DE102020003254A1 - Method and control device for manufacturing a multi-part rotor of a gas turbine engine - Google Patents

Abstract

A method for producing a multi-part rotor (34) with a rotor disk (35) and with several rotor blades (36), which are in operative connection with the rotor disk (35), is arranged over the circumference (U) of the rotor disk (35) and extending radially outwardly with respect to the rotor disk (35). An arrangement of the rotor blades (36) on the rotor disk (35) is determined which is characterized by an imbalance in the rotor (34) which is less than a limit value. Radial distances between an axis of rotation (43) of the rotor (34) and rotor blade tips (42) and the contact surfaces (F37, F38) are determined. Differences between the radial distances between the axis of rotation (43) and the rotor blade tips (42) and further radial distances between the axis of rotation (43) and the rotor blade tips (42) when the rotor blade tips (42) in the circumferential direction (U) on a circle around the axis of rotation (43) are determined. In addition, a change in mass of each rotor blade (36) is determined as a function of the respectively determined difference. The imbalance of the rotor (34) is determined as a function of the determined changes in mass of the rotor blades (36).

Description

The present disclosure relates to a method for manufacturing a multi-part rotor of a gas turbine engine. The disclosure also relates to a control device for performing the method and a corresponding computer program product.

It is known that rotors of gas turbine engines are produced from several individual components. The so-called balancing represents an important production step. Before the production of a rotor using balancing, the individual parts are first cleaned according to the previous production processes.

Before the turbine and compressor rotors are assembled, the blades to be mounted on the rotor blades are weighed individually and, in order to compensate for a known imbalance of the rotor disk, are each mounted in defined positions on the circumference of the respective rotor disk. An attempt is made to compensate for an imbalance in the rotor disk and thus also in the entire rotor in a targeted manner and without adding balancing weights.

The assembly of the rotor, in particular the assembly of the blades, is followed by a balancing test of the rotor and a metrological determination of the blade tip diameter. Then the blade tip diameters are machined using material-removing processes, such as grinding or the like, in order to make the outer diameter of the rotor, which is defined by the blade tips, with a corresponding roundness in relation to an axis of rotation of the rotor and to produce the required blade tip diameter. This production step is also known as cylindrical grinding of the rotor. In this process step, suitable measures, such as generating a sufficiently high centrifugal force by selecting a suitable rotor speed during grinding, ensure that the blades are held in their later operating position. A process control is carried out during cylindrical grinding. The blade tip diameters are measured during the cylindrical grinding process. This can take place on one and the same rotor in different measuring planes and diameters that differ axially from one another.

Another balancing test follows the cylindrical grinding of the rotor. Depending on the measurement result of the balancing test, if necessary, a balancing correction in the form of material removal is carried out in defined balancing areas of the rotor. In addition, the balancing correction can be followed by a new balancing test in order to determine whether the rotor has the desired imbalance after the balancing correction. However, this procedure is characterized by a high manufacturing cost.

Also from the US 7 497 662 B2 and from the US 2019/0332743 A1 Known methods, each of which relates to a defined arrangement of rotor blades on a rotor disk of a rotor of a gas turbine engine, do not contribute to simplifying the manufacture of rotors.

The present disclosure is based on the object of creating a method for manufacturing a multi-part rotor of a gas turbine engine, by means of which a rotor of a gas turbine engine can be manufactured in a simple manner with as little imbalance as possible. In addition, a control device, which is designed to carry out the method, and a computer program product for carrying out the method are to be specified.

From a procedural point of view, this object is achieved with a method with the features of patent claim 1 and 2, respectively. A control device and a computer program product are also the subject of the further independent claims. Advantageous further developments are the subject of the subclaims and the following description.

A method for producing a multi-part rotor of a gas turbine engine with at least one rotor disk and with a plurality of rotor blades is proposed. In the assembled state, the rotor blades are in operative connection with a rotor disk, are arranged distributed over the circumference of the rotor disk and extend outward in the radial direction with respect to the rotor disk.

The disclosure now comprises the technical teaching that an arrangement of the rotor blades on the rotor disk is determined which is characterized by an imbalance of the rotor that is less than a limit value. The rotor blades are then mounted on the rotor disk and radial distances between a rotor axis of the rotor and the mounted rotor blade tips are measured.

Furthermore, differences between the measured radial distances between the axis of rotation and the rotor blade tips and further radial distances are determined. The further distances correspond to distances between the axis of rotation of the rotor and the rotor blade tips if the rotor blade tips lie in the circumferential direction of the rotor on a circle around the axis of rotation of the rotor. Thus, they correspond Differences in length changes in the rotor blades that result from the cylindrical grinding of the mounted rotor.

Such changes in length of the rotor blades cause changes in the masses of the rotor blades and therefore possibly influence the imbalance of the rotor.

Therefore, the changes in mass of the rotor blades are computationally determined as a function of the differences determined in each case between the radial distances and the further radial distances. An imbalance of the rotor is theoretically determined as a function of the determined changes in mass of the rotor blades.

