A cooling device for the induction device used in the dynamic stress measurement test of an aircraft engine

Abstract

A charge air cooling device for an aircraft engine dynamic stress measurement test comprises: a charge air mounting plate; an intake pipe assembly mounted on the charge air mounting plate; a double-layer structure consisting of an intake pipe outer tube and an intake pipe inner tube; the through hole of the intake pipe inner tube forms a main air intake duct; a secondary air intake duct is formed between the intake pipe outer tube and the intake pipe inner tube; a charge air protection cover assembly mounted on the charge air mounting plate, a double-layer structure consisting of a protective cover outer tube and a protective cover inner tube; the inner cavity of the protective cover inner tube forms a first cavity; a second cavity is formed between the protective cover outer tube and the protective cover inner tube; exhaust ports are respectively provided on the first cavity and the second cavity; a first coupling is mounted on the axial center hole of the charge air mounting plate through a bearing; the charge air is arranged in the first cavity and connected to the first coupling; the main air intake duct is connected to the first cavity; the secondary air intake duct is connected to the second cavity; the measuring wire of the charge air passes through the first cavity and then exits from the main air intake duct.

Description

Technical Field

[0001] The present invention relates to a dynamic stress test technology for aircraft engine turbine blades, and in particular to a ignition device cooling device for aircraft engine dynamic stress measurement test, which is suitable for cooling the ignition device ambient temperature and special measurement wires in aircraft engine turbine dynamic stress measurement. Background Art

[0002] Currently, domestic testing for measuring dynamic stress in engine turbines primarily involves connecting wires to a fuse installed in a normal temperature zone. When this is not possible due to space or design requirements, the fuse must be placed in the tailpipe. Since the tailpipe temperature ranges from 700°C to 800°C during engine operation, the fuse's operating environment, along with the dedicated measurement wires and fuse cooling pipes, must be carefully designed to ensure a stable and reliable signal.

[0003] In the prior art, there are relevant documents that disclose related technologies for cooling the induction device. For example, the patent document with publication number CN206942878U discloses a new type of cooling device for testing, whose main structure includes: the end face on the other side of the installation edge is connected to a sleeve with a double-layer cylindrical wall through a welding seat, and is sealed by an end cover, so that a cavity is formed between the two layers of cylindrical walls, and another cavity is formed on the inner side of the inner layer of cylindrical wall. The outer side of the sleeve and the end cover are covered with a heat-insulating coating layer, and the water outlet pipe and the water inlet pipe pass through the heat-insulating coating layer to communicate with a cavity in the sleeve, while the air inlet pipe and the exhaust pipe are connected to the other cavity. The dual cooling working mode of water and air is adopted. The internal flowing cooling water can effectively prevent the heat generated by the high temperature field outside the device from being transferred to the inside of the device. On the other hand, the flowing cooling air can continuously cool the inside of the cooling device to ensure the normal operation of the induction device components.

[0004] However, when conducting engine turbine dynamic stress measurement tests, the fuse needs to be placed at the tail nozzle and requires synchronous rotation of the engine rotor. Since the tail nozzle temperature is maintained at 700°C to 800°C during engine operation, the operating temperature of the fuse, the dedicated measurement wires, and the fuse cooling pipe are high, making the fuse inoperable in this environment. Patent CN206942878U does not disclose how to install the fuse at the tail nozzle and ensure synchronous rotation of the fuse with the engine rotor, nor does it disclose how to lead the fuse's measurement wires out. Summary of the Invention

[0005] The main purpose of the present invention is to provide a cooling device for an electric lead used in a dynamic stress measurement test of an aero-engine, aiming to solve the above-mentioned technical problems.

