A multi-stage compressor rotor dynamic stress and temperature real-time synchronous measuring device

Abstract

The application belongs to the field of compressor measurement, and is a kind of multi-stage compressor rotor dynamic stress and temperature real-time synchronous measurement device, which comprises a transmission shaft, an axle core air lead wire tube, a high-speed slip ring and a compressor test lead wire, one end of the transmission shaft is connected with an engine high-pressure shaft, the other end is connected with the axle core air lead wire tube, the axle core air lead wire tube is coaxially arranged with the engine shaft and is located inside the transmission shaft, and the high-speed slip ring is connected with a core engine external data acquisition device. One end of the compressor test lead wire is connected with the high-speed slip ring, and then is inserted into the axle core air lead wire tube along the engine shaft line, the axle core air lead wire tube and the compressor rotor rotate synchronously, the strain gauge and the thermocouple transmit the vibration or temperature test signals of the high-pressure rotor to the high-speed slip ring after collecting the vibration or temperature test signals of the high-pressure rotor; and the contact type measurement and real-time synchronous measurement of the rotor wall surface parameters in the compressor are realized.

Description

Technical Field

[0001] This application belongs to the field of compressor measurement, and specifically relates to a real-time synchronous measurement device for dynamic stress and temperature of multi-stage compressor rotors. Background Technology

[0002] Real-time synchronous measurement of the wall parameters of the compressor rotor is a recognized challenge in the engine testing industry, with several technical bottlenecks, including limited testing and modification space, difficulty in installing measuring points and extracting test signals.

[0003] Currently, stress and temperature testing of compressors in China is generally conducted on the core engine. Due to space and assembly limitations of the compressor disks, only the first three stages of blades can be measured simultaneously. It is impossible to directly measure the actual strain at the measuring points using strain gauges. Stress measurements beyond the third stage can only be performed using non-contact indirect methods (fiber optic testing), and temperature can only be measured using pre-embedded crystals. The disadvantages of non-contact measurement include poor accessibility to complex measuring points such as the rotor blade roots and disk cavities, discontinuous sampling, indirect measurement, and the reliance of stress measurement accuracy on simulation precision.

[0004] Therefore, how to achieve contact measurement of rotor wall parameters inside the compressor is a problem that needs to be solved. Summary of the Invention

[0005] The purpose of this application is to provide a real-time synchronous measurement device for dynamic stress and temperature of multi-stage compressor rotors, so as to solve the problem that compressor rotor wall parameters are difficult to measure by contact in the prior art.

[0006] The technical solution of this application is: a real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor, comprising a drive shaft, a spool bleed air lead tube, a high-speed slip ring, and a compressor test lead. One end of the drive shaft is connected to the high-pressure shaft of the engine, and the other end is connected to the spool bleed air lead tube. The spool bleed air lead tube is coaxially arranged with the engine axis and located inside the drive shaft. The high-speed slip ring is coaxially arranged with the engine axis and located outside the spool bleed air lead tube. One end of the compressor test lead is connected to the high-speed slip ring, and then inserted into the spool bleed air lead tube along the engine axis. It then extends out from the spool bleed air lead tube and is connected to a strain gauge or thermocouple on the compressor rotor.

[0007] The axial air intake pipe includes an external air intake pipe, a central air intake pipe, and an air intake pipe support. The central air intake pipe is coaxially disposed inside the external air intake pipe, forming an air intake channel between the central air intake pipe and the external air intake pipe. There are multiple sets of air intake pipe supports, which are spaced apart along the length of the central air intake pipe within the air intake channel. A cooling ring cavity is formed between adjacent air intake pipe supports. Multiple sets of air intake through holes are spaced apart along the circumferential direction on the air intake pipe supports, allowing external cold air to enter the air intake ring cavity through the air intake through holes. Multiple sets of disc cooling ports communicating with the rotor disc and disc cavity are circumferentially disposed at positions corresponding to the air intake ring cavity on the external air intake pipe.

[0008] Preferably, the air intake holes and the wheel cooling port are staggered circumferentially, and the lead wire support has multiple sets of lead wire channels spaced apart circumferentially. The lead wire channels are connected to the outer side of the external air intake pipe and the inner side of the central lead wire pipe.

[0009] Preferably, the angle between the lead channel and the axis of the central lead tube is 45° to 60°.