Furthermore, an alternative method for producing a rotor of a gas turbine engine with at least one rotor disk and with a plurality of rotor blades is proposed. The rotor blades are arranged distributed over the circumference of the rotor disk. In addition, in the area of the blade roots, the rotor blades each have contact surfaces that are primarily radially outwardly facing with respect to the rotor disk. The rotor blades are in operative connection with their contact surfaces in the radial direction of the rotor disk in each case with contact surfaces of the rotor disk, which are primarily directed radially inward, and are thus held in the rotor disk in the radial direction.

In addition, an arrangement of the rotor blades on the rotor disk is theoretically determined, which is characterized by an imbalance of the rotor smaller than a limit value. In addition, radial distances between an axis of rotation of the rotor and the rotor blade tips are theoretically determined as a function of the geometrical data of the rotor disk and the rotor blade determined by measurement.

In addition, differences between the radial distances between the axis of rotation and the rotor blade tips and further radial distances between the axis of rotation and the rotor blade tips are determined. The further radial distances correspond to distances between the axis of rotation and the rotor blade tips when the rotor blade tips lie in the circumferential direction on a circle around the axis of rotation of the rotor.

Changes in the mass of the rotor blades are determined as a function of the determined differences between the radial distances. Finally, the imbalance of the rotor is determined as a function of the theoretically determined changes in mass of the rotor blades.

The alternative method according to the present disclosure offers the possibility, in a cost-effective manner, of determining the arrangement of the rotor blades on the rotor disk without prior assembly of the rotor blades on the rotor disk. However, compared to the procedure in which the radial distances between the axis of rotation of the rotor and the already mounted rotor blade tips are determined by measurement, this alternative procedure is characterized by a greater measurement effort.

Regardless of this, when arranging the rotor blades on the rotor disk, both procedures take into account the change in mass of the rotor blades that occurs during cylindrical grinding of the fully assembled rotor.

Both methods according to the present disclosure are based on the knowledge that both the rotor disk and the rotor blades to be mounted on the rotor disk are subject to tolerances and therefore both geometric dimensions and their masses vary within permissible tolerance fields. Even a small local offset when installing the rotor blades on the rotor blade causes a radial positional deviation of the individual blades relative to the optimal radial position. Such a deviation results, for example, from shape deviations due to tolerances or radial position deviations of the blade receiving groove in relation to the axis of rotation of the rotor.

Furthermore, deviations in shape or radial position deviations of the blade also cause a variation in the distance between the load-bearing contact surface and the blade center of gravity. This then leads to different resulting blade lengths and thus to small changes in the individual mass of the rotor blades if the rotor blades are finish-machined to the target diameter after assembly in the area of their rotor blade tips during cylindrical grinding. Then the masses of the individual machined rotor blades and the mass distribution are changed, which can lead to a deviation of the resulting imbalance from the target state. As is well known, this has to be compensated for by a complex final balancing test and an optional fine balancing inspection.

The rotor blades are mounted on the rotor disk by means of the procedures according to the present disclosure with an optimized arrangement which reduces or compensates for any imbalance of the rotor disk that may be determined by the mounted rotor blades. However, when the rotor blades are arranged on the rotor disk, there is also an additional, if necessary Material removal taken into account during cylindrical grinding. This ensures that the rotor is available with a desired low imbalance at the end of its manufacturing process.

In an advantageous variant of the method according to the present disclosure, the assembly positions of the rotor blades on the rotor disk are theoretically determined as a function of a measured imbalance of the rotor disk and as a function of the masses of the rotor blades recorded by measurement.

The mounting positions of rotor blades can be changed and / or at least one mounted rotor blade can be exchanged for a further rotor blade. The exchange can then be carried out when the determined imbalance of the rotor, which is determined as a function of the theoretical changes in mass of the rotor blades, is greater than or equal to the limit value. It can be provided that by changing the mounting positions of the rotor blades and / or by replacing at least one rotor blade with a rotor blade that has not yet been mounted on the rotor disk, the value of the determined unbalance of the rotor is changed in such a way that the the determined unbalance is smaller than the limit value. The rotor can then be produced in a simple manner with low manufacturing costs and with as little unbalance as possible.

Radial distances between the contact surfaces of the rotor disk and the axis of rotation of the rotor can be determined by measurement. An arrangement of a rotor blade on the rotor disk can thus be determined with little effort.

There is also the possibility that radial distances between the contact surfaces of the rotor blades and their rotor blade tips in the longitudinal direction of the rotor blades or in the radial direction of the rotor disk are determined by measurement. The radial protrusion of the rotor blade tip of a rotor blade relative to the outside of the rotor can then be determined without having to mount the rotor blade on the rotor disk. On the basis of this knowledge, the difference between the radial distance between the axis of rotation and the rotor blade tip and the further radial distance between the axis of rotation of the rotor and the rotor blade tip can also be determined without mounting the rotor blades on the rotor disk.

