CN121007058A - Turbine reducer installation structure and gas turbine - Google Patents
Turbine reducer installation structure and gas turbineInfo
- Publication number
- CN121007058A CN121007058A CN202410653317.9A CN202410653317A CN121007058A CN 121007058 A CN121007058 A CN 121007058A CN 202410653317 A CN202410653317 A CN 202410653317A CN 121007058 A CN121007058 A CN 121007058A
- Authority
- CN
- China
- Prior art keywords
- vortex
- support ring
- air duct
- mounting structure
- conical surface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
本发明提供一种减涡器安装结构及燃气轮机。减涡器安装结构设置在压气机的内腔，包括：用于安装减涡管的支撑环，以及用于固定支撑环的叶盘；减涡器安装结构还包括用于引导空气的空气导管；其中，叶盘包括沿周向延伸的锥面，支撑环包括与锥面彼此相对的锥壁、在空气导管的近端环绕空气导管的连接部；空气导管在内腔内固定设置；锥壁和锥面之间设置弹性密封件，连接部和空气导管的近端连接产生使锥壁向靠近锥面移动的预紧力，进而使得弹性密封件被加压提供密封作用。上述减涡器安装结构方便装配和分解减涡器。
This invention provides a vortex suppressor mounting structure and a gas turbine. The vortex suppressor mounting structure is disposed within the compressor cavity and includes: a support ring for mounting the vortex suppressor tube, and an impeller for fixing the support ring; the vortex suppressor mounting structure also includes an air duct for guiding air; wherein, the impeller includes a circumferentially extending conical surface, the support ring includes a conical wall opposite to the conical surface, and a connecting portion surrounding the air duct at its proximal end; the air duct is fixedly disposed within the cavity; an elastic seal is provided between the conical wall and the conical surface, and the connection between the connecting portion and the proximal end of the air duct generates a preload force that moves the conical wall closer to the conical surface, thereby pressurizing the elastic seal to provide a sealing effect. The above-described vortex suppressor mounting structure facilitates the assembly and disassembly of the vortex suppressor.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a vortex breaker mounting structure and a gas turbine.
Background
In turbomachinery of aeroengines or other compressors with pressure, interstage bleed air (part of the air that is extracted from the main flow after a stage of the compressor) is generally used to improve the surge margin of the compressor operation. Wherein in order to achieve bleed air at the root of the blade, a vortex breaker is required. The vortex reducer introduces low-temperature gas of the high-pressure gas compressor into a sealed bearing cavity and a turbine disc cavity of high-temperature components such as a combustion chamber, a high-pressure turbine and the like, and plays a role in bleed air cooling the high-temperature components. The vortex reducer has the main functions of guiding the gas flow, avoiding free vortex flow, weakening the development of vortex and reducing the gas loss.
The vortex reducer comprises a vortex reducing pipe and a supporting ring. The supporting ring is arranged at the bottom of the leaf disc through the locking nut and the clamping ring, the supporting ring is provided with a protruding part matched with the downward protruding structure of the leaf disc, the limiting effect on the leaf disc is achieved, and the vortex reducer can be firmly connected to the leaf disc through the locking nut and the clamping ring.
However, the structure of the support ring is complex, which is not beneficial to the assembly and the disassembly of the vortex reducer, and in order to adapt to the installation of the vortex reducer, the structure of the leaf disc is correspondingly complex due to the downward protruding structure, mainly the center of the disc is affected, the strength of the disc is reduced, and the disc is difficult to process due to the fact that the disc is generally finish-forged, irregular part shapes can bring about difficulty in processing technology, and the disc is difficult to process.
Disclosure of Invention
The invention aims to provide a vortex reducer mounting structure which is simple in structure and convenient to assemble and disassemble.
An aspect of the present invention provides a vortex breaker mounting structure provided in an inner cavity of a compressor, comprising a support ring for mounting a vortex breaker, and a vane for fixing the support ring, the vortex breaker mounting structure further comprising an air duct for guiding air, wherein the vane comprises a tapered surface extending along a circumferential direction, the support ring comprises a tapered wall opposite to the tapered surface, a connecting portion surrounding the air duct at a proximal end of the air duct, the air duct is fixedly provided in the inner cavity, an elastic sealing member is provided between the tapered wall and the tapered surface, and the connection of the connecting portion and the proximal end of the air duct generates a pre-tightening force for moving the tapered wall close to the tapered surface, so that the elastic sealing member is pressurized to provide a sealing effect.
In an embodiment, the proximal end of the air conduit and the connection portion of the support ring are threaded to create the preload force.
