CN113565583A - Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine - Google Patents
Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine Download PDFInfo
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- CN113565583A CN113565583A CN202110814212.3A CN202110814212A CN113565583A CN 113565583 A CN113565583 A CN 113565583A CN 202110814212 A CN202110814212 A CN 202110814212A CN 113565583 A CN113565583 A CN 113565583A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
Abstract
The application relates to the field of a birotor turbofan engine, in particular to a dynamic stress testing device for a high-pressure turbine rotor of a complete machine of the birotor turbofan engine, which comprises a short-range remote measuring mounting seat, a high-vortex disc testing mechanism, a stator testing mechanism and a high-vortex disc testing lead, wherein the short-range remote measuring mounting seat, the high-vortex disc testing mechanism, the stator testing mechanism, the high-vortex disc testing lead, the stator testing lead and a high-temperature strain gauge are arranged; the short-range telemetering mounting seat is arranged at an interstage disk center of the high-pressure compressor rotor assembly and connected with the high-pressure compressor rotor assembly, and the high-vortex testing mechanism is connected with the short-range telemetering mounting seat; the stator testing mechanism is arranged on the intermediary casing and is kept still; the high-vortex disc testing mechanism and the stator testing mechanism are both arranged in the short-range remote measuring mounting seat. The dynamic stress test device has the technical effect of being capable of testing the dynamic stress of the high-pressure turbine rotor of the double-rotor turbofan engine under the integral condition.
Description
Technical Field
The application belongs to the field of double-rotor turbofan engines, and particularly relates to a dynamic stress testing device for a complete machine high-pressure turbine rotor of a double-rotor turbofan engine.
Background
The dynamic stress test of the high-pressure turbine rotor of the complete machine of the birotor turbofan engine is a recognized problem in the world, and a plurality of technical bottlenecks such as limited test modification space, difficult remote measurement system layout, difficult test signal leading-out and the like exist. Therefore, the research on the technical research of the dynamic stress test of the high-pressure turbine rotor of the complete machine of the double-rotor turbofan engine is significant for improving the test capability of the complete machine of the aeroengine in China.
Dynamic stress tests on high-pressure turbine rotors in domestic industries are carried out on single-rotor engines or core machines, and usually a telemetry system or a slip ring current leading device is adopted to realize transmission of test signals from the rotors to ground test equipment. The telemetering system or the slip ring electricity leading device is composed of a rotor component and a stator component. The rotor part is arranged at the shaft end of the rotor shaft and rotates along with the rotor shaft, and the stator part is arranged on a static part (such as a bearing casing) of the engine. Test signal leads on the high vortex rotor typically run along the surface of the turbine disk into the turbine hub and are connected to a telemetry/power system mounted at the shaft end, as disclosed in patent application publication CN 112446146A.
The disadvantages of the prior art solutions are as follows:
because a telemetering device or an electric leading device cannot be arranged at the shaft end of the high-pressure turbine shaft under the condition of the whole machine, the prior art scheme is not suitable for the dynamic stress test of the high-pressure turbine rotor of the whole machine of the double-rotor turbofan engine. Therefore, how to perform dynamic stress test on the high-pressure turbine rotor of the complete machine of the double-rotor turbofan engine is a problem to be solved.
Disclosure of Invention
The application aims at providing a device for testing the dynamic stress of a complete machine high-pressure turbine rotor of a double-rotor turbofan engine, so as to solve the problem that the dynamic stress test of the high-pressure turbine rotor of the double-rotor turbofan engine under the complete machine condition cannot be carried out in the prior art.
The technical scheme of the application is as follows: a dynamic stress testing device for a high-pressure turbine rotor of a complete machine of a birotor turbofan engine comprises a short-range remote measurement mounting seat, a high-vortex disk testing mechanism, a stator testing mechanism and a high-vortex disk testing lead, wherein the short-range remote measurement mounting seat, the high-vortex disk testing mechanism, the stator testing mechanism, the high-vortex disk testing lead, a stator testing lead and a high-temperature strain gauge are included; the short-range telemetering mounting seat is arranged at an interstage disk center of the high-pressure compressor rotor assembly and connected with the high-pressure compressor rotor assembly, and the high-vortex testing mechanism is connected with the short-range telemetering mounting seat; the stator testing mechanism is arranged on the intermediary casing and is kept still; the high-vortex disk testing mechanism and the stator testing mechanism are both arranged in the short-range remote testing mounting seat, and the high-vortex disk testing mechanism comprises a signal processing part, a first power supply part and a transmitting antenna, wherein the first power supply part is electrically connected with the signal processing part; the stator testing mechanism comprises a second power supply part and a receiving antenna, the transmitting antenna is radially coupled with the receiving antenna, and the first power supply part and the second power supply part are radially coupled to supply power to the signal processing part; the high-temperature strain gauge is arranged on the high-pressure turbine rotor, the high-vortex disc test lead is connected between the high-temperature strain gauge and the signal processing part, and the stator test lead is arranged between the stator test mechanism and the bench test equipment.