The difference between the last-mentioned radial distances corresponds to a shortening of the length in the area of one rotor blade in each case, which results from the material removal in the area of the rotor blade tip during the cylindrical grinding of the fully assembled rotor.

The changes in mass of the rotor blades that occur during the cylindrical grinding of the rotor are each determined in a further advantageous variant of the method according to the present disclosure with little measurement effort as a function of CAD data of the rotor blades. The determination of the mass changes of the rotor blades as a function of CAD data and not as a function of the actually available geometry data of the rotor blades is possible, since the tolerance-affected deviations between the actual values and the target values have essentially no influence on the determined mass changes of the rotor blades .

If the assembly positions of the rotor blades and also the mass changes of the rotor blades are theoretically determined by the cylindrical grinding of the rotor, the rotor blades are mounted on the rotor disk according to the theoretically determined assembly positions. The rotor can then be ground straight away and manufactured without having to carry out a subsequent balancing test.

The rotor can be ground round, e.g. by radially grinding the rotor blade tips, until the rotor blade tips lie on the circular line and the diameter of the determined circle to be achieved. In advantageous variants of the method according to the present disclosure, this is carried out when the imbalance of the rotor, which is determined as a function of the determined changes in mass of the rotor blades, is smaller than a limit value. This ensures that the rotor has a desired low unbalance at the end of the manufacturing process.

The invention further relates to a control device which is designed to carry out the method according to the present disclosure. The control device comprises, for example, means that are used to carry out the method according to the present disclosure. These means can be hardware-based means and software-based means. The hardware-based means of the control device or the control device are, for example, data interfaces in order to exchange data with the measuring devices involved in carrying out the method according to the present disclosure. Further hardware means are, for example, a memory for data storage and a processor for data processing. Means on the software side can, among other things, be program modules for carrying out the method according to the invention.

In order to carry out the method according to the present disclosure, the control device can be executed with at least one receiving interface which is designed to receive signals from signal transmitters. The signal transmitters can, for example, be designed as sensors that detect measured variables and transmit them to the control unit. A signal transmitter can also be referred to as a signal sensor. The receiving interface can receive a measurement signal from a signal transmitter.

The control device can also have a data processing unit and to evaluate and / or process the received input signals or the information from the received input signals.

The control device can also be designed with a transmission interface which is designed to output control signals to actuators. An actuator is understood to mean actuators that implement the commands from the control unit. The actuators can, for example, be handling means by means of which the rotor blades and the rotor disk can be handled.

If the control unit recognizes or uses received input signals to determine that a multi-part rotor of a gas turbine engine is to be manufactured, then the control unit uses the recorded input signals to determine an arrangement of the rotor blades on the rotor disk, which is characterized by an unbalance of the rotor smaller than a limit value.

The control unit also determines radial distances between an axis of rotation of the rotor and the rotor blade tips. In addition, the control unit determines differences between the measured radial distances between the axis of rotation and the rotor blade tips and further radial distances between the axis of rotation and the rotor blade tips. Furthermore, the control unit determines changes in the mass of the rotor blades as a function of the respectively determined difference between the radial distances. In addition, the control unit determines the imbalance of the rotor as a function of the determined mass changes of the rotor blades.

Furthermore, the control device can determine radial distances between an axis of rotation of the rotor and the rotor blade tips as a function of the geometrical data of the rotor disk and the rotor blades determined by measurement. The control device can then determine the differences between the radial distances between the axis of rotation and the rotor blade tips and further radial distances between the axis of rotation and the rotor blade tips with little effort.

As a result, a multi-part rotor of a gas turbine engine can be produced with the lowest possible unbalance and, at the same time, low assembly costs. The low assembly effort results when the arrangement of the rotor blades is based on the handling of the rotor disk solely on the basis of measured values or geometry data of the rotor disk and the rotor blades as well as a theoretically determined change in mass that occurs during cylindrical grinding or other processing of the blade tips of the fully assembled rotor is determined.

The signals mentioned above are to be regarded as exemplary only and are not intended to restrict the subject matter of the present disclosure. The recorded input signals and the output control signals can be transmitted via a signal line. The control device or the control device can be designed, for example, as a central electronic control device of a manufacturing plant.

The solution according to the present disclosure can also be embodied as a computer program product which, when it runs on a processor of a control device, instructs the processor in software to carry out the assigned method steps. In this context, the subject matter of the present disclosure also includes a computer-readable medium on which an above-described computer program product is stored in a retrievable manner.

As an alternative to the described method with the finishing of the blade tips following the assembly of the rotor, the blades to be assembled on the rotor can be carried out with knowledge of the rotor and blade geometries, in particular the respective contact surfaces between rotor and blades and the change in blade tip geometry that is required in each case on the blade, can also be manufactured as a single blade to the dimensions determined by the control unit. This ensures that, after the subsequent assembly of the blades, the rotor is present with the desired unbalance and the desired geometry, especially with regard to the roundness, the diameter of the blades and the desired low unbalance. This development of the method further simplifies the manufacturing process, since blade tip machining on the mounted rotor can be partially or completely dispensed with.