[0006] To achieve the above-mentioned objectives, the present invention proposes a charge cooling device for an aircraft engine dynamic stress measurement test, comprising: a charge mounting plate; an intake pipe assembly, mounted on the charge mounting plate; the intake pipe assembly is a double-layer structure consisting of an intake pipe outer tube and an intake pipe inner tube; the through hole of the intake pipe inner tube forms a main air intake duct; the space between the intake pipe outer tube and the intake pipe inner tube forms an auxiliary air intake duct; a charge protection cover assembly, mounted on the charge mounting plate; the charge protection cover assembly is a double-layer structure consisting of a protective cover outer tube and a protective cover inner tube; the inner cavity of the protective cover inner tube forms a first cavity; a second cavity is formed between the protective cover outer tube and the protective cover inner tube; exhaust ports are respectively provided on the first cavity and the second cavity; a first coupling, mounted on the axial center hole of the charge mounting plate through a bearing; the charge is arranged in the first cavity and connected to the first coupling; the main air intake duct is connected to the first cavity; the auxiliary air intake duct is connected to the second cavity; the measuring wire of the charge passes through the first cavity and then exits from the main air intake duct.

[0007] Preferably, the axis of the main air inlet is perpendicular to the axis of the first cavity, and the axis of the first cavity coincides with the axis of the induction device mounting plate.

[0008] Preferably, the induction cooling device for aircraft engine dynamic stress measurement test also includes an isolation inner cylinder, the left end of which is connected to the induction mounting plate, the isolation inner cylinder is coaxially arranged on the outside of the protective cover outer cylinder, and the inner wall surface of the isolation inner cylinder is spaced apart from the outer wall surface of the protective cover outer cylinder.

[0009] Preferably, the induction cooling device for the dynamic stress measurement test of an aircraft engine also includes an outer cone, the left end of the outer cone is used to be connected to the engine tail nozzle, the outer cone is coaxially arranged on the outside of the isolation inner tube, and the inner wall surface of the outer cone and the outer surface of the isolation inner tube are spaced apart to form a gas annular flow channel; the outer end of the outer tube of the intake pipe is fixed to the outer cone, and the middle part of the outer tube of the intake pipe is fixed to the isolation inner tube.

[0010] Preferably, the intake pipe assembly also includes an intake head and an air bleed nut; one end of the air pipe outer tube and the intake pipe inner tube are jointly mounted on the intake head, and the other end are jointly mounted on the air bleed nut; a main air intake connector and multiple auxiliary air intake connectors are provided on the air intake head; the main air intake connector is connected to the main air intake duct; the auxiliary air intake connector is connected to the auxiliary air intake duct; a central through hole and multiple side holes evenly distributed around the central through hole are provided on the air bleed nut; an external threaded connection part is provided on the end of the air bleed nut; a first air bleed hole and a second air bleed hole are provided on the induction device mounting plate; an internal thread is provided at the mouth of the first air bleed hole; the first air bleed hole passes through the central hole of the induction device mounting plate; the external threaded connection part is screwed on the internal thread of the first air bleed hole, the central through hole is connected to the first air bleed hole, and the side hole is connected to the second air bleed hole.

[0011] Preferably, the induction device protection cover assembly also includes a connecting support ring and an end cover; one end of the protection cover outer tube and the protection cover inner tube are jointly installed on the connecting support ring, and the other end is jointly installed on the end cover; a first air inlet is provided in the center of the connecting support ring, and a plurality of second air inlets are evenly distributed around the first air inlet, the first air inlet is connected to the first cavity, and the second air inlet is connected to the second cavity; a threaded connection section is provided on the end face of the induction device mounting disk, and the internal thread of the first air inlet on the connecting support ring is screwed onto the threaded connection section; the first air inlet is connected to the center hole of the induction device mounting disk, and the second air inlet is connected to the second air inlet hole.

[0012] Preferably, a plurality of first through holes are evenly distributed near the center position of the end cover, and a plurality of second through holes are evenly distributed near the edge position of the end cover; the plurality of first through holes together form the exhaust port of the first cavity, and the plurality of second through holes together form the exhaust port of the second cavity.