Preferably, the test device further comprises a double-layer lead guide pipe arranged between the short-range remote measurement mounting seat and the high-pressure turbine rear shaft, wherein a lead channel arranged along the axial direction of the high-pressure turbine rotor is formed in the double-layer lead guide pipe, an inclined hole is formed in the short-range remote measurement mounting seat, and the high-vortex disk test lead penetrates out of the inclined hole, enters one end of the lead channel, extends out of the other end of the lead channel and is connected with the high-temperature strain gauge.
Preferably, the test device further comprises a cooling gas path, wherein a round hole is formed in the short-range remote measurement mounting seat, cooling gas of the cooling gas path is led out from compressed air of the rack, passes through a space between the high-vortex disc testing mechanism and the stator testing mechanism and then is discharged from the round hole of the short-range remote measurement mounting seat, and the stator testing lead is arranged in the cooling gas path.
Preferably, the signal processing part comprises a telemetry circuit mounting bracket, a telemetry circuit module and a rotor test lead, and the first power supply part comprises an induction power supply secondary coil and a rotor insulating ring; the telemetry circuit module, the rotor insulating ring and the transmitting antenna are all arranged on the telemetry circuit mounting bracket, and the induction power supply secondary coil is wound on the rotor insulating ring; the second power supply part comprises a telemetering stator mounting seat, an induction power supply main coil and a stator insulating ring; the remote measuring stator mounting seat is arranged on the middle casing, the receiving antenna and the stator insulating ring are arranged on the remote measuring stator mounting seat, the induction power supply main coil is wound on the stator insulating ring, and the receiving antenna is connected with the rack testing equipment; the receiving antenna and the transmitting antenna are coaxially and oppositely arranged, and the induction power supply main coil and the induction power supply auxiliary coil are coaxially and oppositely arranged.
Preferably, the telemetry circuit module is packaged inside the telemetry circuit mounting bracket by a sealant; the rotor insulating ring is wound with an induction power supply secondary coil on the inner side groove and is fixed by using an adhesive; the rotor insulating ring is fixed on the telemetering circuit mounting bracket through an adhesive;
the stator insulating ring is wound with an induction power supply main coil on the inner side groove and is fixed by using an adhesive; the receiving antenna is fixed on a groove on the outer side of the stator insulating ring through an adhesive, and the stator insulating ring is fixed on the telemetering stator mounting seat through the adhesive.
Preferably, the telemetry circuit mounting bracket is provided with a first slot structure and a second slot structure which are positioned on different side walls; a circumferential positioning pin is connected between the first clamping groove structure and the short-range remote measurement mounting seat, and an axial positioning pin, an end surface locking plate and an end surface locking nut are connected between the second clamping groove structure and the short-range remote measurement mounting seat; and a fastening screw is connected between the telemetering stator mounting seat and the intermediate casing.
Preferably, the short-range remote measurement mounting seat comprises an inner side matched with the rotating shaft, a middle side used for mounting the high-vortex disc testing mechanism and the stator testing mechanism, and an outer side matched with the high-pressure turbine rotor, wherein an annular groove structure is formed in the middle side, a plurality of pin holes are formed in the annular groove and are respectively matched with the axial positioning pin and the circumferential positioning pin, a thread structure is arranged on the upper end face of the annular groove, and a plurality of bolt holes are uniformly distributed in the outer side of the short-range remote measurement mounting seat.
Preferably, the both ends of lead wire passageway are equipped with first lead wire inclined hole and second lead wire inclined hole, the surface of double-deck lead wire pipe is equipped with multiunit annular strengthening rib, be equipped with first banding concave station structure and second banding concave station structure on the outer wall of double-deck lead wire pipe respectively, be equipped with first banding boss structure on the short range telemetering measurement mount pad, first banding concave station structure cooperatees with first banding boss structure.