The present disclosure is not limited to the specified combination of the features of the independent claims or the claims dependent thereon. It surrender in addition, possibilities to combine individual features with one another, also to the extent that they emerge from the claims, the following description of embodiments and directly from the drawing. The reference of the claims to the drawings through the use of reference signs is not intended to limit the scope of protection of the claims.

• 1 eine schematisierte Längsschnittansicht eines Gasturbinentriebwerkes;
• 2 eine stark schematisierte Seitenansicht eines mehrteiligen Rotors des Gasturbinentriebwerkes gemäß 1;
• 3 eine teilweise Querschnittansicht des mehrteiligen Rotors gemäß 2;
• 4 eine 3 entsprechende Darstellung des Rotors; und
• 5 eine 3 entsprechende Darstellung des Rotors, der Positionsänderungen einer Rotorschaufelspitze entnehmbar sind, die aus Rundheitsabweichungen und Exzentrizitäten des Rotors resultieren.

Preferred developments emerge from the subclaims and the following description. An exemplary embodiment of the subject matter according to the present disclosure is explained in more detail with reference to the drawing, without being restricted thereto. It shows:

• 1 a schematic longitudinal sectional view of a gas turbine engine;
• 2 a highly schematic side view of a multi-part rotor of the gas turbine engine according to FIG 1 ;
• 3 a partial cross-sectional view of the multi-part rotor according to FIG 2 ;
• 4th one 3 corresponding representation of the rotor; and
• 5 one 3 Corresponding representation of the rotor, from which changes in the position of a rotor blade tip can be taken that result from deviations in roundness and eccentricities of the rotor.

In 1 is a jet engine 1 and gas turbine engine shown, which have a main and rotational axis 12th having. It also includes the jet engine 1 in the axial direction of flow A. an air inlet 3 , a horn player 4th , a planetary gear 25th , an intermediate pressure compressor 15th , a high pressure compressor 16 , an incinerator 17th , a high pressure turbine 18th , a low pressure turbine 19th and an exhaust nozzle 7th . An engine nacelle 5 surrounds the gas turbine engine 1 and limits admission 3 .

The jet engine 1 works in a conventional manner, being in the inlet 3 incoming air through the blower 4th is accelerated to create two streams of air. A first air stream flows into the intermediate pressure compressor 15th and a second air flow is through a bypass duct 22nd or bypass duct to provide a drive thrust. The intermediate pressure compressor 15th compresses the air flow supplied to it before the air in the area of the high-pressure compressor 16 is further compressed.

The one from the high pressure compressor 16 escaping compressed air is in the incinerator 17th initiated, where it is mixed with fuel and the fuel-air mixture is burned. The resulting hot combustion products expand and drive the high-pressure turbine 18th and the low pressure turbine 19th before going over the discharge nozzle 7th be performed to provide additional drive thrust. The high pressure turbine 18th and the low pressure turbine 19th drive the high pressure compressor 16 or the intermediate pressure compressor 15th each via a suitable connecting shaft 20th , 21 at. The low pressure wave 20th who have favourited the low pressure turbine 19th with the intermediate pressure compressor 15th couples, also drives the wind instruments 4th via the planetary gear 25th at.

The low pressure wave 20th is here with a sun gear 28 of the planetary gear 25th connected, whereas the winds 4th in the area of a wind wave 26th with a rotating planet carrier 27 of the planetary gear 25th is in operative connection. The planet carrier 27 acts via bearing devices (not shown in more detail) with several planet gears distributed around the circumference 29 of the planetary gear 25th together. In the embodiment of the planetary gear shown 25th is a ring gear 31 of the planetary gear 25th fixed to the housing on a housing device 32 arranged. In alternative designs of the planetary gear, the planet carrier or the sun gear can also be fixed to the housing.

With the coupling of the fan shaft shown 26th and the low pressure wave 20th the low pressure turbine 19th to the planetary gear 25th becomes one over the low pressure wave 20th on the planetary gear 25th applied drive torque of the stationary transmission of the planetary gear 25th raised accordingly and the fan shaft 26th fed while the speed of rotation of the low pressure shaft 20th by the factor of the stationary ratio of the planetary gear 25th is greater than the speed of the fan shaft 26th . When the horn 4th from the low pressure turbine 19th is driven, the speed of the low pressure shaft becomes 20th the translation of the planetary gear 25th in the area of the planetary gear 25th accordingly reduced and the wind wave 26th as well as the brass 4th with this reduced speed and with one compared to that on the low-pressure shaft 20th applied torque driven increased torque.

However, there is also the possibility that the gas turbine engine 1 is designed without a planetary gear as described above.

