Turbine rotor test system

Abstract

The present invention provides a turbine rotor test system, which can ensure the assembly of the rotor and the continuity of the sealing flow path in the rear slip ring device scheme. The turbine rotor test system includes a test sensing part, a slip ring device, a data acquisition device, a turbine rear shaft, a transfer structure and a sealing structure. The test sensing part is connected to the surface of the turbine rotor. The slip ring device transmits the measurement data of the test sensing part to the data acquisition device. The inner ring surface of the rear end of the turbine rear shaft is provided with an internal thread. The transfer structure includes a drive shaft and a coupling. The coupling is connected to the rotor part of the slip ring device. One end of the drive shaft is connected to the coupling, and the other end has an external thread, which is connected to the internal thread of the rear end of the turbine rear shaft. The drive shaft is provided with at least one channel connecting the outer peripheral side of the drive shaft with the inner cavity of the turbine rear shaft, which is used to allow the sealing gas in the inner cavity to pass through the drive shaft. The stator part of the slip ring device is detachably connected to the casing, and a sealing structure is provided between the outer peripheral side and the casing.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to a turbine rotor testing system. Background Art

[0002] Accurately measuring the surface temperature, strain and other data of key structural components of aircraft engines is the key to improving the working efficiency and reliability of aircraft engines. During the test of aircraft engines, the test sensor used to measure the surface temperature, strain and other data of the aircraft engine rotor needs to be installed on the rotor surface. As the rotor rotates at high speed, the measurement data needs to be transmitted from the rotating component to the data acquisition device in the ground equipment for processing, analysis and storage.

[0003] At present, the industry usually adopts slip ring devices or telemetry equipment to solve the problem of transmitting data from rotating parts to fixed data acquisition devices. Among them, slip ring devices are widely used due to their low cost and mature technology. During the engine test process, the rotor part and stator part of the slip ring device are connected to the rotor and casing of the engine respectively. The measurement data obtained by the test sensing part set on the surface of the rotor of the engine is transmitted to the rotor part of the slip ring device through the test lead, and then transmitted to the stator part through the rotor part, and finally transmitted to the data acquisition device in the ground equipment through the data lead of the stator part, such as the data acquisition system of the test bench.

[0004] Reference Figure 1 and Figure 2 The core engine test piece 100 of the aircraft engine usually includes an intermediate casing 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, an interstage casing 7 and a tail nozzle (not shown). The high-pressure rotor is composed of a high-pressure compressor rotor 9 and a high-pressure turbine rotor 10. In order to achieve reliable connection and joint operation between the high-pressure compressor rotor 9 and the high-pressure turbine rotor 10, the high-pressure compressor rotor shaft 11 and the high-pressure turbine shaft 12 are usually connected by bolts with flange openings. During assembly, the high-pressure rotor assembly tool 13 is extended from the inner cavity 14 of the high-pressure turbine shaft 12 into the connection position of the high-pressure rotor to tighten the bolts. The high-pressure turbine shaft 12 and the interstage casing 7 are supported by the high-pressure turbine rear bearing 15. The sealing gas of the high-pressure turbine rear bearing 15 is drawn out by the compressor, passes through the inner cavity 14 of the high-pressure turbine shaft 12 and the structural parts of the high-pressure turbine rear bearing cavity, flows from the opening on the structural parts of the interstage casing 7 to the tail nozzle, and finally is discharged from the exhaust port of the tail nozzle.

[0005] When measuring the rotor surface temperature, strain and other data of the high-pressure turbine 6, there are two types of slip ring device settings: front and rear. Both solutions have certain problems in use:

[0006] (1) When the front slip ring device is adopted, the slip ring device is arranged at the front end of the engine, that is, the rotor part of the slip ring device is connected to the front end of the high-pressure compressor rotor shaft 11. In order to meet the measurement lead requirements of the rotating parts at the rear end, it is usually necessary to add a longer lead tube in the engine to lead the lead from the rear end to the front end, which increases the complexity of the rotating parts and affects the stability and accuracy of data transmission. In addition, the slender lead tube is prone to deformation, cracks, and block falling when working for a long time in a high-speed and high-temperature area, which will seriously affect the safety of the engine operation. In addition, when it is necessary to measure the surface temperature, strain and other data of the high-pressure compressor rotor and the high-pressure turbine rotor at the same time, the number of channels of the front slip ring device will not be able to meet the needs of data transmission.

