laser beam 64 through the proximal wall 66 of the airfoil 38, at least a portion of the restricted laser beam 64 may pass therethrough, for example into the cavity 46 of the airfoil 38.

The exemplary system 60 of FIG. 3 additionally includes a transmitter operatively connected to the controller 68. The sensor 80; the sensor 80 may be an optical sensor configured to sense the characteristics of light and send a signal indicating the characteristics of the sensed light to the controller 68; in addition, for the exemplary embodiment shown, the sensor 80 is positioned In order to sense the characteristics of light directed along the beam axis A and away from the near wall 66 of the airfoil 38, for example, the reflected and redirected light from the cooling hole 52; in certain exemplary embodiments, the sensor 80 It can be an oscilloscope sensor suitable for sensing one or more of the following optical characteristics: light intensity, one or more wavelengths of light, amount of light, reflected pulse width, reflected pulse frequency, optical pulse shape and frequency in time Light pulse shape.

In addition, for the illustrated embodiment, the sensor 80 is offset from the beam axis A and is configured to sense the characteristics of the reflected light along the beam axis A by redirecting at least a part of the reflected light with the redirecting lens 82; The redirecting lens 82 is located on the beam axis A, that is, intersects the beam axis A, and forms an angle of about 45 degrees with the beam axis A; however, in other exemplary embodiments, the redirecting lens 82 may define any other suitable with respect to the beam axis A In addition, the redirecting lens 82 may include a coating on the first side (ie, the side closest to the wall 66 of the airfoil 38) that makes the reflected light propagating along the beam axis A At least a portion of the airfoil 38 is redirected away from the proximal wall 66 and a portion of the airfoil 38 reaches the sensor 80; this coating may be a so-called "one-way" coating, so that there is substantially no beam direction towards the proximal wall 66 of the airfoil 38 The traveling light is redirected by the lens or its coating; for example, in certain embodiments, the coating may be an electron beam coating ("EBC") coating.

However, it should be understood that in other exemplary embodiments, the sensor 80 may alternatively be positioned in the beam axis A, and the laser beam 70 may be redirected; alternatively, the sensor 80 may be positioned in the airfoil 38 The outside is offset from the beam axis A and is configured to sense the characteristics of the light from the cooling hole 52 by defining a line of sight with the cooling hole 52; in other embodiments, one or more additional sensors (not shown) may be positioned in the cavity In the body 46, or alternatively in the cavity 46 It should be further understood that, in other embodiments, the sensor 80 may actually be located at any suitable position inside the cavity 46 and outside the airfoil 38. sensor.

Still referring to the exemplary system 60 of FIG. 3, the controller 68 may be any suitable processor-based computing device, and may communicate with, for example, a restricted laser drill 62, a sensor 80, and an operable recoil protection mechanism 74; for example, A suitable controller 68 may include one or more personal computers, mobile phones (including smart phones), personal digital assistants, tablet computers, laptop computers, desktop computers, workstations, game consoles, servers, other computers and any other Suitable computing equipment; as shown in Figure 3, the controller 68 may include one or more processors 84 and associated memory 86; the processor 84 may generally be any suitable processing equipment known in the art; similarly The memory 86 can generally be any suitable one or more computer-readable media, including but not limited to RAM, ROM, hard drives, flash drives or other storage devices; as generally understood, the memory 86 can be configured to store The information accessed by the processor 84 includes instructions or logic 88 that can be executed by the processor 84; the instructions or logic 88 can be any instruction set that enables the processor 84 to provide desired functions when executed by the processor 84; for example, instructions or logic 88 may be software instructions in a computer-readable form. When software is used, any appropriate programming, scripting, or other types of languages or combinations of languages can be used to implement the teachings contained herein; for example, in certain embodiments of the present disclosure, instructions or logic 88 can be configured to implement One or more methods described below with reference to Figures 6, 9 or 10; alternatively, instructions can be implemented by hard-wired logic 88 or other circuits, including but not limited to dedicated circuits; in addition, although the controller 68 is schematically It is shown separate from the sensor 80, but in other exemplary embodiments, the sensor 80 and the controller 68 may be integrated into a single device located in any suitable location.