2 shows a rotor 34 in a greatly simplified side view. The rotor 34 can be part of the intermediate pressure compressor 15th , the high pressure compressor 16 , the high pressure turbine 18th or the low pressure turbine 19th be. The rotor 34 is designed in several parts and includes a rotor disk 35 as well as several rotor blades 36 . The rotor blades 36 stand with the rotor disk 35 in the described in more detail below in operative connection and extend with respect to the rotor disk 35 in the radial direction R. outward. Furthermore are the rotor blades 36 in the circumferential direction U over the circumference of the rotor disk 35 arranged distributed. The rotor 34 can be made up of several separable or inseparable rotor disks 35 exist. Here are the rotor blades 36 arranged in several rows one behind the other on the rotor.

3 Figure 10 shows a partial cross-sectional view of the rotor 34 . In the 3 illustrated rotor blade 36 comprises a dovetail-shaped blade root 37 in a dovetail groove 38 the rotor disk 35 is arranged.

In addition, there is the rotor blade 36 with one platform 39 executed with the rotor blade 36 radially from the outside on an outside 40 the rotor disk 35 rests. On the tip of the blade 37 facing away from the platform 39 has the rotor blade 36 a shovel blade 41 on, the free end of which is hereinafter referred to as the rotor blade tip 42 referred to as. 3 shows the nominal arrangement of the rotor blade 36 in relation to the rotor disk 35 .

One width B37 of the blade root 37 as well as a width B38 the groove 38 changes in the radial direction R. of the rotor 34 . Here are the width B37 of the blade root 37 and the width B38 the groove 38 coordinated. The coordination is such that a contact surface facing radially or primarily radially outward F37 of the blade root 37 and a radially inwardly facing contact surface F38 the groove 38 in the operation of the gas turbine engine 1 rest firmly against one another or are pressed against one another, since then on the rotor blade 36 a corresponding centrifugal force attacks.

The width B37 of the blade root 37 and the width B38 the groove 38 represent a multitude of geometrical characteristics of the contact surfaces F37 and F38 . This can also be designed as a contact line or contact point.

The contact areas F37 and F38 vary due to manufacturing, which means the radial position of the rotor blades 36 to the axis of rotation 43 also vary.

The area in which the blade root 37 and the groove 38 to be in contact with each other is in 4th under the reference number KB shown in more detail and is referred to below as the contact area. A height of the contact area KB extends in the radial direction R. and is in 4th axial direction ideally standing perpendicular to the radial direction R. shown. Depending on the radial distance between the system and the blade root 37 and the groove 38 within the contact area KB the radial distance between an axis of rotation also varies 43 of the rotor 34 and the position of the rotor blade 36 and thus the rotor blade tip 42 .

This means that a production-related greater width B38 the groove 38 leads to the plant of the blade root 37 at the contact surface F38 the groove 38 moves radially outwards and thus also the distance between the rotor blades 36 and thus the rotor blade tip 42 from the axis of rotation 43 of the rotor 34 increases. Furthermore, there is also a manufacturing-related reduction in the width B37 of the blade root 37 on the nominal width of the blade root 37 result in the rotor blade 36 and thus the rotor blade tip 42 in the radial direction R. migrates outwards.

In contrast, each cause an increase in width B37 of the blade root 37 and a reduction in width B38 the groove 38 compared to the nominal widths of the blade root 37 and the groove 38 that the distance between the rotor blade tip 42 and the rotor axis 43 decreases and with it the rotor blade tip 42 migrates radially inward. The radial area in which the rotor blade tip 42 depending on the widths B37 and B38 can be arranged is in 4th between the dashed line 42u and the solid line 42o specified.

5 again shows one 3 corresponding representation of the rotor 34 . The nominal blade arrangement is in 5 through the solid outlines of the rotor blade 36 and the rotor disk 35 reproduced. The dashed lines give the outlines of the rotor blade 36 and the rotor disk 35 within the tolerance fields again, which are characterized by a deviation from an ideal outer circular shape or a roundness deviation of the rotor disk 35 or the groove 38 and an eccentricity of the rotor 34 result. Here, under the eccentricity of the rotor 34 an offset of the axis of rotation 43 with respect to a center point of the rotor disk 35 Understood. Both the roundness deviation of the rotor disk 35 as well as the eccentricity of the rotor 34 in turn lead to the rotor blade tip 42 the rotor blade 36 more or less far from the axis of rotation 43 is spaced.

In addition, there is also the possibility that a radial length of the airfoil 41 and a distance between the rotor blade tip 42 and the contact area F37 of the blade root 37 vary depending on the manufacturing process, which in turn means the distance between the rotor blade tip 42 from the axis of rotation 43 varies. In addition, the geometric dimensions of the rotor blade 36 also their mass.