Preferably, a rear shaft modified piece is arranged on the rear shaft of the high-pressure turbine, a third lead inclined hole through which a high-vortex disc test lead extends is formed in the rear shaft modified piece, the angle of the third lead inclined hole is the same as that of the second lead inclined hole, the high-vortex disc test lead extends from the third lead inclined hole and then is connected with the high-temperature strain gauge, a second belt-shaped boss structure matched with the second belt-shaped boss structure is arranged on the rear shaft modified piece, and an exhaust hole capable of introducing cooling gas is formed in the rear shaft modified piece.
A twin rotor turbofan engine comprising a high pressure turbine rotor rotational stress testing apparatus according to any one of claims 1 to 9.
The utility model provides a birotor turbofan engine complete machine high pressure turbine rotor dynamic stress testing arrangement, disk center department sets up high whirlpool dish accredited testing organization and stator accredited testing organization in the stage of high pressure compressor rotor subassembly, high whirlpool dish accredited testing organization and high pressure turbine rotor rotate in step, stator accredited testing organization keeps motionless, high whirlpool dish accredited testing organization tests high pressure turbine rotor's dynamic stress through high whirlpool dish test lead, send to stator accredited testing organization through radial coupling after to this signal processing, stator accredited testing organization supplies power to the circuit in the high whirlpool dish accredited testing organization through radial coupling, realize the dynamic stress stable measurement of short range high pressure turbine rotor.
Preferably, a double-layer lead guide is arranged between the short-range remote measurement mounting seat and the rear shaft of the high-pressure turbine, a lead channel is arranged on the double-layer lead guide, and the high-vortex disk test lead penetrates through the lead channel to realize long-distance stable transmission.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic overall cross-sectional view of an embodiment of the present application;
FIG. 2 is a schematic cross-sectional view of a double layer wire guide according to an embodiment of the present application;
FIG. 3 is a schematic cross-sectional view of a short-range telemetry system in accordance with an embodiment of the present application;
FIG. 4 is a schematic structural diagram of a first and a second card slot structure according to an embodiment of the present disclosure;
FIG. 5 is a schematic cross-sectional view of a short-range telemetry mount according to an embodiment of the present application;
fig. 6 is a schematic structural view of a rear axle modification according to an embodiment of the present application.
1. A short-range telemetry mount; 2. a short-range telemetry system; 3. a double-layer lead guide tube; 4. a rear axle retrofit part; 5. a conduit lock nut; 6. cooling the gas circuit; 7. a high scroll test lead; 8. an axial positioning pin; 9. a circumferential positioning pin; 10. a thread structure; 11. a circular hole; 12. an inclined hole; 13. a first band-shaped boss structure; 14. bolt holes; 15. a telemetry circuit module; 16. the telemetering circuit is provided with a bracket; 17. an inductive power supply secondary coil; 18. a rotor insulating ring; 19. end face locking plates; 20. an end face lock nut; 21. a transmitting antenna; 22. a stator test lead; 23. a telemetering stator mounting base; 24. fastening screws; 25. a receiving antenna; 26. a stator insulating ring; 27. an inductively powered main coil; 28. a rotor test lead; 29. a first card slot structure; 30. a second card slot structure; 31. a first strip-shaped recessed land structure; 32. a first lead inclined hole; 33. an annular reinforcing rib; 34. a second lead inclined hole; 35. a second belt-like plateau structure; 36. a second band-shaped boss structure; 37. a third lead inclined hole; 38. an exhaust hole; 39. a fan rotor assembly; 40. a high pressure compressor rotor assembly; 41. A high pressure turbine rotor assembly; 42. a low pressure turbine rotor assembly; 43. an intermediary case; 44. a fulcrum bearing; 45. a low-pressure turbine shaft; 46. high temperature strain gauges.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In a first embodiment, a device for testing dynamic stress of a high-pressure turbine rotor of a complete machine of a birotor turbofan engine, as shown in fig. 1 and 3, comprises a short-range remote measurement mounting base 1, a high-vortex testing mechanism, a stator testing mechanism, a high-vortex testing lead 7, a stator testing lead 22 and a high-temperature strain gauge 46.
The birotor turbofan engine comprises a fan rotor assembly 39, a high-pressure compressor rotor assembly 40, a combustion chamber, a high-pressure turbine rotor assembly 41, a low-pressure turbine rotor assembly 42, an intermediate casing 43, a fulcrum bearing 44, a low-pressure turbine shaft 45 and a nozzle. The fan rotor, the low-pressure turbine rotor and the low-pressure turbine shaft 45 form a low-pressure rotor, and the high-pressure compressor rotor and the high-pressure turbine shaft form a high-pressure rotor. According to the structural characteristics of the whole double-rotor turbofan engine, a telemetering or electric leading device cannot be installed at the shaft end.