In order to repair the airfoil, it may be necessary to derive certain information about one or more cooling holes 52 in the airfoil 38; for the embodiment of FIG. 3, the exemplary system 60 is configured to use a restricted laser drill 62 and sensors 80 to derive certain information about one or more holes 52 in the airfoil 38 to determine the maintenance status of one of the one or more holes 52; more specifically, the exemplary system 60 is configured to determine The position of each hole 52, the vector of each hole 52 and whether the hole 52 is blocked.

For example, still referring to FIG. 3, the system 60 is configured to determine the material into which the restricted laser beam 64 is directed based on the characteristics of the light sensed by the sensor 80; in some embodiments, the material sensed by the sensor 80 The characteristics of the light may be one or more wavelengths of the light reflected during the drilling operation; different materials absorb and reflect the light from the restricted laser beam 64 at different wavelengths; therefore, it is sensed by the sensor 80 during the drilling operation The received reflected light may define a wavelength or a pattern of wavelengths that indicates the material to which the restricted laser beam 64 is directed; for example, it is sensed by the sensor 80 when drilling into the metal portion 40 of the airfoil 38 The incoming light may define a pattern of wavelengths that is different from the wavelength pattern defined by the light sensed by the sensor 80 when drilling into the debris 90 located in the airfoil 38. One or more cooling holes 52, when the restricted laser beam passes completely through the proximal wall 66 of the airfoil 38, it may be different from the wavelength mode defined by the light sensed by the sensor 80 and is not directed to the wing In the metal portion 40 of the profile 38; however, it should be understood that in other exemplary embodiments, the characteristics of the light sensed by the sensor may additionally or alternatively include any material that indicates the restricted laser beam is directed to. Other characteristics.

Therefore, in some embodiments, the exemplary system 60 may use the restricted laser beam 64 of the restricted laser drill 62 essentially as a probe to derive certain information about one or more holes 52; more particularly, in certain In some embodiments, the controller 68 may receive one or more cooling holes in the airfoil 38 The original hole information of 52; the original hole information may include the original position of one or more holes 52 and the original vector of one or more holes 52; it may be in the form of an original design file such as a CAD design file or any other suitable Format to receive such raw hole information.

As shown in FIG. 3, the controller 68 can guide the restricted laser beam 64 of the restricted laser drill 62 to the original position of the first hole 92 and along the original vector of the first hole 92; it is worth noting that the restricted laser The drill 62 can be operated at a reduced power level to reduce the risk of damaging the proximal wall 66 of the airfoil 38; for the illustrated embodiment, the first hole 92 is in the original position and defines a vector V1 that is unchanged from the original vector. In addition, for the illustrated embodiment, there is no debris 90 in the first hole 92; therefore, when the restricted laser beam 64 of the restricted laser drill 62 is aligned with the original position of the first hole 92 and directed to the first hole along the original vector When there is a hole 92, the restricted laser beam 64 completely passes through the proximal wall 66 of the airfoil 38, so that the restricted laser beam 64 is not guided into the proximal wall 66 of the airfoil 38; the system 60 can determine the restricted laser beam 64 completely penetrates the proximal wall 66 of the airfoil 38 (for example, based on the characteristics of the light sensed by the sensor 80), so it is determined that the first hole 92 is complete and not blocked, and the Original position and original vector; it should be understood that, as used herein, determining the material into which the restricted laser beam 64 is directed includes determining that the restricted laser beam 64 is not directed into any material near the wall 66, but is completely Pass it through the proximal wall 66, ie completely through a hole in the proximal wall 66.

In contrast, referring now to FIG. 4, the restricted laser beam 64 of the restricted laser drill 62 is directed to the original position of the second hole 94 and along the original vector of the second hole; the position of the second hole 94 is the same as that of the second hole 94 The original position is the same, and the vector V2 defined by the second hole 94 is the same as the original vector of the second hole 94; however, in the illustrated embodiment, the debris 90 is positioned in the second hole 94 so that the restricted The laser beam 64 does not completely pass through the proximal wall 66 of the airfoil 38 at the second hole 94; the system 60 may determine to direct the restricted laser beam 64 into the debris 90 based on the characteristics of the light sensed by the sensor 80 ; As a sound Should, the system 60 can increase the power of the restricted laser drill 62 so that the restricted laser beam 64 of the restricted laser drill 62 ablates the debris 90, that is, drills through the debris 90; once the restricted laser drill 62 drills through the debris 90, and the restricted laser beam 64 has completely passed through the proximal wall 66 of the airfoil 38 and has not been guided into the proximal wall 66 of the airfoil 38, the system 60 can determine that the second hole 94 is complete and not It is blocked, and the original position and original vector of the second hole 94 can be confirmed.