In one embodiment, the threaded connection is a sealed pipe threaded connection.
In one embodiment, the resilient seal comprises at least one sealing ring.
In an embodiment, the conical surface is located adjacent to a leaf disc of the vortex reducing pipe, the conical surface is formed on the inner periphery of one side of the leaf disc opposite to the vortex reducing pipe, and the pretightening force is a tensile force acting on the support ring.
In an embodiment, the elastic seal is mounted on a radially outer side of the conical surface of the conical wall facing the conical surface of the blisk.
Another aspect of the present invention provides a gas turbine comprising a compressor and a turbine connected by a shaft, the compressor being provided with a vortex breaker mounting structure as described in any one of the preceding claims, the support ring being provided with a vortex breaker tube, the distal end of the air conduit being secured to the inner cavity of the turbine. In one embodiment, the compressor is provided with a bleed hole, the vortex reduction pipe is arranged opposite to the bleed hole so as to lead at least part of air flow from the bleed hole to the vortex reduction pipe, and the air flow led in by the bleed hole flows to the inner cavity of the turbine through a runner on the outer periphery side of the air conduit so as to cool the turbine.
The support ring of the vortex breaker mounting structure is not fixed on the impeller by other parts, but is connected with the air guide pipe to fix the position of the support ring, so that the support ring and the impeller are convenient to assemble and disassemble, the elastic sealing element is pressurized by the pretightening force generated by the connection of the support ring and the air guide pipe to realize the sealing of the support ring and the impeller, compared with the rigid connection, the impeller without the annular groove and the protruding structure is beneficial to the production and the processing of the impeller, the economy is better, and the integral strength of the impeller can be improved.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description in conjunction with the accompanying drawings and embodiments, in which:
FIG. 1 is a schematic illustration of a vortex breaker mounting structure of a gas turbine engine prior to modification;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is a schematic view of a vortex breaker prior to modification;
FIG. 4 is a schematic view of an embodiment of a gas turbine according to the present invention;
FIG. 5 is a partial enlarged view at B in FIG. 4;
FIG. 6 is a schematic illustration of the flow path of the air flow introduced by bleed holes in accordance with an embodiment of the gas turbine of the present invention.
Detailed Description
The latter embodiment is modified on the basis of the vortex breaker mounting structure shown in fig. 1 to 3. As shown in fig. 1 to 3, the vortex breaker includes a vortex breaker tube 50 and a support ring 100. The support ring 100 is mounted to the bottom of the blisk 200 by a lock nut 20 and collar 30. The impeller 200 is provided with a ring groove 201 and a downwardly protruding structure 202, the support ring 100 is provided with a protruding portion 101 matched with the downwardly protruding structure 202, the limiting effect on the impeller 200 is achieved, the support ring 100 can be firmly connected to the impeller 200 through the lock nut 20 and the clamping ring 30, and the air guide pipe 300 is connected with the support ring 100 through the sealing rubber ring 40. The structure of the supporting ring 100 is mainly that the protruding part 101 matched with the downward protruding structure 202 is complex and is not beneficial to the assembly and the disassembly of the vortex reducer, and in order to adapt to the installation of the vortex reducer, the structure of the impeller 200 is correspondingly complex, the center of the impeller is influenced mainly by the ring groove 201 and the downward protruding structure 202, the strength of the impeller is reduced, and because the impeller is generally finish-forged, the irregular part shape can bring about difficulty in processing technology, so that the processing of the impeller is not easy.
Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation, not limitation, of the invention. Indeed, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. Accordingly, it is intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.
The term "radial" is a direction perpendicular to the central axis of the blisk 200 or parallel to the central axis of the blisk 200, the term "circumferential" is a direction about the central axis of the blisk 200 or parallel to the central axis of the blisk 200, and the terms "proximal" and "distal" are the positions of the air duct 300 relative to the blisk 200 adjacent the vortex reduction tube.
On the basis of the vortex breaker mounting structure shown in fig. 1 to 3, the improved vortex breaker mounting structure according to the embodiment described below reduces the number of parts required for mounting the vortex breaker, makes the structure of the support ring 100 and the blisk 200 simpler, facilitates assembly and disassembly, facilitates production and processing of the blisk 200, is better in economical efficiency, and improves the strength of the tray.
The term "Gas Turbine" is an internal combustion power machine that uses a continuously flowing Gas as a working medium to drive an impeller to rotate at a high speed, converting the energy of a fuel into useful work, and can be, but is not limited to, an engine for aviation or marine use or for power generation.