Around the rotor 34 To be able to produce with the smallest possible unbalance, the rotor blades 36 that are in the in 2 illustrated way in the groove 38 are to be assembled, first weighed and their real dimensions determined. In addition, there is an imbalance in the rotor disk 35 determined by measurement. This is followed by defined assembly positions for the rotor blades 36 in the circumferential direction on the rotor disk 35 set. The assembly positions of the rotor blades are then determined 36 on the rotor disc 35 depending on the previously measured mass of the rotor blades 36 to the effect that through the distribution of the rotor blades 36 in the circumferential direction U and thus the different masses of the rotor blades 36 the unbalance of the rotor disk previously determined by measurement 35 is minimized.

Following this, the rotor disk 35 together with the rotor blades mounted on it 36 set in rotation. This causes the radial play in the groove 38 the rotor disk 35 arranged rotor blades 36 of the then acting centrifugal force radially outwards against the contact surfaces F38 the groove 38 be pressed. In this operating state of the rotor 34 are via a measuring unit 44 the radial clearances between the rotor blade tips 42 of the rotor blades 36 and the axis of rotation 43 of the rotor 34 determined by measurement.

The rotor blade tips 42 of the rotor blades 36 are due to manufacturing tolerances of the rotor blades 36 and the rotor disk 35 different distances from the rotor disk 43 spaced. The rotor 34 must, however, be designed with a defined roundness for a desired functionality of the gas turbine engine. Because of this, the rotor becomes 34 In a further manufacturing step, ground round or with another manufacturing process into a round one with the axis of rotation 43 brought concentric shape. This is done on the basis of the radial distances between the rotor blade tips 42 of the individual rotor blades 36 from the axis of rotation 43 a corresponding diameter of the circle around the axis of rotation 43 calculated on the basis of all rotor blade tips at the end of the cylindrical grinding process 42 should lie so that the rotor 34 the required roundness and the required diameter or the required shape of the rotor blade tips 42 having.

The material removal in the area of the rotor blade tips 42 of the rotor blades 36 that takes place during the cylindrical grinding process has a change in the mass of the rotor blades 36 result. The mass changes of the rotor blades 36 may have an influence on the imbalance of the rotor 34 . For this reason, there is a difference between the radial distances between the rotor blade tips before cylindrical grinding 42 Calculated before the cylindrical grinding process and after the cylindrical grinding process. Depending on the difference that is found for each rotor blade 36 results, and depending on known CAD data or design data of the rotor blades 36 are the change in mass of the rotor blades 36 determined that result from the cylindrical grinding process.

The changes in mass of the rotor blades determined in this way 36 are used to determine whether any cylindrical grinding of the mounted rotor that has to be carried out 34 an imbalance in the rotor 34 impaired.

Will affect the imbalance of the rotor 34 determined by the cylindrical grinding, it is checked whether there is a change in the assembly positions of already assembled rotor blades 36 leads to the fact that the cylindrical grinding process to be carried out of the rotor 34 whose imbalance does not worsen. In addition or as an alternative to this, there is also the possibility of using at least one of the already mounted rotor blades 36 by another rotor blade 36 to replace, with which the subsequent cylindrical grinding process a desired imbalance of the rotor 34 results.

In other words, after the installation or assembly of the rotor blades 36 a measurement of the protrusion of the rotor blades 36 in the radial direction opposite the outside 40 the rotor disk 35 carried out. On the basis of the measured protrusion of the rotor blade tips 42 of the rotor blades 36 a calculation of the mass distribution is carried out on the basis of existing CAD construction data. On this basis it can then be decided whether the rotor 34 in the currently assembled state, it is round-ground, or whether the overall data measured and determined with the aid of the CAD data indicate a changed arrangement of the blades on the rotor disk 35 is carried out before the final cylindrical grinding takes place.

The aim is to have blades on the rotor disk 35 which ideally does not require cylindrical grinding or which at least in the circumferential direction requires evenly distributed grinding of the rotor blade 36 enables. Then the cylindrical grinding process does not worsen the unbalance of the rotor 34 .

As an alternative to this, there is also the possibility of using the real geometric dimensions of the rotor blades 36 and the rotor disk 35 , as a function of which the radial distances between the rotor blade tips 42 and the axis of rotation 43 of the rotor 34 stand, to be determined by measurement. This means that all dimensions of the rotor blades 36 and the rotor disk 35 be determined by measurement. This applies in particular to the dimensions that the contact surfaces F37 and F38 between rotor blades 36 and rotor disk 35 and their position in relation to the axis of rotation 43 or determine the center of gravity for the rotor blade. Depending on the geometrical dimensions of the rotor blades determined by measurement 36 and the rotor disk 35 there is then the option of the rotor blades 36 taking into account their masses over the circumference U on the rotor disc 35 to assemble. This is the circumferential arrangement of the individual rotor blades 36 on the rotor disc 35 even before the rotor blades are assembled 36 on the rotor disc 35 possible. The arrangement can be made with the aid of the measurement data both as a function of the masses of the rotor blades 36 as well as depending on the then also before the assembly of the rotor blades 36 theoretically determinable mass changes of the rotor blades 36 caused by any necessary cylindrical grinding of the rotor 34 caused, be determined.