In contrast, referring now to FIG. 4, the restricted laser beam 64 of the restricted laser drill 62 is directed to the original position of the second hole 94 and along the original vector of the second hole; the position of the second hole 94 is the same as that of the second hole 94 The original position is the same, and the vector V2 defined by the second hole 94 is the same as the original vector of the second hole 94; however, in the illustrated embodiment, the debris 90 is positioned in the second hole 94 so that the restricted laser The beam 64 does not completely pass through the proximal wall 66 of the airfoil 38 at the second hole 94; the system 60 may determine to direct the restricted laser beam 64 into the debris 90 based on the characteristics of the light sensed by the sensor 80; In response, the system 60 can increase the power of the restricted laser drill 62 so that the restricted laser beam 64 of the restricted laser drill 62 ablates the debris 90, that is, drills through the debris 90; once the restricted laser drill 62 has drilled through Debris 90, and the restricted laser beam 64 has completely passed through the proximal wall 66 of the airfoil 38 and is not guided into the proximal wall 66 of the airfoil 38, the system 60 can determine that the second hole 94 is complete and It is not blocked, and the original position and original vector of the second hole 94 can be confirmed.

Referring now to FIG. 6, a flow chart of an exemplary method (200) is provided for repairing one or more holes in the proximal wall of an airfoil, such as depicted in FIG. 2. And the airfoil as described above; the exemplary method (200) of FIG. 6 can be used in conjunction with the system 60 shown in FIGS. 3 to 5 and described above; therefore, although the example is described in the context of repairing an airfoil The exemplary method (200), but the exemplary method (200) may additionally or alternatively be used in conjunction with repairing any other suitable components of the gas turbine.

The exemplary method (200) includes at (202), using a controller to receive the original hole information of the first hole in the near wall of the airfoil; the original hole information of the first hole received at (202) includes the information of the first hole The original position and the original vector of the first hole; the exemplary method (200) further includes placing the restricted laser beam of the restricted laser drill at the original position of the first hole and along the original vector of the first hole at (204) Guide towards the near wall of the wing; more particularly, in certain exemplary aspects, at (204), the restricted laser beam may define the beam axis and guide the restricted laser beam along the original vector of the first hole, which may include The restricted laser beam is guided along the original vector of the first hole so that the beam axis of the restricted laser beam is aligned or substantially aligned with the original vector of the first hole.

The exemplary method (200) further includes sensing at (206) the characteristics of the light reflected from the original position of the first hole; in some exemplary aspects, sensing the characteristics of the light at (206) may include sensing the indication received The characteristic of light of the material (if any) to which the laser beam is directed is limited; for example, in certain exemplary aspects, sensing the characteristic of light at (206) may include sensing reflection from the original position of the first hole One or more wavelengths of the light; however, it should be understood that, in other exemplary aspects, the characteristic of sensing light at (206) may additionally or alternatively include any other suitable characteristic of sensing light of the indicating material, if If yes, introduce the restricted laser beam.

The method (200) also includes, at (208), determining the repair status of the first hole based on the characteristics of the light sensed at (206); more particularly, for the depicted embodiment, determining at (208) The repair state of the first hole includes determining at (210) the material (if any) to which the restricted laser beam is directed based on the characteristics of the light sensed at (206).

In a first alternative to the depicted exemplary aspect, the first hole may be in the original position and may extend along the original vector; in addition, the first hole may not include any debris or other contaminants blocked or otherwise blocked Passage through the first hole; in such an alternative , Determining the material (if any) to which the restricted laser beam is directed (210) includes determining at step (212) that the restricted laser beam completely passes through the proximal wall of the airfoil at the first hole. The confined laser beam is not directed to the near wall of the wing; in response to determining at (212) that the confined laser beam completely passes through the near wall of the airfoil, method (200) further includes determining at (214) that the hole is complete It is not clogged and the information of the first hole of the original hole is confirmed at (216).

Still referring to FIG. 6, and the first alternative is that, in response to confirming the original hole information of the first hole in (216), determining the repair status of the first hole in (208) also includes determining updated hole information in (218); More specifically, the method includes determining the updated position of the first hole and the updated vector of the first hole at (218); it is worth noting that for the first alternative, the updated hole information is equal to the original hole information, The updated position of the first hole is equal to the original position of the first hole, and the update vector of the first hole is equal to the initial position of the hole, that is, the original vector of the first hole.