In order to test the vibration stress of the high-pressure turbine rotor of the double-rotor turbofan engine, the requirement of the environmental temperature is firstly required to be met, namely the temperature of a test part cannot be too high; then, power supply of the test part and output of signals need to be ensured so as to process and output the acquired signals; and finally, the space requirement is required to be met, and the slip ring electricity leading device is taken as an integral piece with an independent function, so that the slip ring electricity leading device cannot be disassembled, occupies a large space and is difficult to meet the space requirement. Therefore, the power supply and the signal output are carried out in a radial coupling mode, the occupied space is greatly reduced, the stator testing mechanism and the high-vortex disk testing mechanism are arranged on two sides of the radial coupling, the stator testing mechanism is fixed and does not move to be connected with external equipment, and the high-vortex disk testing mechanism and the high-pressure turbine rotor synchronously move to meet the testing requirements.
The stator testing mechanism is disposed on the intermediate case 43, and the stator testing mechanism and the stator testing lead 22 are fixed. The short-range remote measuring mounting seat 1 is arranged on the high-pressure compressor rotor assembly 40, and the short-range remote measuring mounting seat 1, the high-vortex disc testing mechanism and the high-vortex disc testing lead 7 move synchronously along with the high-pressure compressor rotor assembly 40.
Because the ambient temperature of the high-pressure turbine rotor is more than 700 ℃, the short-range telemetering mounting seat 1 is arranged at the interstage disk center of the high-pressure compressor rotor assembly 40, and the problem that the high ambient temperature of the high-pressure turbine rotor causes over-temperature damage of testing devices such as telemetering and electrical leading devices is solved.
The high vortex plate testing mechanism and the stator testing mechanism form a telemetering circuit, the high vortex plate testing mechanism and the stator testing mechanism are both arranged in the short-range telemetering mounting seat 1, and the high vortex plate testing mechanism comprises a signal processing part, a first power supply part and a transmitting antenna 21, wherein the first power supply part is connected with the signal processing part; the stator testing mechanism includes a second power supply and a receiving antenna 25. The transmitting antenna 21 is radially coupled with the receiving antenna 25, and the transmitting antenna 21 can send the signal processed by the signal processing part to the receiving antenna 25, so that the signal output requirement is met; the first power supply member is radially coupled to the second power supply line to meet a demand for power supply to the signal processing member.
The high-temperature strain gauge 46 is arranged on the high-pressure turbine rotor, the high-vortex disc test lead 7 is connected between the high-temperature strain gauge 46 and the high-vortex disc test mechanism, the stator test lead 22 is arranged between the stator test mechanism and the bench test equipment, and the test signals are transmitted in a long distance through the high-vortex disc test lead 7 and the stator test lead 22.
When the vibration stress of the high-pressure turbine rotor is tested, the high-temperature strain gauge 46 senses a vibration test signal of the high-pressure turbine rotor, the test signal is transmitted into the signal processing piece through the high-pressure turbine disk test lead 7, the signal processing piece amplifies, filters and collects the test signal, the high-pressure turbine rotor test signal is sent out by the transmitting antenna 21, the receiving antenna 25 right opposite to the transmitting antenna 21 receives the signal, and the signal is transmitted to the bench test equipment through the static test lead to complete transmission of the test signal. In the process, the first power supply part and the second power supply part rotate mutually to supply power to the signal processing part effectively. The technical bottlenecks of limited complete machine test modification space, difficult layout of a remote measuring system, difficult leading-out of a test signal and the like of the double-rotor turbofan engine are broken through, and the problem that a transmitted shaft end remote measuring/electric leading device system cannot complete the dynamic stress test of the complete machine high-pressure turbine rotor of the double-rotor turbofan engine is solved.
As shown in fig. 1 and 2, preferably, in order to realize the long-distance stable transmission of the high-scroll testing lead 7 of the lead, the high-scroll testing lead further comprises a double-layer lead guide 3 arranged between the short-range telemetering mounting seat 1 and the rear shaft of the high-pressure turbine, wherein the double-layer lead guide 3 is cylindrical and is sleeved between the high-pressure shaft and the low-pressure shaft, the high-pressure shaft is positioned at the inner side of the double-layer lead guide 3, and the double-layer lead guide 3 moves synchronously along with the rotor of the high-pressure turbine.