[0007] (2) When the rear-mounted slip ring device is adopted, the slip ring device is arranged at the rear end of the engine, that is, the rotor part of the slip ring device is connected to the rear end of the high-pressure turbine shaft 12. The high-pressure turbine shaft 12 is usually composed of multiple sections, wherein the last section is the high-pressure turbine rear shaft 17. In order to connect the rotor part of the slip ring device, the high-pressure turbine rear shaft 17 needs to be modified, and a connecting structure is added to the inner ring surface of the high-pressure turbine rear shaft 17, resulting in a corresponding reduction in the minimum inner diameter of the high-pressure turbine shaft 12; the size of the high-pressure turbine shaft 12 usually decreases with the reduction of the required thrust, while the size of the high-pressure rotor assembly tool 13 is difficult to further compress. Therefore, for a small-sized high-pressure turbine shaft 12, the adoption of the rear-mounted slip ring device will result in the minimum inner diameter of the high-pressure turbine shaft 12 being difficult to meet the assembly requirements of the high-pressure rotor, resulting in the inability to assemble the high-pressure rotor, thereby affecting the development cost and cycle of the engine; in addition, placing the slip ring device at the rear end of the engine will also cause the sealing flow path of the high-pressure turbine rear bearing cavity to be cut off by the slip ring device. Summary of the invention

[0008] The object of the present invention is to provide a turbine rotor testing system which can ensure the assembly of the rotor and the continuity of the sealed flow path in a post-slip ring device solution.

[0009] A turbine rotor testing system for achieving the above-mentioned purpose comprises a test sensing part, a slip ring device, a data acquisition device, a turbine rear shaft, a transfer structure and a sealing structure, wherein the test sensing part is connected to the surface of the turbine rotor, the slip ring device is used to transmit the measurement data of the test sensing part to the data acquisition device, the inner ring surface of the rear end of the turbine rear shaft is provided with an internal thread, the transfer structure comprises a drive shaft and a coupling, the coupling is connected to the rotor part of the slip ring device, one end of the drive shaft is connected to the coupling, and the other end is connected to the rear end of the turbine rear shaft, the other end has an external thread, the external thread is connected to the internal thread, the drive shaft is provided with at least one channel connecting the outer peripheral side of the drive shaft with the inner cavity of the turbine rear shaft, for allowing the sealing gas in the inner cavity to pass through the drive shaft, the stator part of the slip ring device is detachably connected to the casing, and the sealing structure is provided between the outer peripheral side and the casing.

[0010] In one or more embodiments of the turbine rotor testing system, the coupling includes a bellows structure.

[0011] In one or more embodiments of the turbine rotor testing system, the turbine rotor testing system further comprises a sealing baffle detachably connected to the casing, and the sealing structure is arranged between the inner peripheral side of the sealing baffle and the outer peripheral side of the drive shaft.

[0012] In one or more embodiments of the turbine rotor testing system, the sealing structure is a comb teeth sealing structure.

[0013] In one or more embodiments of the turbine rotor testing system, a stopping structure is provided at the rear end of the turbine rear shaft or the other end of the drive shaft for stopping and positioning the other end of the drive shaft.

[0014] In one or more embodiments of the turbine rotor testing system, the turbine rotor testing system further includes a locking device for locking and preventing loosening of the threaded connection between the external thread and the internal thread.

[0015] In one or more embodiments of the turbine rotor testing system, the locking device includes an elastic locking washer and a groove arranged on the outer surface of the other end of the drive shaft, the radial inner side of the elastic locking washer is inserted into the groove, and the radial outer side of the elastic locking washer is bent in the axial direction and clamped between the outer surface and the inner annular surface.

[0016] In one or more embodiments of the turbine rotor testing system, the other end of the drive shaft is provided with a torque groove for clamping a tightening tool.

[0017] In one or more embodiments of the turbine rotor testing system, the test sensing portion is used to measure the temperature and / or strain data of the turbine rotor.

[0018] In one or more embodiments of the turbine rotor testing system, the turbine rotor is a high-pressure turbine rotor, and the stator portion is detachably connected to an interstage casing.