However, in the second alternative, the first hole may be in the original position and may extend along the original vector, but may include debris or other contaminants blocking or blocking the passage through the first hole; therefore, at (208) Determining the repair status of the first hole, or more specifically, determining the material (if any) to which the restricted laser beam is directed at (210) includes determining at (220) whether the restricted laser beam is directed to In the debris within the first hole; in response to determining at (220) that the restricted laser beam is directed into the debris positioned within the first hole, the method (200) may further include modifying the restricted at (222) The operating parameters of the laser drill are to drill through the located debris. In the first hole near the wall of the wing; for example, in certain exemplary aspects, modifying the operating parameters at (222) may include controlling the power of a limited laser drill to drill through a hole positioned in the near wall of the airfoil Debris in the first hole; for example, modifying the operating parameters at (222) may include increasing the power of the limited laser drill, or alternatively may include reducing the power of the limited laser drill; however, in other exemplary aspects, Exemplary The method (200) may not include modifying operating parameters at (222), but, for example, the drill bit may already be operating at a sufficient power level to drill through such debris; however, in other exemplary aspects, the exemplary method ( 200) Instead of drilling through debris, holes can be marked for manual inspection.

Still referring to the second alternative, once the restricted laser beam has drilled through any and all debris positioned in the first hole, determining the repair status of the first hole at (208) also includes determining the first laser at (212) The restricted laser beam of the beam and the restricted laser drill pass completely through the near wall of the wing; similar to the first alternative discussed above, the exemplary method (200) then includes at (214) determining that the hole is complete and not Is blocked, and the original hole information of the first hole is confirmed at (216); in addition, the method (200) includes determining updated hole information at (218). In this alternative, the updated hole information is again equal to the original hole information.

In addition, in the third alternative, the first hole may not be in the original position and may not extend along the original vector; in such an alternative, determine the material (if any) to which the restricted laser beam is directed ( 210) includes determining at step (224) that the restricted laser beam is directed at least partially into the near wall of the wing (which may include, for example, the metal part of the airfoil and the coating on the metal part of the airfoil; in response, Determine the repair status, the first hole at (208) is additionally included at (226), it is determined that the near wall of the wing has been at least partially deformed, and for the exemplary aspect shown, search or repair at (228) The subroutine determines the first hole of the new information; the new information of the first hole can include the new position of the first hole and the new vector of the first hole; in some aspects, the repair subroutine can make restricted laser drilling Move around the original position of the first hole in a spiral pattern to determine the new position of the first hole and the new vector of the first hole; in such an alternative, determining the repair state of the first hole in (208) may also include Determine the updated hole information in (218); in such an alternative, the updated hole information determined in (218) is equal to the new hole information determined in (228); More specifically, in such an alternative, the updated position of the first hole is equal to the new position of the first hole, and the updated vector of the first hole is equal to the new vector of the first hole; in addition, in such an alternative , Determining the updated hole information at (218) may additionally include: in view of the updated hole information of the first hole, updating the hole information of one or more additional holes; more specifically, in this alternative, the method (200 ) The new hole information of one or more additional holes can be estimated based on the deformation amount of the component indicated by the new hole information of the first hole determined at (228).

However, it should be understood that in other exemplary aspects, the method (200) may additionally or alternatively include, for example, marking the first hole for manual inspection in response to the determination at (224) that the restricted laser beam is aligned, at least partially Enter the near wall of the airfoil and determine at (226) that the near wall of the airfoil has been at least partially deformed; in addition, in other exemplary aspects, the repair subroutine may include any other suitable information for determining new information for the first hole method.

Although not shown in FIG. 6, the exemplary method (200) may further include determining updated hole information for a plurality of cooling holes in the airfoil (such as all cooling holes in the near wall of the airfoil); therefore, the method (200) may further include receiving the original hole information of the second hole in the near wall of the airfoil together with the controller; the original hole information of the second hole may also include the original position of the second hole and the original vector of the second hole; The method (200) may further include: at the original position of the second hole and along the original vector of the second hole, directing the restricted laser beam of the restricted laser drill toward the near wall of the airfoil, thereby following the restricted The laser beam is substantially aligned with the original vector of the second hole; the method (200) may further include sensing the characteristics of the light reflected from the original position of the second hole, and based on the sensed second hole The characteristics of the light reflected from the original position of the hole are used to determine the repair status of the second hole; the method (200) may further include determining the updated hole information of the second hole; it is worth noting that, in some exemplary aspects, determining the second hole The repair status of the hole may include the above-mentioned determination in (208) Any and all alternatives to the repair state of a hole.