The double-layer lead guide pipe 3 is provided with a lead channel which is arranged along the axial direction of the high-pressure turbine rotor, the near distance telemetering mounting seat 1 is provided with an inclined hole 12, and the high-vortex disk testing lead 7 penetrates out of the inclined hole 12 and is led into one end of the lead channel, and extends out of the other end of the lead channel to be connected with the high-temperature strain gauge 46. Because high vortex dish test lead 7 and high-pressure turbine rotor synchronous revolution, double-deck wire guide 3 plays effectual guard action to high vortex dish test lead 7 to realize the long distance of high vortex dish test lead 7 and stably transmit.
As shown in fig. 1, 3 and 4, a cooling gas circuit 6 is preferably further included to ensure stable operation of the high scroll testing mechanism and the stator testing mechanism. The intermediate casing 43 is provided with a comb tooth sleeve, the cooling gas path 6 is arranged between the intermediate casing 43 and the comb tooth sleeve, namely the intermediate casing 43 is correspondingly modified according to the arrangement of the cooling gas path 6, the short-range remote measurement mounting seat 1 is provided with a round hole 11, the cooling gas of the cooling gas path 6 is led out from the rack compressed air, is discharged from the round hole 11 of the short-range remote measurement mounting seat 1 after passing between the high vortex disc testing mechanism and the stator testing mechanism, and the stator testing lead 22 is arranged in the cooling gas path 6.
When high whirlpool dish accredited testing organization and stator accredited testing organization work, cooling gas flows into between the two through cooling gas circuit 6, and the steady work in order to guarantee both continues to cool off, and stator test lead wire 22 can cool off stator test lead wire 22 on the one hand in locating cooling gas circuit 6, and on the other hand has reduced the winding displacement problem of stator test lead wire 22.
The cooling gas discharged from the circular hole 11 continuously flows along the axial direction of the high-pressure turbine rotor, flows into the rear shaft of the high-pressure turbine rotor to cool the high-pressure turbine rotor, and plays a cooling role for the high-pressure turbine rotor and the high scroll testing lead 7 under the condition that the normal operation of the high-pressure turbine shaft is not influenced.
Preferably, the signal processing element comprises a telemetry circuit mounting bracket 16, a telemetry circuit module 15 and a rotor test lead 28, and the first power supply element comprises an induction power supply secondary coil 17 and a rotor insulating ring 18; the telemetry circuit module 15, the rotor insulating ring 18 and the transmitting antenna 21 are all arranged on the telemetry circuit mounting bracket 16, the induction power supply secondary coil 17 is wound on the rotor insulating ring 18, and the rotor test lead 28 is connected with the telemetry circuit module 15 and is led out from the short-range telemetry mounting base 1 to be connected with the high-scroll disk test lead 7.
The second power supply part comprises a telemetering stator mounting seat 23, an induction power supply main coil 27 and a stator insulating ring 26; the telemetering stator mounting seat 23 is arranged on the intermediary casing 43, the receiving antenna 25 and the stator insulating ring 26 are arranged on the telemetering stator mounting seat 23, the induction power supply main coil 27 is wound on the stator insulating ring 26, the receiving antenna 25 is connected with the bench test equipment, the receiving antenna 25 and the induction power supply main coil 27 are two different wires and are transmitted by the stator test lead 22.
The receiving antenna 25 and the transmitting antenna 21 are coaxially disposed oppositely, and the inductive feeding main coil 27 and the inductive feeding sub-coil 17 are coaxially disposed oppositely. The receiving antenna 25, the transmitting antenna 21, the inductive power supply main coil 27 and the inductive power supply auxiliary coil 17 are all in a circular ring shape, and the inductive power supply main coil 27 and the inductive power supply auxiliary coil 17 achieve effective power supply of the telemetry circuit module 15 on the high-voltage rotor under the rotating condition.
Preferably, in order to ensure the performance of the telemetry circuit, a telemetry circuit packaging structure is required to be designed so as to realize fixation, sealing, insulation and protection of the telemetry circuit. Specifically, the telemetry circuit module 15 is packaged inside the telemetry circuit mounting bracket 16 through sealant, the rotor insulating ring 18 is wound around the induction power supply secondary coil 17 on the inner side groove and fixed by using adhesive, and the rotor insulating ring 18 is fixed on the telemetry circuit mounting bracket 16 through adhesive.
The stator insulating ring 26 is wound on the inner side groove to supply the power main coil and is fixed by using adhesive, the receiving antenna 25 is fixed on the outer side groove of the stator insulating ring 26 by using adhesive, and the stator insulating ring 26 is remotely measured on the stator mounting seat 23 by using adhesive.
The structure realizes the sealing, insulation and protection of the telemetering circuit.