The last-described procedure, in which the arrangement of the rotor blades 36 is optimized and determined essentially on a computational basis, manufacturing expenditure can be reduced, since rotor blades are already installed 36 do not have to be dismantled again for an optimized arrangement and then reassembled if it is recognized that a currently theoretically determined arrangement of the rotor blades 36 has an unbalance that is too great after cylindrical grinding. In contrast to this, the procedure described last causes the rotor to operate in accordance with the procedure 34 is first assembled and then it is checked whether theoretically determined changes in mass of the rotor blades that have already been assembled are caused by cylindrical grinding 36 an imbalance in the rotor 34 affect, a higher measurement effort.

List of reference symbols

1

Jet engine

3

Air inlet

4th

Wind players

5

Engine nacelle

7th

Outlet nozzle

12th

Axis of rotation

15th

Intermediate pressure compressor

16

High pressure compressor

17th

Incinerator

18th

High pressure turbine

19th

Low pressure turbine

20th

Low pressure wave

21

High pressure wave

22nd

Bypass duct

25th

Planetary gear

26th

Wind wave

27

Planet carrier

28

Sun gear

29

Planetary gear

31

Ring gear

32

Housing equipment

34

rotor

35

Rotor disk

36

Rotor blade

37

Blade root

38

Groove

39

platform

40

Outside

41

Shovel blade

42

Rotor blade tip

42u

line

42o

line

43

Axis of rotation

44

Measuring unit

B37

Width of the blade root

B38

Width of the groove

F37

Contact surface of the blade root

F38

Contact surface of the groove

KB

Contact area

R.

radial direction

U

Circumferential direction

A.

axial direction

QUOTES INCLUDED IN THE DESCRIPTION

This list of the documents listed by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent literature cited

• US 7497662 B2 [0006]
• US 2019/0332743 A1 [0006]

Claims (16)