[0013] Preferably, an air bleed branch hole is provided on the induction device mounting plate, the axis of the air bleed branch hole is perpendicular to the axis of the first air bleed hole, and the first air bleed hole is connected to the first air inlet through the air bleed branch hole.

[0014] Preferably, the number of the air intake pipe assemblies is four, and they are evenly distributed in a ring shape on the induction device mounting plate.

[0015] Preferably, the induction cooling device for aircraft engine dynamic stress measurement test also includes a second coupling, which is connected to the first coupling by a pin; a sealing ring is arranged between the first coupling and the axial center hole of the induction mounting plate, and the sealing ring is a rotating lip sealing ring.

[0016] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0017] (1) In the present invention, the air intake pipe assembly is a double-layer structure consisting of an air intake pipe outer tube and an air intake pipe inner tube, and the electric discharger protection cover assembly is a double-layer structure consisting of a protection cover outer tube and a protection cover inner tube. During the test, two cooling air paths are formed by dry compressed air cooling. The first cooling air path is that dry compressed air passes through the main air intake duct and enters the first cavity of the electric discharger protection cover assembly, and is then discharged from the exhaust port of the first cavity. The function of this cooling air path is to cool the measuring wires in the main air intake duct and the electric discharger arranged in the first cavity; the second cooling air path is that dry compressed air passes through the auxiliary air intake duct and enters the second cavity and is discharged from the exhaust port of the second cavity. The function of this cooling air path is to form a cooling interlayer between the auxiliary air intake duct of the air intake pipe assembly and the second cavity of the electric discharger protection cover assembly, so as to further cool the working environment temperature of the electric discharger and the working environment temperature of the measuring wires in the main air intake duct.

[0018] (2) In the present invention, when conducting the test, the induction device mounting plate is installed at the tail nozzle, and the induction device is set in the first cavity. The induction device can be connected to the rotor of the engine by using the first coupling, so that the induction device and the rotor rotate synchronously.

[0019] (3) In the present invention, the purpose of separating the high-temperature area of the tail nozzle and the working area of the fuse is achieved by utilizing the air intake pipe assembly and the fuse protection cover assembly. The measuring wire of the fuse passes through the first cavity and then out of the main air intake duct, and is then connected to the data acquisition equipment to ensure the stability of the turbine blade dynamic stress measurement signal output. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0021] Figure 1 This is a schematic structural diagram of the induction device cooling device for aero-engine dynamic stress measurement test provided by the present invention;

[0022] Figure 2 This is a schematic structural diagram of the air intake pipe assembly in the present invention;

[0023] Figure 3 This is a schematic diagram of the structure of the electrical installation plate of the present invention;

[0024] Figure 4 for Figure 3 CC rotated section view (without hatching);

[0025] Figure 5 for Figure 3 C2-C2 rotated sectional view (without hatching);

[0026] Figure 6 for Figure 3 C1-C1 rotated sectional view (without hatching);

[0027] Figure 7 It is a schematic diagram of the structure of the induction device protection cover assembly in the present invention.

[0028] Explanation of the reference numerals: 1. induction device; 2. screw; 3. sealing ring; 4. bearing; 5. first coupling; 6. second coupling; 7. pin; 8. induction device mounting plate; 8a. first air inlet hole; 8b. second air inlet hole; 8c. threaded connection section; 8d. air inlet branch hole; 9. air inlet pipe assembly; 9a. main air inlet duct; 9b. auxiliary air inlet duct; 10. isolation inner cylinder; 11. outer cone; 12. induction device protection cover assembly; 12a. first cavity; 1 2b, second cavity; 12c, connecting support ring; 12d, end cover; 13, main air intake connector; 14, auxiliary air intake connector; 15, air intake head; 16, outer tube of air intake pipe; 17, air bleed nut; 17a, central through hole; 17b, side hole; 17c, external threaded connection; 18, inner tube of air intake pipe; 19, inner tube of protective cover; 20, outer tube of protective cover; 21, second air inlet; 22, second through hole; 23, first through hole; 24, first air inlet. DETAILED DESCRIPTION