Fastening screws 24 are connected between the telemetering stator mounting seat 23 and the intermediate casing, a first clamping groove structure 29 and a second clamping groove structure 30 which are located on different side walls are arranged on the telemetering circuit mounting support 16, the first clamping groove structure 29 and the second clamping groove structure 30 respectively comprise two groups of clamping plates which are arranged side by side at intervals and offset against the short-range telemetering mounting seat 1, a circumferential positioning pin 9 is connected between the first clamping groove structure 29 and the short-range telemetering mounting seat 1, and an axial positioning pin 8 is connected between the second clamping groove structure 30 and the short-range telemetering mounting seat 1. To achieve stable fixation of the telemetry circuit.
Through the design, the remote sensing circuit is fixed, sealed, insulated and protected, the electric heating performance of the remote sensing circuit is enhanced, and the resistance of the remote sensing module to adverse factors such as vibration, impact, electromagnetic interference and the like at a high rotating speed is improved.
As shown in fig. 1 and 5, preferably, the short-range telemetry mounting base 1 is divided into an inner portion, a middle portion and an outer portion, the inner side is a step-shaped hollow cylinder and is sleeved on the rotating shaft, two first band-shaped boss structures 13 are symmetrically distributed on one side of the step, and the first band-shaped boss structures 13 are arranged in an arc shape.
The middle side is a hollow cylinder with an opening facing one side of the cooling gas circuit 6, an annular groove structure is arranged at the middle side, the telemetering circuit is arranged in the annular groove, a plurality of pin holes are uniformly distributed on the side wall of the circumferential surface of the annular groove and used for being matched with a telemetering circuit mounting support 16 to mount a circumferential positioning pin 9 for circumferential limiting of the short-range telemetering system 2 and preventing the short-range telemetering system 2 from axially rotating in a test; the end of the annular groove is provided with a pin hole matched with the axial positioning pin 8 for axially limiting the short-range remote sensing system 2.
The round hole 11 and the inclined hole 12 are uniformly distributed along the end part of the annular groove, the thread structure 10 is arranged on the upper end face of the annular groove, namely the opening part, the annular end face locking plate 19 and the annular end face locking nut 20 are arranged between the telemetering circuit mounting bracket 16 and the thread structure 10, and the end face locking nut 20 is matched with the end face locking plate 19 and the thread structure 10 to realize the mutual fixation between the telemetering circuit mounting bracket 16 and the short-range telemetering mounting seat 1. The outer side of the threaded structure 10 is provided with a comb tooth tightly matched with the comb tooth sleeve for sealing and ensuring the flow direction of cooling air in the cooling air path 6 to the telemetering circuit.
The short-range remote sensing mounting seat 1 is of a hollow cylindrical structure with an opening facing a high-pressure compressor rotor, a flanging is arranged at the opening of the cylinder on the outer side, and a plurality of bolt holes 14 are uniformly distributed in the flanging, namely the bottom surface of the short-range remote sensing mounting seat 1 and used for fixing the short-range remote sensing mounting seat 1 to the high-pressure compressor rotor assembly 40.
As shown in fig. 2, preferably, a plurality of groups of lead channels are uniformly distributed on the double-layer lead guide 3 along the circumferential direction thereof, the high-pressure scroll test lead 7 has a plurality of strands and is respectively disposed in different lead channels, a first lead inclined hole 32 and a second lead inclined hole 34 are disposed at two ends of the lead channel, a plurality of groups of annular reinforcing ribs 33 are disposed on the outer surface of the double-layer lead guide 3, a first strip-shaped concave platform structure 31 and a second strip-shaped concave platform structure 35 are respectively disposed on the outer wall of the double-layer lead guide 3, the first strip-shaped concave platform structure 31 is matched with the first strip-shaped convex platform structure 13, and the second strip-shaped concave platform structure 35 is used for being matched and fixed with the rear shaft of the high-pressure turbine, so as to effectively protect the high-pressure scroll test lead 7. The outer surface of the double-layer lead guide pipe 3 is provided with a plurality of groups of environment reinforcing ribs 33 so as to improve the strength of the double-layer lead guide pipe 3.
As shown in fig. 1 and 6, preferably, a rear shaft modification member 4 is disposed on the high-pressure turbine rear shaft, the rear shaft modification member 4 includes a connection portion and a cone portion, the connection portion is in a V-shaped structure and is connected to the high-pressure turbine rotor assembly 41, a second strip-shaped boss structure 36 is disposed at one end of the cone portion, which is far away from the double-layer wire guide tube 3, the second strip-shaped boss structure 36 and the second strip-shaped boss structure 35 are locked to each other, and a guide tube locking nut 5 for fixing the double-layer wire guide tube 3 to the rear shaft modification member 4 is further disposed at an end of the cone portion.