The exemplary method (200) depicted in Figure 6 can assist in the repair of the wing; more particularly, removing debris from one or more cooling holes can allow such cooling holes to operate correctly; in addition, inferred information can For example, to facilitate additional steps in the repair process; for example, information derived using the exemplary method (200) can facilitate the exemplary method (300) described below with reference to FIG. 9 and the exemplary method (400) described below with reference to FIG. 10 One or two; additionally or alternatively, the information derived using the exemplary method (200) may allow a determination of whether additional repairs are possible, or whether and to what extent additional repairs to this airfoil are required .

In addition, although not shown, the exemplary method (200) of FIG. 6 may further include moving the restricted laser drill to the location of additional holes, and repeating the process discussed herein to determine each corresponding additional hole The updated hole information.

Referring now to FIG. 7, a schematic diagram of an exemplary system 60 is provided for repairing one or more holes 52 in the proximal wall 66 of the airfoil 38 of a gas turbine; the exemplary system 60 depicted in FIG. 7 may be configured To work in conjunction with the exemplary system 60 of FIG. 3, and may be configured in substantially the same manner as the exemplary system 60 of FIG. 3; therefore, the same or similar numbers may refer to the same or similar parts.

For example, the exemplary system 60 of FIG. 7 includes a restricted laser drill 62 that utilizes a restricted laser beam 64, a sensor 80, and a controller 68 operably connected to the restricted laser drill 62 and the sensor 80; as shown, the sensor 80 is positioned to sense the characteristics of the light reflected along the beam axis A of the restricted laser beam A away from the airfoil 38; for example, when the restricted laser beam is directed at the near wall 66 of the airfoil 38 In the case of the first hole 92, the sensor 80 is configured to sense light from the updated position of the first hole 92 in the proximal wall 66 of the airfoil 38.

After determining the updated hole information of one or more cooling holes 52 in the proximal wall 66 of the airfoil 38, the exemplary system 60 of FIG. 7 may be utilized; the updated hole information may include the updated position of each hole 52 and each The update vector of the hole 52; in some embodiments, the exemplary method (200) described above with reference to FIG. 6 or alternatively any other suitable method can be used to determine the updated hole information.

Moreover, after recoating the outer surface 34 of the airfoil, the exemplary system 60 of FIG. 7 can be utilized; recoating the outer surface 34 of the airfoil 38 can include adding one or more of the following: thermal barrier coating 36. Bonding coating 98, environmental barrier coating (which can be composed of multiple layers of different materials) or any other suitable coating; as shown in the figure, recoating the outer surface 34 of the airfoil 38 includes coating the airfoil At least a portion of one or more holes 52 in the proximal wall 66 of the airfoil member 38; therefore, after recoating the outer surface 34 of the proximal wall 66 of the airfoil member 38, one of the proximal walls 66 of the airfoil member 38 or The plurality of holes 52 may be at least partially covered by the coating and have the coating positioned therein (as shown).

However, the exemplary system 60 of FIG. 7 can remove the coating covering one or more holes 52 and positioned in the one or more holes 52 without damaging the metal portion 40 below the proximal wall 66 of the airfoil 38; More specifically, the exemplary system 60 of FIG. 7 can determine the material to which the restricted laser beam 64 of the restricted laser drill 66 is directed, using one or more characteristics of the light sensed by the sensor 80 to determine the "laser beam ", and determine the depth to which the laser beam 64 has been limited.

For example, as described above, the sensor 80 can sense one or more characteristics of light indicating the material to which the restricted laser beam 64 of the restricted laser drill 62 is directed; for example, the sensor 80 can sense one or more wavelengths Light; the sensor 80 may additionally or alternatively sense one or more characteristics of light indicating the depth to which the restricted laser beam 64 of the restricted laser drill 62 has been drilled; for example, the sensor 80 may sense the following One or more of: reflected pulse rate, reflected pulse width, The light intensity, the amount of noise in the light intensity, or any other suitable characteristic; however, it should be understood that in other embodiments, the sensor 80 may additionally or alternatively sense the direction to which the constrained laser beam 64 is directed. One or both of the materials and any other suitable characteristics of the light to the depth to which the confined laser beam 64 has drilled.