[0029] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0030] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0031] In addition, the descriptions of "first", "second", etc. in the present invention are for descriptive purposes only and should not be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of such features. In addition, the technical solutions between the various embodiments can be combined with each other, but this must be based on the fact that they can be implemented by ordinary technicians in this field. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0032] Combine Figure 1 、 Figure 2 as well as Figure 7As shown, a fuse cooling device for an aircraft engine dynamic stress measurement test comprises: a fuse mounting plate 8; an air intake pipe assembly 9, mounted on the fuse mounting plate 8; the air intake pipe assembly 9 is a double-layer structure consisting of an air intake pipe outer tube 16 and an air intake pipe inner tube 18; the through hole of the air intake pipe inner tube 18 forms a main air intake duct 9a; the space between the air intake pipe outer tube 16 and the air intake pipe inner tube 18 forms a secondary air intake duct 9b; a fuse protection cover assembly 12, mounted on the fuse mounting plate 8; the fuse protection cover assembly 12 is a double-layer structure consisting of a protection cover outer tube 20 and a protection cover inner tube 19; the protection cover The inner cavity of the inner tube 19 of the cover forms a first cavity 12a; a second cavity 12b is formed between the outer tube 20 of the protective cover and the inner tube 19 of the protective cover; exhaust ports are respectively provided on the first cavity 12a and the second cavity 12b; the first coupling 5 is mounted on the axial center hole of the induction device mounting plate 8 through the bearing 4; the induction device 1 is arranged in the first cavity 12a and is connected to the first coupling 5; the main air inlet duct 9a is connected to the first cavity 12a; the auxiliary air inlet duct 9b is connected to the second cavity 12b; the measuring wire of the induction device 1 passes through the first cavity 12a and then out of the main air inlet duct 9a.

[0033] Through the above structure, the intake pipe assembly 9 is a double-layer structure composed of the intake pipe outer tube 16 and the intake pipe inner tube 18, and the induction cover assembly 12 is a double-layer structure composed of the protection cover outer tube 20 and the protection cover inner tube 19. During the test, dry compressed air cooling is used to form two cooling air paths. The first cooling air path is that the dry compressed air passes through the main air intake duct 9a and enters the first cavity 12a of the induction cover assembly 12, and is then discharged from the exhaust port of the first cavity 12a. The function of this cooling air path is to cool the air in the main air intake duct 9a. The measuring wires are cooled, as is the fuse 1 located in the first cavity 12a. The first cooling air path involves dry compressed air entering the second cavity 12b through the secondary air inlet duct 9b and then being discharged from the exhaust port of the second cavity 12b. This cooling air path functions as a cooling barrier between the secondary air inlet duct 9b of the intake pipe assembly 9 and the second cavity 12b of the fuse protection cover assembly 12, creating a temperature partitioning effect to further cool the operating environment temperature of the fuse 1 and the measuring wires in the main air inlet duct 9a. This achieves a cooling effect by separating the high-temperature zone of the tail nozzle from the operating environment of the fuse 1, and separating the temperature of the high-temperature zone of the tail nozzle from the distribution area of the measuring wires.

[0034] Combine Figure 1As shown, the axis of the main air inlet 9a is perpendicular to the axis of the first cavity 12a, and the axis of the first cavity 12a coincides with the axis center line of the induction device mounting disk 8. This ensures that after the induction device 1 is installed, the axial direction of the induction device 1 coincides with the axis center line of the induction device mounting disk 8, thereby facilitating the induction device 1 to be connected to the engine rotor through the first coupling 5, thereby realizing synchronous rotation of the induction device 1 and the engine rotor.