Fig. 4 shows a part of a compressor of a gas turbine, which is located approximately at the location of a high-pressure compressor, which compressor is connected to a turbine, not shown in the drawing, via a shaft 80. The compressor includes a plurality of stages, each stage including a rotor and a stator. Fig. 4 shows a two-stage rotor, which includes blades 71 and a disk 200, and a one-stage stator, which includes a casing 10 and vanes 72 mounted thereon. The blisks 200 are connected together by an axially extending shaft 80. The compressor has an outer wall surface of a flow passage provided by the casing 10 and an inner wall surface of a flow passage provided by the shaft 80. The shaft 80 is compressed around the interior cavity 90 of the compressor, and a majority of the blisk 200 is located within the interior cavity of the compressor. The inner chamber of the compressor is provided with a vortex breaker mounting structure for mounting a vortex breaker or vortex breaker tube 50. The vortex breaker mounting structure as shown in fig. 4 and 5 includes a support ring 100, a blisk 200 and an air duct 300. The support ring 100 is provided with a vortex reducing tube 50. The air conduit 300 comprises a proximal end 310 and a distal end (not shown), the proximal end 310 being connected to the support ring 100, the distal end being fixed to the inner cavity of a turbine not shown in the figures.
As shown in fig. 4, the compressor is provided with bleed holes 60, and the vortex reducing pipe 50 is disposed opposite the bleed holes 60. The flow path of the air flow introduced by the bleed holes 60 according to an embodiment of the present invention is shown in fig. 6, and the path shown by the arrow in fig. 6 is the flow path of the air flow. At least part of the air flow is led from the bleed holes 60 to the vortex tube 50, where it flows via the flow channel of the outer circumferential side 320 of the air duct 300 to the inner cavity of the turbine for cooling the turbine to ensure proper operation of the turbine.
As can be seen from fig. 6, if the connection between the support ring 100 and the blisk 200 and between the support ring 100 and the air duct 300 is not sufficiently tight, i.e. the sealing of the bleed air path is not sufficiently tight, and the air flow of the compressor has a high air pressure in the operating state, the high pressure air compressed by the compressor leaks from the bleed air holes 60 through the gaps between the support ring 100 and the blisk 200 and/or the gaps between the support ring 100 and the air duct 300, which affects the operating efficiency of the engine. And the compressor is from the shutdown state to the working state, the temperature change of the working environment of the vortex breaker is very large, and the sealing is also adversely affected.
The vortex breaker mounting structure as shown in fig. 4 and 5 includes a support ring 100, a blisk 200 and an air duct 300. The support ring 100 is used for installing the vortex reducing pipe 50, the impeller 200 is used for fixing the support ring 100, the air guide pipe 300 is used for guiding air, and the air guide pipe 300 is fixedly arranged in the inner cavity. Wherein the blisk 200 comprises a circumferentially extending conical surface 210, the support ring 100 comprising a conical wall 110 and a connecting portion 120. The tapered wall 110 and the tapered surface 210 are opposite to each other, the connection portion 120 is at the proximal end 310 of the air duct 300, and the connection portion 120 surrounds the air duct 300. An elastomeric seal 400 is provided between the tapered wall 110 and the tapered surface 210, and the connection 120 is connected to the proximal end 310 of the air conduit 300, creating a preload force that moves the tapered wall 110 toward the tapered surface 210, and the preload force acting on the connection 120 is generally rightward in FIG. 5. The preload in turn causes the elastomeric seal 400 to be pressurized providing a sealing action. Compared with the prior art vortex breaker mounting structure shown in fig. 1 to 3, an embodiment of the present invention can simplify the structure of the support ring 100, the air duct 300 and the blisk 200, facilitate assembly and disassembly, facilitate production and processing of the blisk 200, provide better economy, and improve the strength of the tray. Meanwhile, the elastic sealing member 400 facing the conical surface 210 on the conical wall 110 is deformed by the pre-tightening force, and the deformation is enough to counteract the influence of thermal deformation, so as to ensure tightness.
In some embodiments, as shown in fig. 4 and 5, the tapered surface 210 is located adjacent to the impeller 200 of the vortex reducing tube 50, the impeller 200 having a side 202 opposite the vortex reducing tube 50 and a side 203 opposite the vortex reducing tube 50, wherein the inner circumference of the side 203 of the impeller 200 opposite the vortex reducing tube 50 forms the tapered surface 210, the pre-load being a pulling force acting on the support ring 100. The support ring 100 is connected with the air guide 300 through the connecting part 120, the air guide 300 is relatively fixed at the inner cavity of the compressor, the support ring 100 needs to be controlled to move towards the distal direction of the air guide 300 to complete the connection of the connecting part 120 and the air guide 300, the conical wall 110 of the support ring 100 moves towards the conical surface 210, and the elastic connecting piece 400 is compressed due to the action of external force and is respectively tightly matched with the conical wall 110 and the conical surface 210 to realize the sealing effect.