[0010] Preferably, the front end of the axial air duct is provided with a front support seat, the inner side of the front support seat is connected to the axial air duct with a front positioning pin, the outer side of the front support seat is connected to the drive shaft, and a front sealing ring is provided between the front support seat and the drive shaft; the rear end of the axial air duct is provided with a rear support seat, the inner side of the rear support seat is connected to the axial air duct with a rear positioning pin, and a rear sealing ring is connected between the rear support seat and the drive shaft.

[0011] Preferably, the front end of the axial bleed air lead tube is fixed to the drive shaft by bolts, the rear support seat is a funnel-shaped structure, the open end of the rear support seat faces the rear of the compressor rotor, the end of the axial bleed air lead tube is a tapered structure and the end of the axial bleed air lead tube is tightly fitted to the inner wall of the rear support seat.

[0012] This application discloses a real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor, comprising a drive shaft, a bleed air lead tube, a high-speed slip ring, and compressor test leads. One end of the drive shaft is connected to the high-pressure shaft of the engine, and the other end is connected to the bleed air lead tube. The bleed air lead tube is coaxially arranged with the engine axis and located inside the drive shaft. The high-speed slip ring is connected to external data acquisition equipment of the core engine. One end of the compressor test lead is connected to the high-speed slip ring and then inserted into the bleed air lead tube along the engine axis. During operation, the bleed air lead tube rotates synchronously with the compressor rotor. After the strain gauge and thermocouple acquire the vibration or temperature test signals of the high-pressure rotor, the test signals pass through the compressor test lead, through the compressor rotor, into the bleed air lead tube, and then are transmitted to the high-speed slip ring. This achieves contact measurement and real-time synchronous measurement of the rotor wall parameters inside the compressor. Attached Figure Description

[0013] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0014] Figure 1 This is a schematic diagram of the connection structure between this application and the compressor;

[0015] Figure 2 This is a schematic diagram of the end structure of the axial air venting lead tube in this application;

[0016] Figure 3 for Figure 2 Schematic diagram of the FF section;

[0017] Figure 4 for Figure 2 Schematic diagram of the HH section;

[0018] Figure 5 This is an isometric view of the cross-sectional structure of the axial bleed air lead tube of this application.

[0019] 1. Drive shaft; 2. Shaft bleed air lead pipe; 3. Front support; 4. Front locating pin; 5. Front sealing ring; 6. Compressor test lead; 7. Rear support; 8. Rear locating pin; 9. Rear sealing ring; 10. External bleed air pipe; 11. Lead pipe bracket; 12. Central lead pipe; 13. Bleed air channel; 14. Wheel cooling port; 15. Front pin hole; 16. Rear pin hole; 17. Lead wire channel; 18. High-speed slip ring; 19. Compressor rotor; 20. Coupling. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] A real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor, such as Figure 1As shown, the system includes a drive shaft 1, a bleed air lead tube 2, a high-speed slip ring 18, and a compressor test lead 6. One end of the drive shaft 1 is connected to the engine's high-pressure shaft, and the other end is connected to the bleed air lead tube 2. The bleed air lead tube 2 is coaxially aligned with the engine axis and located inside the drive shaft 1. The high-speed slip ring 18 is coaxially aligned with the engine axis and located outside the bleed air lead tube 2. The high-speed slip ring 18 is connected to external data acquisition equipment of the core engine. One end of the compressor test lead 6 is connected to the high-speed slip ring 18, and then inserted along the engine axis into the bleed air lead tube 2. It then extends from the bleed air lead tube 2 and connects to a strain gauge or thermocouple 20 on the compressor rotor 19. The compressor test lead 6 is fixed to the blades of the compressor rotor 19 as it passes through them. The strain gauge or thermocouple 20 can be installed on any stage of the compressor rotor. Figure 1 In the middle, strain gauges and thermocouples 20 are installed on the eighth stage rotor of the compressor.

[0022] Before assembly, strain gauges or thermocouples 20 are installed on the compressor rotor 19. By installing the strain gauges or thermocouples 20 at designated positions on the compressor rotor 19, the vibration or temperature signals of the compressor rotor 19 can be measured. During operation, the shaft bleed air lead tube 2 rotates synchronously with the compressor rotor 19. After the strain gauges and thermocouples 20 collect the vibration or temperature test signals of the high-pressure rotor, the test signals pass through the compressor test lead 6, through the compressor rotor 19, into the shaft bleed air lead tube 2, and then through the drive shaft 1 into the high-speed slip ring 18. The signals transmitted by the high-speed slip ring 18 are collected and analyzed to obtain the dynamic stress or temperature test data of the high-pressure rotor, and finally transmitted to the external data acquisition equipment.