Therefore, as shown in FIG. 7, the restricted laser drill 62 may be positioned to direct the restricted laser beam 64 over the first hole 92 in the proximal wall 66 of the airfoil 38 to remove the extension and be positioned on the first wing. The coating on the profile 38, the hole 92 on the proximal wall 66 of the airfoil 38; more specifically, the restricted laser drill 62 can be moved to the updated position of the first hole 92 to drill through the first hole 92 The coating extending on the hole 92 and positioned on the first hole 92 (as shown in the figure); it is worth noting that the restricted laser drill 62 can be positioned such that the beam axis A of the restricted laser beam 64 is substantially not along the The vector V1 defined by the first hole 92 extends, more specifically, the update vector along the first hole; more particularly, for the depicted embodiment, the restricted laser drill 62 is positioned such that the restricted laser beam The beam axis A of 64 is substantially perpendicular to the outer surface 34 of the metal portion 40 near the wall 66; such a configuration may allow for a more convenient repair process; however, it should be understood that in other exemplary embodiments, the limited laser drill may be 62 is positioned such that the beam axis A of the restricted laser beam 64 extends along or substantially along the update vector of the first hole 92.

Referring now to FIG. 8, an exemplary system 60 is shown that has drilled through the coating over and in the first hole 92 in the proximal wall 66 of the airfoil 38; One or more characteristics of the light sensed by the sensor 80, the system 60 can determine that the restricted laser bit 62 has drilled the coating extending through and positioned in the first hole 92 in the proximal wall 66 of the airfoil 38 The system 60 can then stop the drilling operation to prevent unnecessary damage to the first hole 92 in the proximal wall 66 of the airfoil 38; however, it is worth noting that, in certain exemplary embodiments, The opening of the first hole 92 may be larger than the width of the restricted laser beam 64; therefore, in such an exemplary implementation For example, the system 60 can continue drilling-covering the entire position of the first hole, that is, the entire opening of the first hole-until the entire coating that extends over and lies in the opening of the first hole is drilled through And remove.

After removing the coating that extends over the first hole and is located in the first hole, the exemplary system 60 can be moved to the renewal position of the second hole 94, the renewal position of the third hole 96, etc.; remove the covering on the airfoil 38 has a coating on and located in each of the plurality of cooling holes 52 in the proximal wall 66.

Referring now to FIG. 9, there is provided a flowchart of an exemplary method (300) of repairing one or more holes in the proximal wall of an airfoil, such as depicted in FIG. 2 and as described above The exemplary method of FIG. 9 can be used in conjunction with the system 60 shown in FIGS. 7 and 8 and described above; therefore, although the exemplary method (300) is described in the context of repairing an airfoil, but The exemplary method (300) may additionally or alternatively be used to repair any other suitable components of a gas turbine.

The exemplary method (300) of FIG. 9 includes using restricted laser drilling to determine updated hole information of the first hole in (302); the updated hole information of the first hole determined in (302) may include the updated hole information of the first hole Position and updated vector of the first hole; in some exemplary aspects, the exemplary method (200) depicted in FIG. 6 and described above can be used to complete the determination of updated hole information for the first hole at (302) For example, in some aspects, determining the updated hole information of the first hole at (302) may include: receiving the original information of the first hole in the near wall of the airfoil, the original information including the original position of the first hole And the original vector of the first hole; determine that the first hole is complete and not blocked; and confirm the original hole information of the first hole; however, alternatively, in other exemplary aspects, any can be used in (302) Other suitable means or methods to determine the first hole New hole information.

After determining the updated hole information of the first hole in step (302), the exemplary method (300) may further include (304) applying a coating on the outer surface of the proximal wall of the airfoil; there is no need to apply on the first hole Any covering or other similar protection can be applied to the outer surface of the wing near the wall at (304); therefore, applying the coating at (304) may include extending the coating at least partially and Positioned in the first hole.