[0019] The turbine rotor test system adopts the scheme of the rear slip ring device to measure the data of the turbine rotor. Compared with the scheme of the front slip ring device, the length of the test lead is shorter and not easy to be damaged, which can improve the stability and accuracy of data transmission and the service life of the test system. A transfer structure is used to connect the high-pressure turbine rear shaft and the rotor part of the slip ring device. The drive shaft of the transfer structure and the high-pressure turbine rear shaft are connected by internal and external threads. The connection structure is simple, safe and reliable, and easy to operate. It has little effect on the structure and inner diameter of the high-pressure turbine rear shaft, and can effectively solve the assembly problem between the compressor rotor and the turbine rotor caused by the scheme of the rear slip ring device in the prior art. By setting a channel connected to the inner cavity of the high-pressure turbine rear shaft on the drive shaft to ensure the continuity of the sealing flow path, and setting a sealing structure between the outer peripheral side of the drive shaft and the interstage casing to prevent the leakage of the sealing gas, it can ensure that the sealing gas is sealed to the high-pressure turbine rear bearing cavity. The turbine rotor test system has a simple structure and is easy to replace. It does not require too many replacement parts. When the turbine rotor data does not need to be measured, it is only necessary to remove the slip ring device and replace the turbine rear shaft and the sealing structure. When the safety of the turbine rear shaft can meet the use requirements, the turbine rear shaft can also be replaced. The turbine rotor test system can be used not only to measure the data of high-pressure turbine rotors, but also to measure the data of low-pressure turbine rotors. It is not only suitable for measuring the turbine rotor data of aircraft engines, but also suitable for measuring the turbine rotor data of wind turbines, gas turbines, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0021] Figure 1 It is a structural diagram of an aircraft engine.

[0022] Figure 2 It is a schematic diagram of the assembly method of the high-pressure rotor.

[0023] Figure 3 It is a structural diagram of the turbine rotor test system.

[0024] Figure 4 It corresponds to Figure 3 Partial schematic diagram at point A in the middle. DETAILED DESCRIPTION

[0025] The following discloses a variety of different implementation methods or embodiments of the subject technical solution. To simplify the disclosure, specific examples of each element and arrangement are described below. Of course, these are only examples and are not intended to limit the scope of protection of the present invention. It should be noted that the drawings are only examples, which are not drawn according to the conditions of equal proportions, and should not be used to limit the scope of protection actually required by the present invention. In addition, certain features, structures or characteristics in one or more embodiments of the present application may be appropriately combined.

[0026] The turbine rotor testing system 200 according to one embodiment is shown in FIG. Figure 3 and Figure 4 The turbine rotor test system 200 includes a test sensing part (not shown), a slip ring device 20, a data acquisition device (not shown), a turbine rear shaft, a transfer structure 40 and a sealing structure 50. The test sensing part is connected to the surface of the turbine rotor to measure the temperature and / or strain data and / or other data of the turbine rotor. The slip ring device 20 is used to transmit the measurement data of the test sensing part to the data acquisition device.

[0027] The slip ring device 20 includes a rotor part 21 and a stator part 22. The stator part 22 is detachably connected to the casing, and the rotor part 21 is connected to the rear end of the turbine rotor through the adapter structure 40. During the test of the engine, the measurement data obtained by the test sensing part arranged on the surface of the turbine rotor is transmitted to the rotor part 21 of the slip ring device 20 through the test lead 60, and then transmitted to the stator part 22 through the rotor part 21, and finally transmitted to the data acquisition device in the ground equipment through the data lead (not shown) of the stator part 22, such as the data acquisition system of the test bench.

[0028] In the description of the present invention, the directional words "front" and "rear" refer to the upstream direction and the downstream direction of the engine respectively.

[0029] exist Figure 3 and Figure 4In the embodiment shown, the turbine rotor is a high-pressure turbine rotor 10, the stator portion 22 of the slip ring device 20 is detachably connected to the interstage casing 7 through the stator retainer 30 and fasteners (not shown), and the rotor portion 21 is connected to the rear end of the high-pressure turbine shaft 12 through the adapter structure 40. The high-pressure turbine shaft 12 is composed of multiple sections, wherein the last section is the high-pressure turbine rear shaft 17. In this embodiment, the high-pressure turbine rear shaft 17 serves as the turbine rear shaft of the turbine rotor test system 200, and an internal thread 173 is provided on the inner annular surface 172 of the rear end 171 of the high-pressure turbine rear shaft 17. The adapter structure 40 includes a drive shaft 41 and a coupling 42, the coupling 42 is connected to the rotor portion 21 of the slip ring device 20, one end 411 of the drive shaft 41 is connected to the coupling 42, and the other end 412 is connected to the rear end 171 of the high-pressure turbine rear shaft 17, and the other end 412 has an external thread 413 for connecting to the internal thread 173 of the rear end 171.