[0023] By installing a device inside the compressor that rotates synchronously with the compressor rotor 19, contact measurement and real-time synchronous measurement of the rotor wall parameters inside the compressor can be achieved, solving the problem in the prior art that the compressor rotor 19 cannot be measured in real time after the third stage.

[0024] Combination Figure 2-3Preferably, due to the high temperature inside the core machine, in order to ensure that the compressor test lead 6 can be in a normal working environment, the specific design is as follows: The axial bleed air lead pipe 2 includes an external bleed air pipe 10, a central lead pipe 12, and a lead pipe support 11; the central lead pipe 12 is coaxially arranged inside the external bleed air pipe 10, and a bleed air channel 13 is formed between the central lead pipe 12 and the external bleed air pipe 10. In this embodiment, the bleed air channel 13 is set into 6 groups, and each group of bleed air channel 13 is fan-shaped. There are multiple groups of lead pipe supports 11, which are spaced apart along the length direction of the central lead pipe 12 in the bleed air channel 13. A cooling ring cavity is formed between adjacent bleed air pipe supports. Multiple groups of bleed air through holes are opened at intervals along the circumferential direction of the bleed air pipe supports. External cold air can enter the bleed air ring cavity through the bleed air through holes. Multiple groups of wheel cooling ports 14 communicating with the rotor disk and disk cavity are opened along the circumferential direction at the position of the external bleed air pipe 10 corresponding to the position of the bleed air ring cavity.

[0025] The bleed air passage 13 can be connected to the cooling sealing gas inside the core engine. The cooling sealing gas enters the cooling ring cavity through the bleed air through hole. Part of it is used to cool the various stages of the discs and the disc cavity to ensure the normal operation and performance of the engine. The other part goes along the lead air pipe to the rear to supply cooling or sealing to the rear bearing and turbine disc cavity of the engine. In this process, the inside of the shaft bleed air lead pipe 2 is cooled. The test lead is located inside the shaft bleed air lead pipe 2. Being bathed in cold air can improve its life and reliability.

[0026] Through the above design, while ensuring the engine's basic cooling and power transmission functions, the compressor test lead 6 is brought out, which means that the compressor stress and temperature can be measured.

[0027] Preferably, the air intake holes and the wheel cooling port 14 are staggered circumferentially, so that the cooling sealing gas entering the cooling ring cavity from each air intake hole mixes with each other and then flows out through the wheel cooling port 14, thereby effectively improving the cooling effect. The lead tube support 11 has multiple sets of lead tube channels 17 spaced circumferentially. The lead tube channels 17 are connected to the outer side of the external air intake pipe 10 and the inner side of the central lead tube 12. The compressor test lead 6 is connected to the strain gauge and thermocouple 20 on the compressor rotor 19 through the lead tube channels 17, and it is ensured that the sealing cooling gas and the lead tube channels 17 do not interfere with each other at the connection position.

[0028] Combination Figure 4-5 Preferably, the angle between the lead channel 17 and the axis of the central lead tube 12 is 45° to 60° to ensure the operability of the test lead assembly and the reliability of the working state.

[0029] Preferably, the front end of the external air intake pipe 10 is provided with a front support seat 3, and a front pin hole 15 is opened on the outer wall of the front end of the external air intake pipe 10. A front positioning pin 4 is provided in the front pin hole 15 and connected to the inner side of the front support seat 3. The outer side of the front support seat 3 is connected to the drive shaft 1, and a front sealing ring 5 is provided between the front support seat 3 and the drive shaft 1. The rear end of the external air intake pipe 10 is provided with a rear support seat 7, and a rear pin hole 16 is opened on the outer wall of the rear end of the external air intake pipe 10. A rear positioning pin 8 is provided in the rear pin hole 16 and connected to the inner side of the rear support seat 7. A rear sealing ring 9 is connected between the rear support seat 7 and the drive shaft 1. The front support seat 3 and the rear support seat 7 ensure the stability of the connection between the external air intake pipe 10 and the drive shaft 1, and the front sealing ring 5 and the rear sealing ring 9 ensure the sealing of the connection between the external air intake pipe 10 and the drive shaft 1.

