A test rig for aeroengine bore sight test simulation

Abstract

The application discloses a tester for aero-engine bore test simulation, and relates to the technical field of aero-engine bore test, which comprises a test support and a tester module, wherein the tester module comprises an outer casing, an inner casing, a rotating shaft, a low-pressure compressor supporting stator, a three-stage low-pressure compressor disc, a high-pressure compressor supporting stator, a four-stage high-pressure compressor disc, a three-stage turbine disc and a turbine supporting stator which are sequentially arranged on the rotating shaft; and blade mounting seats are arranged on the three-stage low-pressure compressor disc, the four-stage high-pressure compressor disc and the three-stage turbine disc. The tester can simulate the aero-engine bore environment under a real environment, clamp various numbers and types of damaged blades, meet the aero-engine blade damage preparation and bore simulation test, solve the problems of the development and test of bore test equipment and the lack of secondary development of real machines, and is beneficial to the research of bore detection technology.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine bore test, in particular to a tester for aero-engine bore test simulation. BACKGROUND

[0002] An aero-engine is the main power source for a plane to fly. Since it works in a high-temperature, high-pressure and high-vibration environment for a long time, and a high-bypass-ratio turbofan engine is prone to sucking in stones, parts left by a plane, birds and other foreign objects near a runway and taxiway during the process of takeoff, landing and taxiing of the plane, the aero-engine is prone to failure. Serious engine failure will cause engine surge or parking in the air, which poses a great threat to flight safety. Regular inspection of the engine or visual maintenance after an emergency can ensure the continuous airworthiness of the plane, improve the daily utilization rate of the plane, save maintenance costs and increase the economic benefits of an airline. Internal component and structural damage is an important cause of failure of the aero-engine, and internal damage of the engine is usually detected by a non-destructive testing method. Common non-destructive testing methods include magnetic powder detection, penetration detection, eddy current detection, ultrasonic detection, ray detection and bore test (endoscopy). The bore test is the most widely used non-destructive testing method in the maintenance of the aero-engine at present due to its rapidity and convenience, and scholars at home and abroad have also conducted in-depth research on the bore test technology. However, the research results are difficult to apply to engineering practice. An important reason is the lack of corresponding aero-engine bore test verification. A real aero-engine is extremely expensive and the internal core engine is difficult to disassemble and customize, so it is extremely important to design and manufacture an aero-engine simulation tester that can meet the bore test research.

[0003] However, the existing aero-engine bore test research device has one or several of the following deficiencies: no casing, only engine rotor part or no stator blade part; no real aero-engine core engine basic structure, only simple structure such as a blade disc; blade and blade disc integration, which cannot replace and preform defects on the blade; position limitation between the casing and the rotor, which is not convenient for bore test equipment to take bore test photos; bore test environment is not real enough, which cannot simulate the actual defect detection environment well; the types of installable blades and the relative positions are single; and the like. Thus, the bore test device has great limitations in bore test use. SUMMARY

[0004] The present application aims to provide a tester for aero-engine bore test simulation to solve the problems in the prior art, simulate bore test environments that are more consistent with the real environments of various aero-engines, meet aero-engine blade damage preformation and bore test simulation, and reduce the limitations of bore test.

[0005] To achieve the above object, the present application provides the following solutions:

[0006] The application provides a tester for aero-engine bore test simulation, which comprises a test support and a tester module; the tester module is consistent with the size and shape of an aero-engine after removing the combustion chamber and the last three high-pressure compressors; the tester module comprises an outer casing, an inner casing, a rotating shaft, a low-pressure compressor supporting stator, a three-stage low-pressure compressor disc, a high-pressure compressor supporting stator, a four-stage high-pressure compressor disc, a three-stage turbine disc and a turbine supporting stator; the outer casing is fixedly arranged on the test support, the inner casing is sleeved in the outer casing, and the inner casing is sleeved outside the rotating shaft; a plurality of bore test holes consistent with those on the real machine are arranged on the corresponding positions of the outer casing and the inner casing; the low-pressure compressor supporting stator, the high-pressure compressor supporting stator and the turbine supporting stator are fixedly arranged in the outer casing and are sequentially arranged on the rotating shaft in a rotating mode around the axis of the rotating shaft; the three-stage low-pressure compressor disc is fixedly arranged on the rotating shaft between the low-pressure compressor supporting stator and the high-pressure compressor supporting stator; the four-stage high-pressure compressor disc and the three-stage turbine disc are sequentially fixedly arranged on the rotating shaft between the high-pressure compressor supporting stator and the turbine supporting stator, the four-stage high-pressure compressor disc is located on the side of the three-stage turbine disc close to the three-stage low-pressure compressor disc, and the four-stage high-pressure compressor disc and the three-stage turbine disc are both located in the inner casing; the three-stage low-pressure compressor disc, the four-stage high-pressure compressor disc and the three-stage turbine disc can be adjusted in position along the axis direction of the rotating shaft and keep the adjusted relative position; blade mounting seats are arranged on the circumferential sidewalls of the three-stage low-pressure compressor disc, the four-stage high-pressure compressor disc and the three-stage turbine disc, and corresponding blades are fixedly connected to the blade mounting seats, and the position and shape of each stage of blades are consistent with those of the real machine.