[0030] Continue to refer to Figure 3 and Figure 4 The drive shaft 41 is provided with at least one channel 415, and the channel 415 connects the outer peripheral side 414 of the drive shaft 41 with the inner cavity 14 of the high-pressure turbine rear shaft 17, that is, the inner cavity 14 of the high-pressure turbine shaft 12. As a result, the sealing gas 18 of the high-pressure turbine rear bearing cavity 16 is drawn out by the compressor, passes through the inner cavity 14 of the high-pressure turbine shaft 12, the channel 415 of the drive shaft 41 and the structural parts of the high-pressure turbine rear bearing cavity 16, flows from the opening (not shown) on the structural parts of the interstage casing 7 to the tail nozzle, and finally is discharged from the exhaust port of the tail nozzle. In order to prevent the leakage of the sealing gas 18, a sealing structure 50 is provided between the outer peripheral side 414 of the drive shaft 41 and the interstage casing 7.

[0031] The turbine rotor test system 200 uses a rear slip ring device to measure the data of the turbine rotor. Compared with a front slip ring device, the test lead 60 is shorter and less prone to damage, which can improve the stability and accuracy of data transmission and increase the service life of the test system.

[0032] The turbine rotor testing system 200 uses a transfer structure 40 to connect the high-pressure turbine rear shaft 17 and the rotor part 21 of the slip ring device 20. The drive shaft 41 of the transfer structure 40 and the high-pressure turbine rear shaft 17 are connected by internal and external threads. The connection structure is simple, safe and reliable, and easy to operate. It has little effect on the structure and inner diameter of the high-pressure turbine rear shaft 17, and can effectively solve the assembly problem between the compressor rotor and the turbine rotor caused by the rear slip ring device solution in the prior art.

[0033] The turbine rotor testing system 200 ensures the continuity of the sealing flow path by setting a channel 415 on the drive shaft 41 that is connected to the inner cavity 14 of the high-pressure turbine rear shaft 17, and sets a sealing structure 50 between the outer peripheral side 414 of the drive shaft 41 and the interstage casing 7 to prevent leakage of the sealing gas 18, thereby ensuring the sealing of the high-pressure turbine rear bearing cavity 16 by the sealing gas 18.

[0034] The turbine rotor testing system 200 has a simple structure and is easy to replace without too many replacement parts. When it is not necessary to measure the data of the turbine rotor, such as when measuring other data of the engine, or when the engine is put into formal use at the end of the test phase, it is only necessary to remove the slip ring device 2 and replace the turbine rear shaft and the sealing structure 50. Alternatively, since the structure of the turbine rear shaft used by the turbine rotor testing system 200 is slightly different from that of the turbine rear shaft when the engine is officially used, when the safety of the turbine rear shaft can meet the use requirements, the turbine rear shaft may not be replaced.

[0035] The turbine rotor test system 200 can be used not only to measure the data of the high-pressure turbine rotor, but also to measure the data of the low-pressure turbine rotor. When measuring the data of the low-pressure turbine rotor, the rotor part 21 and the stator part 22 of the slip ring device 20 are respectively connected to the rear end of the low-pressure turbine rotor and the low-pressure turbine rear casing (not shown), and the positions of the turbine rear shaft and the sealing structure 50 are set accordingly. In addition, the turbine rotor test system 200 is not only suitable for measuring the turbine rotor data of aircraft engines, but also suitable for measuring the turbine rotor data of wind turbines, gas turbines, etc.

[0036] Continue to refer to Figure 3 and Figure 4 , the coupling 42 of the adapter structure 40 includes a bellows structure 421. Due to the machining deviation of the engine rotor during the machining process, the accumulated error will cause the rotor to be cold-state eccentric or axially displaced. In addition, the engine rotor has thermal deformation during operation and the transient radial or axial displacement of the rotor caused by the bearing clearance. The superposition of the two will have an adverse effect on the slip ring device 20 driven by the engine rotor, and in severe cases, the slip ring device 20 will be damaged and the dynamic stress monitoring will fail, thereby exposing the engine to a high-risk state. By arranging a coupling 42 including a bellows structure 421 between the drive shaft 41 and the rotor part 21 of the slip ring device 20 to achieve a flexible connection between the rotor part 21 of the slip ring device 20 and the engine rotor, the eccentricity or radial and axial displacement of the engine rotor in the cold state or transient state of operation can be compensated, the impact on the slip ring device 20 can be reduced, and the working safety and reliability of the slip ring device 20 can be improved.

[0037] Optionally, the turbine rotor testing system 200 further includes a sealing baffle 80 detachably connected to the casing, for example, Figure 3and Figure 4 In the illustrated embodiment, the sealing baffle 80 is detachably connected to the interstage casing 7 by fasteners, and the sealing structure 50 is disposed between the inner circumference 81 of the sealing baffle 80 and the outer circumference 414 of the drive shaft 41. Thus, the sealing structure 50 can be easily installed and removed.