[0030] Preferably, the front end of the axial bleed air lead pipe 2 is fixed to the drive shaft 1 with bolts. The rear support 7 has a funnel-shaped structure, with the open end of the rear support 7 facing the rear of the compressor rotor 19. The end of the axial bleed air lead pipe 2 has a tapered structure and is tightly fitted to the inner wall of the rear support 7. Because the temperature is high at the axial position of the compressor rotor 19, the axial bleed air lead pipe 2 will undergo thermal expansion and contraction. During normal engine operation, the temperature inside the compressor disk cavity gradually increases, and the axial bleed air lead pipe will deform due to heat. If the front and rear sections of the lead pipe adopt a fixed support structure, the center position of the lead pipe will warp and deform due to axial limitation, causing it to rub against the disk center, resulting in excessive vibration of the entire engine and, in severe cases, breakage. Therefore, in this application, the front end of the axial air duct 2 is fixed with bolts so that the distance between it and the high-speed slip ring 18 will not change. The rear end is formed by the funnel-shaped structure of the rear support 7. When thermal expansion and contraction occur, the axial air duct 2 will extend axially, so as not to affect other connection structures on the axial air duct 2, thus ensuring structural stability.

[0031] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change.

[0032] Secondly: The accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0033] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor, characterized in that: The system includes a drive shaft (1), a spool bleed air lead tube (2), a high-speed slip ring (18), and a compressor test lead (6). One end of the drive shaft (1) is connected to the high-pressure shaft of the engine, and the other end is connected to the spool bleed air lead tube (2). The spool bleed air lead tube (2) is coaxial with the engine axis and located inside the drive shaft (1). The high-speed slip ring (18) is coaxial with the engine axis and located outside the spool bleed air lead tube (2). One end of the compressor test lead (6) is connected to the high-speed slip ring (18), and then inserted into the spool bleed air lead tube (2) along the engine axis. Then it extends out from the spool bleed air lead tube (2) and is connected to a strain gauge or thermocouple (20) on the compressor rotor (19). The axial air intake pipe (2) includes an external air intake pipe (10), a central air intake pipe (12), and an air intake pipe support (11). The central air intake pipe (12) is coaxially disposed inside the external air intake pipe (10). An air intake channel (13) is formed between the central air intake pipe (12) and the external air intake pipe (10). There are multiple sets of air intake pipe supports (11) and they are spaced apart along the length of the central air intake pipe (12) in the air intake channel (13). A cooling ring cavity is formed between adjacent air intake pipe supports (11). Multiple sets of air intake holes are spaced apart along the circumferential direction of the air intake pipe supports (11). External cold air can enter the air intake ring cavity through the air intake holes. Multiple sets of wheel cooling ports (14) communicating with the rotor disk and disk cavity are opened along the circumferential direction at the position of the external air intake pipe (10) corresponding to the position of the air intake ring cavity.

2. The real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor as described in claim 1, characterized in that: The air intake holes and the wheel cooling port (14) are staggered in the circumferential direction. The lead wire support (11) has multiple sets of lead wire channels (17) spaced apart in the circumferential direction. The lead wire channels (17) are connected to the outer side of the outer air intake pipe (10) and the inner side of the central lead wire pipe (12).

3. The real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor as described in claim 2, characterized in that: The angle between the lead channel (17) and the axis of the central lead tube (12) is 45° to 60°.

4. The real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor as described in claim 1, characterized in that: The front end of the axial air duct (2) is provided with a front support seat (3), and the inner side of the front support seat (3) is connected to the axial air duct (2) with a front positioning pin (4). The outer side of the front support seat (3) is connected to the drive shaft (1), and a front sealing ring (5) is provided between the front support seat (3) and the drive shaft (1). The rear end of the axial air duct (2) is provided with a rear support seat (7), and the inner side of the rear support seat (7) is connected to the axial air duct with a rear positioning pin (8). A rear sealing ring (9) is connected between the rear support seat (7) and the drive shaft (1).

5. The real-time synchronous measurement device for dynamic stress and temperature of a multi-stage compressor rotor as described in claim 4, characterized in that: The front end of the axial bleed air lead tube (2) is fixed to the drive shaft (1) by bolts. The rear support seat (7) has a funnel-shaped structure. The open end of the rear support seat (7) faces the rear of the compressor rotor (19). The end of the axial bleed air lead tube (2) has a tapered structure and the end of the axial bleed air lead tube (2) is tightly fitted to the inner wall of the rear support seat (7).

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