Still referring to the exemplary method (300) of FIG. 9, the exemplary method (300) further includes, at (306), directing the restricted laser beam of the restricted laser drill toward the near wall of the wing at the updated position of the first component. The hole is drilled through the coating that extends and is located in the first hole near the wall; in some exemplary aspects, the restricted laser beam may define the beam axis, and the restricted laser drilled by the restricted laser at (306) Directing the beam toward the near wall of the wing may include directing the restricted laser beam toward the near wall of the wing such that the beam of the laser beam bound by the beam axis is not parallel to the update vector of the first hole; for example, in some examples In terms of sex, directing the restricted laser beam of the restricted laser drill toward the near wall of the wing at (306) may include directing the restricted laser beam toward the near wall of the airfoil so that the beam axis of the restricted laser beam is approximately The outer surface perpendicular to the proximal wall of the wing; such a configuration may allow more convenient removal of the coating that extends over and is positioned in the first hole in the proximal wall of the airfoil.

However, it should be understood that in other exemplary aspects, the beam axis may define any suitable angle with respect to the update vector of the first hole; for example, in other exemplary aspects, a restricted laser beam may be directed toward the near wall of the wing , So that the beam axis extends substantially along the update vector of the first hole.

Still referring to FIG. 9, the exemplary method (300) further includes sensing at (308) the characteristics of light reflected from the updated position of the first hole; in addition, the exemplary method includes sensing at (310) based on the sensed light Characteristics, confirm that the restricted laser beam of the restricted laser drill has penetrated the coating of the airfoil, the The coating of the airfoil extends and is located in the first hole in the proximal wall of the airfoil and in the first hole in the proximal wall of the airfoil at (308); for the exemplary aspect depicted, at (308) Sensing the characteristic of light reflected from the updated position of the first hole includes sensing one or more characteristics of light indicating the material to which the restricted laser beam is directed; more particularly, in the depicted exemplary aspect, The characteristic of sensing light reflected from the update position of the first hole at (308) includes sensing one or more wavelengths of the light reflected from the update position of the first hole at (312); however, in other exemplary aspects The characteristics of sensing light reflected from the updated position of the first hole at (308) may additionally or alternatively include sensing any other characteristics of light indicative of the material to which the confined laser beam is directed.

In addition, for the depicted exemplary aspect, determining the restricted laser beam of the restricted laser drill that has drilled through the coating of the airfoil includes determining the material to which the restricted laser beam of the restricted laser drill is directed; for example, As described above, the light of one or more wavelengths reflected from the region where the constrained laser beam is incident can indicate the material on which the constrained laser beam is incident; more specifically, once it is determined that the constrained laser beam is directed to the wall near the wing For the metal part, it can be determined that the restricted laser beam has penetrated through the coating that extends and is located in the first hole on the proximal wall of the wing.

Therefore, the depicted exemplary (300) method may allow recoating of the proximal wall of the airfoil during repair operations without the need to take measures to cover or otherwise prevent such coating in the proximal wall of the airfoil One or more cooling holes extend over and are located within; such a process may allow a more cost-effective and time-efficient method for repairing airfoils or other components for gas turbines.

Referring now to FIG. 10, a flowchart of another exemplary method (400) is provided for repairing one or more holes in the proximal wall of an airfoil, such as the airfoil depicted in FIG. 2 and described above Piece 38; the exemplary method (400) of FIG. 10 can be compared with that shown in FIGS. 7 and 8 and the above The systems 60 described above are used in combination; in addition, the exemplary method (400) of FIG. 10 is similar to the exemplary method (300) of FIG. 9, so similar numbers may refer to the same or similar steps.

For example, the exemplary method (400) of FIG. 10 includes: using a restricted laser drill at (402) to determine updated hole information for a first hole; and at (404) applying a coating to the near wall of the wing The outer surface is such that the coating is at least partially extended and located in the first hole; in addition, the exemplary method (400) of FIG. 10 includes in (406) placing the restricted laser beam of the restricted laser drill at the updated position of the first hole Guide towards the proximal wall of the airfoil to drill through that part of the coating. Extends and is located in the first hole; in addition, the exemplary method (400) of FIG. 10 includes sensing at (408) the characteristics of the light reflected from the updated position of the first hole, and determining the limit at (410) The limited laser beam of the laser drill has penetrated the coating to drill out the change of the airfoil shape at the update position of the first hole based on the characteristics of the light sensed at (408).