[0038] The sealing structure 50 may adopt a comb-teeth sealing structure to facilitate processing and manufacturing, or the sealing structure 50 may also adopt other sealing structures commonly used in the art such as brush seals, spiral seals, etc., or a combination of multiple sealing structures.

[0039] Optionally, the rear end 171 of the high-pressure turbine rear shaft 17 also includes a stopping boss 174 to facilitate stopping and positioning the other end 412 of the drive shaft 41, or a boss or a block or other stopping structure may be provided at the other end 412 of the drive shaft 41, or the external thread 413 and the internal thread 173 may be connected by a tapered thread or a pipe thread to achieve stopping and positioning while tightening the thread.

[0040] Optionally, the turbine rotor test system 200 further includes a locking device 70 for locking the threaded connection between the external thread 413 and the internal thread 173 to prevent loosening. Figure 3 and Figure 4 In the illustrated embodiment, the locking device 70 includes an elastic locking washer 71 and a groove 417 arranged on the outer surface 416 of the other end 412 of the drive shaft 41, the radial inner side 711 of the elastic locking washer 71 is inserted into the groove 417, and the radial outer side 712 is bent in the axial direction and clamped between the outer surface 416 and the inner annular surface 172 of the high-pressure turbine rear shaft 17, or the external thread 413 and the internal thread 173 can adopt fine pitch threads to achieve anti-loosening, thereby, the locking and anti-loosening between the external thread 413 and the internal thread 173 can be achieved, and the impact on the structure of the turbine rear shaft can be reduced.

[0041] Optionally, the other end 412 of the driving shaft 41 is provided with a torque groove 418 for clamping a tightening tool (not shown) to achieve tightening and loosening of the driving shaft 41 according to torque.

[0042] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A turbine rotor testing system, comprising a test sensing part, a slip ring device and a data acquisition device, wherein the test sensing part is connected to the surface of the turbine rotor, and the slip ring device is used to transmit the measurement data of the test sensing part to the data acquisition device, characterized in that: It also includes a turbine rear shaft, a transfer structure and a sealing structure. The inner ring surface of the rear end of the turbine rear shaft is provided with an internal thread. The transfer structure includes a drive shaft and a coupling. The coupling is connected to the rotor part of the slip ring device. One end of the drive shaft is connected to the coupling, and the other end is connected to the rear end of the turbine rear shaft. The other end has an external thread, and the external thread is connected to the internal thread. The drive shaft is provided with at least one channel connecting the outer peripheral side of the drive shaft and the inner cavity of the turbine rear shaft, which is used to allow the sealing gas in the inner cavity to pass through the drive shaft. The stator part of the slip ring device is detachably connected to the casing, and the sealing structure is provided between the outer peripheral side and the casing.

2. The turbine rotor testing system according to claim 1, characterized in that: The coupling includes a bellows structure.

3. The turbine rotor testing system according to claim 1, characterized in that: The turbine rotor testing system further includes a sealing baffle detachably connected to the casing, and the sealing structure is arranged between the inner peripheral side of the sealing baffle and the outer peripheral side of the driving shaft.

4. The turbine rotor testing system according to claim 1, characterized in that: The sealing structure is a comb teeth sealing structure.

5. The turbine rotor testing system according to claim 1, characterized in that: The rear end of the turbine rear shaft or the other end of the drive shaft is provided with a stopping structure for stopping and positioning the other end of the drive shaft.

6. The turbine rotor testing system according to claim 1, characterized in that: The turbine rotor testing system also includes a locking device for locking and preventing the threaded connection between the external thread and the internal thread from loosening.

7. The turbine rotor testing system according to claim 6, characterized in that: The locking device includes an elastic locking washer and a groove arranged on the outer surface of the other end of the drive shaft, the radial inner side of the elastic locking washer is inserted into the groove, and the radial outer side of the elastic locking washer is bent in the axial direction and clamped between the outer surface and the inner annular surface.

8. The turbine rotor testing system according to claim 1, characterized in that: The other end of the driving shaft is provided with a torque groove for clamping a tightening tool.

9. The turbine rotor testing system according to any one of claims 1 to 8, characterized in that: The test sensing part is used to measure the temperature and / or strain data of the turbine rotor.

10. The turbine rotor testing system according to any one of claims 1 to 8, characterized in that: The turbine rotor is a high-pressure turbine rotor, and the stator part is detachably connected to the interstage casing.

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