[0035] Combine Figure 1 As shown, the ignition device cooling device for aircraft engine dynamic stress measurement tests also includes an isolation inner tube 10, the left end of which is connected to the ignition device mounting plate 8. The isolation inner tube 10 is coaxially arranged outside the protective cover outer tube 20, with a gap between the inner wall of the isolation inner tube 10 and the outer wall of the protective cover outer tube 20. The isolation inner tube 10 can serve as a partition and flow diversion device. Specifically, the high-temperature gas ejected from the tail nozzle is discharged rearward along the isolation inner tube 10, thereby reducing heat exchange between the high-temperature gas ejected from the tail nozzle and the protective cover outer tube 20. Furthermore, the ignition device cooling device for aircraft engine dynamic stress measurement tests also includes an outer cone 11, the left end of which is used to connect to the engine tail nozzle. The outer cone 11 is coaxially arranged outside the isolation inner tube 10, with a gap between the inner wall of the outer cone 11 and the outer surface of the isolation inner tube 10 to form a gas annular flow channel. The high-temperature gas ejected from the tail nozzle is directly discharged rearward along this gas annular flow channel, which further serves to divert the gas. In addition, the outer end of the intake pipe outer tube 16 is fixed to the outer cone 11, and the middle part of the intake pipe outer tube 16 is fixed to the isolation inner tube 10. The outer cone 11 and the isolation inner tube 10 can be used to install and fix the intake pipe assembly 9.

[0036] Combine Figure 2 、 Figure 5As shown, the intake pipe assembly 9 also includes an intake head 15 and an air bleed nut 17; one end of the trachea outer tube 16 and the intake pipe inner tube 18 are mounted on the intake head 15, and the other end is mounted on the air bleed nut 17; a main intake joint 13 and multiple auxiliary intake joints 14 are provided on the intake head 15; the main intake joint 13 is connected to the main intake duct 9a; the auxiliary intake joint 14 is connected to the auxiliary intake duct 9b; a central through hole 17a is provided on the air bleed nut 17, and air bleed nut 17 is evenly distributed on the central through hole. Multiple side holes 17b are arranged around the inlet nut 17a; an externally threaded connection portion 17c is provided at the end of the inlet nut 17; a first air inlet hole 8a and a second air inlet hole 8b are provided on the inlet duct mounting plate 8; the mouth of the first air inlet hole 8a is provided with an internal thread; the first air inlet hole 8a extends through the center hole of the inlet duct mounting plate 8; the externally threaded connection portion 17c is screwed onto the internal thread of the first air inlet hole 8a, the center through hole 17a is in communication with the first air inlet hole 8a, and the side hole 17b is in communication with the second air inlet hole 8b. The air inlet head 15 and the air inlet nut 17 are used to install the air pipe outer tube 16 and the air pipe inner tube 18, ensuring that they are coaxially arranged to facilitate the annular gap of the auxiliary air inlet duct 9b. In addition, the air inlet head 15 is also used to install the main air inlet connector 13 and the auxiliary air inlet connector 14 to facilitate connection to the cooling gas pipeline. The main function of the air bleed nut 17 is to install the air pipe outer tube 16, the air intake pipe inner tube 18, and to connect the air intake pipe assembly 9 to the bleeder mounting plate 8.

[0037] Combine Figure 5 、 Figure 7 As shown, the induction device protection cover assembly 12 also includes a connecting support ring 12c and an end cover 12d; one end of the protection cover outer tube 20 and the protection cover inner tube 19 are jointly installed on the connecting support ring 12c, and the other end is jointly installed on the end cover 12d; a first air inlet 24 is provided in the center of the connecting support ring 12c, and a plurality of second air inlets 21 are evenly distributed around the first air inlet 24, the first air inlet 24 is connected to the first cavity 12a, and the second air inlet 21 is connected to the second cavity 12b; a threaded connection section 8c is provided on the end face of the induction device mounting disk 8, and the internal thread of the first air inlet 24 on the connecting support ring 12c is screwed onto the threaded connection section 8c; the first air inlet 24 is connected to the center hole of the induction device mounting disk 8, and the second air inlet 21 is connected to the second air inlet hole 8b.