Method for producing a multi-part rotor (34) of a gas turbine engine (1) with at least one rotor disk (35) and with several rotor blades (36), which are in operative connection with the rotor disk (35), over the circumference (U) of the rotor disk (35) ) are arranged distributed and extend radially outward with respect to the rotor disk (35), wherein an arrangement of the rotor blades (36) on the rotor disk (35) is determined, which is characterized by an imbalance of the rotor (34) smaller than a limit value, wherein radial distances between an axis of rotation (43) of the rotor and rotor blade tips (42) of the rotor blades (36) are measured, wherein differences between the measured radial distances between the axis of rotation (43) and the rotor blade tips (42) and radial distances between the axis of rotation (43) and the rotor blade tips (42) when the rotor blade tips (42) in the circumferential direction (U) on a circle the axis of rotation (43) of the rotor (34) are determined, wherein a change in mass of each rotor blade (36) is determined as a function of the respectively determined difference between the radial distances, and wherein the unbalance of the rotor (34) is determined as a function of the determined change in mass of the rotor blades (36). Method for manufacturing a rotor (34) with at least one rotor disk (35) and with several rotor blades (36), the rotor blades (36) being distributed over the circumference (U) of the rotor disk (35) and in the area of the blade roots each ( 37) in relation to the rotor disk (35) have primarily radially outwardly facing contact surfaces (F37) with which the rotor blades (36) in the radial direction (R) of the rotor disk (35) each have predominantly radially inwardly directed contact surfaces of (F38 ) The rotor disk (35) are in operative connection and are held in the rotor disk (35) in the radial direction (R), wherein an arrangement of the rotor blades (36) on the rotor disk (35) is determined, which is characterized by an imbalance of the rotor (34) smaller than a limit value, wherein radial distances between an axis of rotation (43) of the rotor (34) and rotor blade tips (42) of the rotor blades (36) are theoretically determined as a function of metrologically determined geometric data of the rotor disk (35) and the rotor blades (36), wherein differences between the radial distances between the axis of rotation (43) and the rotor blade tips (42) and further radial distances between the axis of rotation (43) and the rotor blade tips (42) when the rotor blade tips (42) in the circumferential direction on a circle around the axis of rotation ( 43) of the rotor (34) are theoretically determined, a change in mass of each rotor blade (36) being determined as a function of the respectively determined difference between the radial distances, and the imbalance of the rotor (34) depending on the theoretically determined change in mass of the Rotor blades (36) is determined. Procedure according to Claim 1 or 2 , characterized in that the assembly positions of the rotor blades (36) on the rotor disk (35) are theoretically determined as a function of a measured unbalance of the rotor disk (35) and the masses of the rotor blades (36) recorded by measurement. Method according to one of the Claims 1 until 3 , characterized in that the assembly positions of rotor blades (36) are changed and / or at least one mounted rotor blade (36) is exchanged for a further rotor blade when the determined unbalance of the rotor (34), which is determined as a function of the theoretical change in mass, is greater than or equal to the limit value, the value of the imbalance determined being changed by changing the assembly positions and / or by replacing at least one rotor blade (36) so that the imbalance determined is smaller than the limit value. Method according to one of the Claims 2 until 4th , characterized in that radial distances between the contact surfaces (F38) of the rotor disk (35) and the axis of rotation (43) of the rotor (34) are determined by measurement. Method according to one of the Claims 2 until 5 , characterized in that radial distances between the contact surfaces (F37) of the rotor blades (36) and their rotor blade tips (42) in the longitudinal direction of the rotor blades (36) are determined by measurement. Method according to one of the Claims 1 until 6th , characterized in that the changes in mass of the rotor blades (36) are determined as a function of CAD data for the rotor blades (36). Method according to one of the Claims 1 until 7th , characterized in that the rotor blades (36) are mounted in the theoretically determined assembly positions on the rotor disk (35) and driven in rotation together with the rotor disk (35) during the cylindrical grinding of the rotor (35) and grinding in the area of the rotor blade tips (42) or processed using another manufacturing process. Method according to one of the Claims 1 until 8th , characterized in that the rotor (34) by radial grinding of the rotor blade tips (42) round-ground or by means of another manufacturing process round-machined until the rotor blade tips (42) lie on the circular line of the determined circle, when the unbalance of the rotor (34), which depends on the determined mass changes that occur during the cylindrical grinding of the rotor (34) occurs in the area of the rotor blade tips, be determined is smaller than a limit value. Method according to one of the Claims 1 until 9 , characterized in that the rotor (35) is a rotor (35) consisting of at least one rotor stage or several separable or inseparably connected rotor stages. Method according to one of the Claims 1 until 10 , characterized in that it is the rotor of a gas turbine engine or another engine for propulsion or energy generation. Method according to one of the Claims 1 until 11th , characterized in that the rotor blades are completely machined before assembly as a single blade to the geometry determined by the control device, in particular the rotor blade tips (42), for example, and thus finishing machining of the rotor blade tips (42) after assembly can be dispensed with. Control device for the production of a multi-part rotor (34) of a gas turbine engine (1) with a rotor disk (35) and with several rotor blades (36), which are in operative connection with the rotor disk (35), are arranged distributed over the circumference of the rotor disk (35) and extend in the radial direction (R) outward with respect to the rotor disk (35), wherein the control device is designed such that an arrangement of the rotor blades (36) on the rotor disk (35) is determined, which is characterized by an imbalance of the rotor (34) smaller than a limit value, radial distances between an axis of rotation (43) of the rotor (34) and rotor blade tips (42) of the rotor blades (36) are measured, differences between the measured radial distances between the axis of rotation (43) and the rotor blade tips (42) and further radial distances between the Axis of rotation (43) and the rotor blade tips (42) are determined when the rotor blade tips (42) lie in the circumferential direction (U) on a circle around the axis of rotation (43) of the rotor (34), a change in mass of each rotor blade (36) as a function the respectively determined difference between the radial distances is determined, and the imbalance of the rotor (34) is determined as a function of the determined change in mass of the rotor blades (36). Control device for manufacturing a rotor (34) of a gas turbine engine (1) with a rotor disk (35) and with several rotor blades (36), the rotor blades (36) being distributed over the circumference (U) of the rotor disk (35) and in the area of blade roots (37) each have contact surfaces (F37) facing radially outward in relation to the rotor disk (35), with which the rotor blades (36) each have contact surfaces (F37) directed radially inward in the radial direction (R) of the rotor disk (35). F38) of the rotor disk (35) are in operative connection and are held in the rotor disk (35) in the radial direction (R), the control device being designed such that an arrangement of the rotor blades (36) on the rotor disk (35) is determined, which is characterized by an imbalance of the rotor (34) smaller than a limit value, radial distances between an axis of rotation (43) of the rotor (34) and rotor blade tips (42) of the rotor blades (36) are determined as a function of metrologically determined geometric data of the rotor disk (35) and the rotor blades (36), Differences between the radial distances between the axis of rotation (43) and the rotor blade tips (42) and further radial distances between the axis of rotation (43) and the rotor blade tips (42) when the rotor blade tips (42) in the circumferential direction (U) on a circle around the The axis of rotation (43) of the rotor (34) are theoretically determined, a change in mass of each rotor blade (36) is determined as a function of the respectively determined difference between the radial distances, and the imbalance of the rotor (34) is determined as a function of the theoretically determined changes in mass of the rotor blades (36). Control unit after Claim 13 or 14th , characterized in that the same the method according to one of the Claims 1 until 12th Executes on the control side. Computer program product with program code means which are stored on a computer-readable data carrier in order to carry out all the steps of a method according to one of the Claims 1 until 12th perform when the computer program product is on a computer or on a corresponding computing unit, in particular a control device according to one of the Claims 13 until 15th is performed.

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