In addition, for the exemplary aspect depicted in FIG. 10, determining at step (410) that the restricted laser beam of the restricted laser drill has drilled through the coating of the airfoil includes determining at step (414) that the restricted laser drill is subjected to Limit the depth of the laser beam. The airtight laser drill has been drilled; further, for the exemplary aspect shown, the method (400) also includes determining the depth of the coating in step (416), and determining in step (418) in step (414) The depth into which the restricted laser beam of the restricted laser drill has been drilled is compared with the depth of the workpiece, and the coating is determined at (416); for example, the exemplary method (400) can be applied to the coating at (416) Determine the depth of the coating on the fin or coupon, where the fin is separated from the airfoil, when the coating is applied to the outer surface of the airfoil at (404), and measure the coating depth on the tab The depth of the coating on the airfoil can indicate the depth of the coating on the outer surface of the airfoil, and therefore can indicate that the limited laser beam of the limited laser drill must drill the depth to which the coating extends. And located in the first hole; once the restricted laser beam of the restricted laser drill has been The determined depth of drilling is equal to or within a predetermined threshold of the determined coating depth, then the method (400) can determine that the limited laser beam of the limited laser drill has drilled through the airfoil coating at the updated position of the first hole The updated position extends and is located in the first hole.

Notably, in certain exemplary aspects, the exemplary method (400) may additionally include modifying the geometry of the first hole according to certain parameters input during the repair; for example, during the repair, it may be determined, for example, to To obtain better aerodynamics, the opening of the first hole on the near wall of the airfoil should be wider, deeper and should define a different shape; therefore, a limited laser drill can extend and extend over the first hole. The coating positioned in the first hole is drilled deeper to provide the desired updated geometry of the first hole.

In addition, although not shown, the exemplary method (300) of FIG. 9 and the exemplary method (400) of FIG. 10 may further include moving the restricted laser drill to the updated position of the additional hole, and repeating what is discussed herein The process is to drill through, a part of the coating extends and is located in each corresponding additional hole.

10: Turbo part

12: Rotor

14: shell

16: gas path

18: Centerline

20: rotor wheel

22: Rotor spacer

24: Bolt

26: working fluid

30: Rotating blade

32: fixed blade

Claims (7)

A repair system for a hole in a near wall of a component, the repair system comprising: a restricted laser drill using a restricted laser beam; and a sensor positioned to sense light reflected from the updated position of the first hole in the near wall of the component Characteristics; and a controller operably connected to the restricted laser drill and the sensor, the controller configured to determine updated hole information of the first hole in the near wall of the component, the updated hole information of the first hole including the update of the first hole The location is on the near wall; the restricted laser beam is directed toward the near wall of the component at the update location of the first hole to drill through the component coating extending and located in the first hole; and based on reflection from the update location of the first hole The sensor senses the characteristics of the light and determines that the restricted laser beam of the restricted laser drill has penetrated and extended the coating in the first hole. The repair system for the hole in the near wall of the component as described in the first item of the scope of patent application, wherein the restricted laser beam defines the beam axis, and the controller is further configured to guide the restricted laser beam toward the near wall of the component , So that the beam axis of the restricted laser beam is substantially perpendicular to the outer surface of the component near the wall. The repair system for the hole in the near wall of the component as described in the first item of the scope of patent application, wherein the restricted laser beam defines a beam axis, and the updated hole information further includes an update vector of the first hole The controller is also configured to direct the restricted laser beam toward the near wall of the component so that the beam axis of the restricted laser beam is not parallel to the update vector of the first hole. The repair system for the hole in the near wall of the component as described in the scope of patent application 1, wherein the controller is configured to determine to direct the restricted laser beam of the restricted laser drill to the material to determine the restricted laser drill The restricted laser beam has been drilled through the coating of the component. The repair system for the hole in the near wall of the component as described in claim 4, wherein the characteristic of the light sensed by the sensor includes reflecting one or more wavelengths of light from the updated position of the first hole. The repair system for the hole in the near wall of the component as described in the first item of the scope of patent application, wherein, after determining that the restricted laser beam of the restricted laser drill has been drilled through the coating of the component When the time, the controller is further configured to determine that the restricted laser beam of the restricted laser drill has been drilled to a required depth. According to the sixth item of the scope of patent application, the repair system for the hole in the near wall of the component, wherein the characteristics of the light sensed by the sensor include one or two of the reflected pulse width and the reflected pulse frequency.

Images