[0038] Combine Figure 7 As shown, a plurality of first through holes 23 are evenly distributed near the center position of the end cover 12d, and a plurality of second through holes 22 are evenly distributed near the edge position of the end cover 12d; the plurality of first through holes 23 together form the exhaust port of the first cavity 12a, and the plurality of second through holes 22 together form the exhaust port of the second cavity 12b.

[0039] Combine Figure 5As shown, an air branch hole 8d is provided on the induction device mounting plate 8. The axis of the air branch hole 8d is perpendicular to the axis of the first air hole 8a. The first air hole 8a is connected to the first air inlet 24 through the air branch hole 8d. The purpose of providing the air branch hole 8d is to increase the area between the first air hole 8a and the first air inlet 24, further increasing the amount of air intake.

[0040] Combine Figure 3 、 Figure 5 As shown, four groups of first air inlet holes 8a and second air inlet holes 8b are provided on the induction device mounting plate 8. Correspondingly, the number of the air intake pipe assemblies 9 is four, which are evenly distributed in a ring shape on the induction device mounting plate 8. The purpose of setting four air intake pipe assemblies 9 is to increase the air intake volume and provide a cooling effect.

[0041] Combine Figure 1 As shown, the fuse cooling device for the aircraft engine dynamic stress measurement test also includes a second coupling 6, which is connected to the first coupling 5 by a pin 7; a sealing ring 3 is provided between the first coupling 5 and the axial center hole of the fuse mounting plate 8, and the sealing ring 3 is a rotating lip sealing ring. In actual use, the first coupling 5 is installed on the fuse mounting plate 8, and the second coupling 6 is connected to the rotor of the engine. The first coupling 5 and the second coupling 6 are used to realize the connection transmission. Therefore, the first coupling 5 and the second coupling 6 can be set as an interface of uniform specifications to facilitate the connection between the two. When testing different tail nozzles, there is no need to disassemble and replace the first coupling 5.

[0042] The above description is only a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformation made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields, is included in the patent protection scope of the present invention.

Claims

1. A cooling device for an electric lead used in aero-engine dynamic stress measurement test, characterized in that: include: Induction device mounting plate (8); An air intake pipe assembly (9) is mounted on the induction device mounting plate (8); the air intake pipe assembly (9) is a double-layer structure consisting of an air intake pipe outer tube (16) and an air intake pipe inner tube (18); the through hole of the air intake pipe inner tube (18) forms a main air intake passage (9a); and the space between the air intake pipe outer tube (16) and the air intake pipe inner tube (18) forms a secondary air intake passage (9b); The induction device protection cover assembly (12) is mounted on the induction device mounting plate (8); the induction device protection cover assembly (12) is a double-layer structure consisting of an outer protection cover tube (20) and an inner protection cover tube (19); the inner cavity of the inner protection cover tube (19) forms a first cavity (12a); a second cavity (12b) is formed between the outer protection cover tube (20) and the inner protection cover tube (19); exhaust ports are respectively provided on the first cavity (12a) and the second cavity (12b); A first coupling (5) is mounted on the axial center hole of the induction device mounting plate (8) via a bearing (4); A current inducer (1) is disposed in the first cavity (12a) and connected to the first coupling (5); The main air inlet (9a) is in communication with the first cavity (12a); the auxiliary air inlet (9b) is in communication with the second cavity (12b); and the measuring wire of the induction device (1) passes through the first cavity (12a) and then exits from the main air inlet (9a).

2. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 1, characterized in that: The axis of the main air inlet (9a) is perpendicular to the axis of the first cavity (12a), and the axis of the first cavity (12a) coincides with the axis of the induction device mounting plate (8).

3. The cooling device for the lead for dynamic stress measurement test of an aircraft engine according to claim 1, characterized in that: The device further comprises an isolation inner cylinder (10), the left end of which is connected to the induction device mounting plate (8), the isolation inner cylinder (10) being coaxially arranged on the outside of the protective cover outer cylinder (20), and the inner wall surface of the isolation inner cylinder (10) and the outer wall surface of the protective cover outer cylinder (20) being spaced apart.

4. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 3, characterized in that: The invention also includes an outer cone (11), the left end of which is used to connect to the tail nozzle of the engine. The outer cone (11) is coaxially arranged on the outside of the isolation inner cylinder (10), and the inner wall surface of the outer cone (11) and the outer surface of the isolation inner cylinder (10) are spaced apart to form a gas annular flow channel; the outer end of the intake pipe outer cylinder (16) is fixedly connected to the outer cone (11), and the middle part of the intake pipe outer cylinder (16) is fixedly connected to the isolation inner cylinder (10).

5. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 1, characterized in that: The air intake pipe assembly (9) further comprises an air intake head (15) and an air introduction nut (17); One end of the trachea outer tube (16) and the air intake inner tube (18) are mounted on the air intake head (15), and the other end are mounted on the air inlet nut (17); A main air intake connector (13) and a plurality of auxiliary air intake connectors (14) are provided on the air intake head (15); the main air intake connector (13) is connected to the main air intake passage (9a); the auxiliary air intake connector (14) is connected to the auxiliary air intake passage (9b); The nut (17) is provided with a central through hole (17a) and a plurality of side holes (17b) uniformly distributed around the central through hole (17a); the end of the nut (17) is provided with an external thread connection portion (17c); A first air inlet hole (8a) and a second air inlet hole (8b) are provided on the induction device mounting plate (8); an internal thread is provided at the mouth of the first air inlet hole (8a); the first air inlet hole (8a) penetrates to the center hole of the induction device mounting plate (8); The external thread connection portion (17c) is screwed onto the internal thread of the first air inlet hole (8a), the central through hole (17a) is in communication with the first air inlet hole (8a), and the side hole (17b) is in communication with the second air inlet hole (8b).

6. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 5, characterized in that: The current inductor protection cover assembly (12) further includes a connecting support ring (12c) and an end cover (12d); One end of the protective cover outer cylinder (20) and the protective cover inner cylinder (19) are mounted on the connecting support ring (12c), and the other end are mounted on the end cover (12d). A first air inlet (24) is provided at the center of the connecting support ring (12c), and a plurality of second air inlets (21) are evenly distributed around the first air inlet (24), the first air inlet (24) is communicated with the first cavity (12a), and the second air inlet (21) is communicated with the second cavity (12b); A threaded connection section (8c) is provided on the end surface of the induction device mounting plate (8), and the internal thread of the first air inlet (24) on the connecting support ring (12c) is screwed onto the threaded connection section (8c); the first air inlet (24) is in communication with the central hole of the induction device mounting plate (8), and the second air inlet (21) is in communication with the second air inlet hole (8b).

7. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 6, characterized in that: A plurality of first through holes (23) are evenly distributed near the center of the end cover (12d), and a plurality of second through holes (22) are evenly distributed near the edge of the end cover (12d); the plurality of first through holes (23) together form an exhaust port of the first cavity (12a), and the plurality of second through holes (22) together form an exhaust port of the second cavity (12b).

8. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 6, characterized in that: An air inlet branch hole (8d) is provided on the inlet device mounting plate (8), the axis of the air inlet branch hole (8d) is perpendicular to the axis of the first air inlet hole (8a), and the first air inlet hole (8a) is connected to the first air inlet (24) through the air inlet branch hole (8d).

9. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 1, characterized in that: The number of the air intake pipe assemblies (9) is four, and they are evenly distributed in an annular shape on the induction device mounting plate (8).

10. The induction device cooling device for aero-engine dynamic stress measurement test according to claim 1, characterized in that: The invention also includes a second coupling (6), which is connected to the first coupling (5) via a pin (7); a sealing ring (3) is provided between the first coupling (5) and the axial center hole of the induction device mounting plate (8), and the sealing ring (3) is a rotating lip sealing ring.

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