Compared with the rigid connection between the impeller 200 and the support ring 100 in fig. 1 to 3, the sealing performance between the impeller 200 and the support ring 100 can be improved by using the elastic sealing member 400 deformed between the conical wall 110 and the conical surface 210, so that other structures are prevented from being damaged due to the leakage of the high-pressure gas compressed by the compressor.
In some embodiments, as shown in fig. 5, the proximal end 310 of the air conduit 300 is threaded with the connection 120 of the support ring 100 to create a preload force. The structure of the support ring 100 and the air duct 300 may be simpler, further facilitating the assembly between the support ring 100 and the air duct 300.
In some embodiments, the threaded connection between the air conduit 300 and the support ring 100 is a sealed tube threaded connection, the connection 120 of the support ring 100 being provided with internal threads and the peripheral side 320 of the proximal end 310 of the air conduit 300 being provided with external threads. The connecting part 120 rotates relative to the air conduit 300, so that the air conduit 300 is screwed into the connecting part 120, and a sufficient contact pressure is generated between the threads through the pretightening force generated by the matching of the internal thread and the external thread, so that the connecting part 120 and the air conduit 300 can be tightly contacted, and a better sealing effect is realized.
In some embodiments, as shown in fig. 5, the elastomeric seal 400 includes at least one sealing ring. The embodiment of the invention shown in fig. 5 includes three sealing rings spaced apart to further enhance the sealing. In some embodiments, the elastomeric seal 400 is mounted on the radially outer side 111 of the cone wall 110 facing the cone 210 of the blisk 200. In other embodiments, the elastomeric seal 400 is mounted to the tapered surface 210 of the blisk 200. "mounted" may mean that the elastic sealing member 400 is fixedly coupled to the radially outer side 111 of the tapered surface 210 or the tapered surface 210 of the disk 200, such as by being limited by a predetermined groove, or that the elastic sealing member 400 is detachably coupled to the radially outer side 111 of the tapered surface 210 or the tapered surface 210 of the disk 200. In still other embodiments, only between the radially outer side 111 of the conical wall 110 and the conical surface 210, no fixed connection is provided at the conical wall 110 and/or the conical surface 210.
It can be appreciated that the larger the contact area between the elastic sealing member 400 and the blisk 200, the better the sealing effect, and the number and size of the elastic sealing members 400 can be adjusted accordingly according to the actual application scenario and the characteristic parameters of the compressor.
In some embodiments, the support ring 100 is integrally formed, which may increase the overall strength of the support ring 100.
In some embodiments, as shown in fig. 5, the inclination angle of the tapered wall 110 of the support ring 100 is consistent with the inclination angle of the tapered surface 210 of the blisk 200, which may reduce the gap between the support ring 100 and the blisk 200, further improving the tightness between the support ring 100 and the blisk 200. It should be noted that, the inclination angles of the conical wall 110 and the conical surface 210 in the embodiment of the invention can be adjusted according to the actual application scenario, and the invention is not limited.
The assembly flow of the vortex breaker mounting structure of the embodiment of the invention is as follows:
The vortex reducing pipe is assembled with the support ring 100, then the air conduit 300 is screwed into the support ring 100, and the vortex reducing pipe and the support ring are assembled by utilizing the seal pipe threads, and a certain pretightening force is required to be applied to the threaded connection of the vortex reducing pipe and the support ring, so that the elastic sealing piece 400 can generate a certain deformation, and the sealing effect is realized.
While the invention has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the invention, as will occur to those skilled in the art, without departing from the spirit and scope of the invention. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present invention fall within the protection scope defined by the claims of the present invention.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410653317.9A CN121007058A (en) | 2024-05-23 | 2024-05-23 | Turbine reducer installation structure and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410653317.9A CN121007058A (en) | 2024-05-23 | 2024-05-23 | Turbine reducer installation structure and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN121007058A true CN121007058A (en) | 2025-11-25 |
Family
ID=97727897
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410653317.9A Pending CN121007058A (en) | 2024-05-23 | 2024-05-23 | Turbine reducer installation structure and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN121007058A (en) |
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2024
- 2024-05-23 CN CN202410653317.9A patent/CN121007058A/en active Pending
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