A third lead inclined hole 37 is formed in the position, corresponding to the second lead inclined hole 34, of the conical part, the angle between the second lead inclined hole 34 and the third lead inclined hole 37 is the same, and after the high-vortex test lead 7 extends out of the second lead pipe, the high-vortex test lead passes through the third lead inclined hole 37 and is connected with the high-temperature strain gauge 46 along the connecting part. The portion of the high scroll test lead 7 protruding above the conical portion is fixed by means of a metal foil by spot welding.
A plurality of exhaust holes 38 distributed along the circumferential direction of the rotating shaft are formed between the cone part and the connecting part, and cooling air led out from the near distance telemetering mounting seat 1 passes through the high-pressure turbine rotor assembly 41, enters the exhaust holes 38 and is exhausted from the exhaust holes 38 for cooling.
The double-rotor turbofan engine comprises the high-pressure turbine rotor dynamic stress testing device in the first embodiment, and the technical effect of effectively testing the high-pressure turbine rotor dynamic stress of the whole double-rotor turbofan engine is achieved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a birotor turbofan engine complete machine high pressure turbine rotor dynamic stress testing arrangement which characterized in that: the testing device comprises a short-range remote measuring mounting seat (1), a high-vortex disc testing mechanism, a stator testing mechanism, a high-vortex disc testing lead (7), a stator testing lead (22) and a high-temperature strain gauge (46);
the short-range telemetering mounting seat (1) is arranged at an interstage disk center of the high-pressure compressor rotor assembly (40) and connected with the high-pressure compressor rotor assembly (40), and the high-vortex testing mechanism is connected with the short-range telemetering mounting seat (1); the stator testing mechanism is arranged on the intermediary casing (43) and is kept still;
the high-vortex disc testing mechanism and the stator testing mechanism are both arranged in the short-range remote measuring mounting seat (1), and the high-vortex disc testing mechanism comprises a signal processing part, a first power supply part and a transmitting antenna (21), wherein the first power supply part is electrically connected with the signal processing part; the stator testing mechanism comprises a second power supply part and a receiving antenna (25), the transmitting antenna (21) and the receiving antenna (25) are coupled in a radial direction, and the first power supply part and the second power supply part are coupled in the radial direction to supply power to the signal processing part;
the high-temperature strain gauge (46) is arranged on the high-pressure turbine rotor, the high-vortex disc test lead (7) is connected between the high-temperature strain gauge (46) and the signal processing part, and the stator test lead (22) is arranged between the stator test mechanism and the rack test equipment.
2. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine according to claim 1, characterized in that: the high-temperature turbine testing device is characterized by further comprising a double-layer lead guide pipe (3) arranged between the short-range remote sensing mounting seat (1) and the rear shaft of the high-pressure turbine, wherein a lead channel arranged along the axial direction of the high-pressure turbine rotor is formed in the double-layer lead guide pipe (3), an inclined hole (12) is formed in the short-range remote sensing mounting seat (1), and the high-temperature turbine disk testing lead (7) penetrates out of the inclined hole (12) to enter one end of the lead channel and extends out of the other end of the lead channel to be connected with a high-temperature strain gauge (46).
3. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine according to claim 1, characterized in that: still include cooling gas circuit (6), round hole (11) have been seted up on short range telemetering measurement mount pad (1), the cooling gas of cooling gas circuit (6) is drawn forth, is discharged from round hole (11) of short range telemetering measurement mount pad (1) after between high whirlpool dish accredited testing organization and the stator accredited testing organization from rack compressed air, stator test lead wire (22) are located in cooling gas circuit (6).
4. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine according to claim 1, characterized in that: the signal processing part comprises a telemetry circuit mounting bracket (16), a telemetry circuit module (15) and a rotor test lead (28), and the first power supply part comprises an induction power supply secondary coil (17) and a rotor insulating ring (18); the telemetry circuit module (15), the rotor insulating ring (18) and the transmitting antenna (21) are all arranged on the telemetry circuit mounting bracket (16), and the induction power supply secondary coil (17) is wound on the rotor insulating ring (18);
the second power supply part comprises a telemetering stator mounting seat (23), an induction power supply main coil (27) and a stator insulating ring (26); the telemetering stator mounting seat (23) is arranged on the intermediary casing (43), the receiving antenna (25) and the stator insulating ring (26) are arranged on the telemetering stator mounting seat (23), the induction power supply main coil (27) is wound on the stator insulating ring (26), and the receiving antenna (25) is connected with the bench test equipment;
the receiving antenna (25) and the transmitting antenna (21) are coaxially arranged oppositely, and the inductive power supply main coil (27) and the inductive power supply secondary coil (17) are coaxially arranged oppositely.
5. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine according to claim 4, wherein: the telemetry circuit module (15) is packaged inside the telemetry circuit mounting bracket (16) through sealant; the rotor insulating ring (18) is wound with an induction power supply auxiliary coil (17) on the inner side groove and is fixed by using an adhesive; the rotor insulating ring (18) is fixed to the telemetry circuit mounting bracket (16) through adhesive;
the stator insulating ring (26) is wound with an induction power supply main coil (27) on the inner groove and is fixed by using an adhesive; the receiving antenna (25) is fixed on a groove on the outer side of the stator insulating ring (26) through adhesive, and the stator insulating ring (26) is fixed on the telemetering stator mounting seat (23) through adhesive.
6. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine according to claim 4, wherein: a first clamping groove structure (29) and a second clamping groove structure (30) which are positioned on different side walls are arranged on the telemetering circuit mounting bracket (16); a circumferential positioning pin (9) is connected between the first clamping groove structure (29) and the short-range remote measurement mounting seat (1), and an axial positioning pin (8) is connected between the second clamping groove structure (30) and the short-range remote measurement mounting seat (1);
and a fastening screw (24) is connected between the telemetering stator mounting seat (23) and the intermediate casing.
7. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine as claimed in claim 6, is characterized in that: short range telemetering measurement mount pad (1) including with pivot complex inboard, be used for installing high whirlpool dish accredited testing organization and stator accredited testing organization the well side, with high-pressure turbine rotor complex outside, the ring channel structure has been seted up to well side position, seted up a plurality of cotter holes on the ring channel and respectively with axial positioning pin (8) and circumference locating pin (9) cooperation, the up end of ring channel is equipped with helicitic texture (10), the outside equipartition of short range telemetering measurement mount pad (1) has a plurality of bolt holes (14).
8. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine as claimed in claim 2, wherein: the both ends of lead wire passageway are equipped with first lead wire inclined hole (32) and second lead wire inclined hole (34), the surface of double-deck lead wire pipe (3) is equipped with multiunit annular strengthening rib (33), be equipped with first banding concave station structure (31) and banding concave station structure of second (35) on the outer wall of double-deck lead wire pipe (3) respectively, be equipped with first banding boss structure (13) on short range telemetering measurement mount pad (1), first banding concave station structure (31) cooperate with first banding boss structure (13).
9. The device for testing the dynamic stress of the complete high-pressure turbine rotor of the double-rotor turbofan engine according to claim 8, wherein: the rear shaft of the high-pressure turbine is provided with a rear shaft assembly part (4), a third lead inclined hole (37) for extending a high-vortex disc test lead (7) is formed in the rear shaft assembly part (4), the angle between the third lead inclined hole (37) and a second lead inclined hole (34) is the same, the high-vortex disc test lead (7) extends out of the third lead inclined hole (37) and then is connected with a high-temperature strain gauge (46), a second belt-shaped boss structure (36) matched with the second belt-shaped boss structure (35) is arranged on the rear shaft assembly part (4), and an exhaust hole (38) capable of introducing cooling gas is formed in the rear shaft assembly part (4).
10. A birotor turbofan engine is characterized in that: comprising a high pressure turbine rotor dynamic stress testing device according to any of the claims 1-9.
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| CN202110814212.3A CN113565583B (en) | 2021-07-19 | 2021-07-19 | Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine |
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| CN114964787A (en) * | 2022-05-12 | 2022-08-30 | 中国航发沈阳发动机研究所 | Stress measurement structure for whole-machine low-vortex rotor blade of aero-engine |
| CN115950639A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for rotor blade of disk separation fan |
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| CN114964787A (en) * | 2022-05-12 | 2022-08-30 | 中国航发沈阳发动机研究所 | Stress measurement structure for whole-machine low-vortex rotor blade of aero-engine |
| CN114964787B (en) * | 2022-05-12 | 2023-09-22 | 中国航发沈阳发动机研究所 | Aeroengine complete machine low vortex rotor blade stress measurement structure |
| CN115950639A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for rotor blade of disk separation fan |
| CN115950639B (en) * | 2023-03-09 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for disc separation fan rotor blade |
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