[0007] Preferably, the three-stage low-pressure compressor disc comprises a low-pressure first-stage compressor disc, a low-pressure second-stage compressor disc and a low-pressure third-stage compressor disc fixedly arranged on the rotating shaft in sequence, the low-pressure first-stage compressor disc is close to the low-pressure compressor supporting stator at the end far from the low-pressure second-stage compressor disc; the four-stage high-pressure compressor disc comprises a high-pressure first-stage compressor disc, a high-pressure second-stage compressor disc, a high-pressure third-stage compressor disc and a high-pressure fourth-stage compressor disc fixedly arranged on the rotating shaft in sequence, the high-pressure first-stage compressor disc is close to the high-pressure compressor supporting stator at the end far from the high-pressure second-stage compressor disc; the three-stage turbine disc comprises a high-pressure turbine disc, a low-pressure first-stage turbine disc and a low-pressure second-stage turbine disc fixedly arranged on the rotating shaft in sequence, the high-pressure turbine disc is close to the high-pressure compressor supporting stator at the end far from the low-pressure first-stage turbine disc; sleeves for separating the stages are arranged between the three-stage low-pressure compressor disc, between the four-stage high-pressure compressor disc and between the three-stage turbine disc, and the sleeves are fixedly connected with the rotating shaft.

[0008] Preferably, the high-pressure compressor supporting stator is fixedly connected with the inner wall of the outer casing through a plurality of high-pressure compressor spoke plates fixed on the circumferential side wall; the turbine supporting stator is fixedly connected with the inner wall of the outer casing through a plurality of turbine spoke plates fixed on the circumferential side wall; the inner casing is a complete quarter; one end of the inner casing is fixedly connected with at least one high-pressure compressor spoke plate, and the other end of the inner casing is fixedly connected with at least one turbine spoke plate.

[0009] Preferably, a first adjusting long hole is arranged on the high-pressure compressor spoke plate, and a second adjusting long hole is arranged on the turbine spoke plate; the extending directions of the first adjusting long hole and the second adjusting long hole are parallel to the radial direction of the outer casing; a first fixing hole is arranged on one end of the inner casing, and a second fixing hole is arranged on the other end of the inner casing; the first fixing hole corresponds to the first adjusting long hole and is provided with a first fastener; the second fixing hole corresponds to the second adjusting long hole and is provided with a second fastener.

[0010] Preferably, the outer casing, the low-pressure compressor supporting stator, the high-pressure compressor supporting stator and the turbine supporting stator are all composed of upper and lower half structures; the upper half of the outer casing is detachably connected with the lower half of the outer casing; the upper half of the low-pressure compressor supporting stator, the upper half of the high-pressure compressor supporting stator and the upper half of the turbine supporting stator are fixedly connected with the upper half of the outer casing; the lower half of the low-pressure compressor supporting stator, the lower half of the high-pressure compressor supporting stator, the lower half of the turbine supporting stator and the inner casing are fixedly connected with the lower half of the outer casing, and the lower half of the outer casing is fixedly connected with the test support.

[0011] Preferably, the blade mounting seat comprises a first side ring plate, a second side ring plate, a first long supporting screw rod, a second long supporting screw rod, a first side pressure connecting bolt and a second side pressure connecting bolt; the first side ring plate and the second side ring plate are arranged in parallel and fixed in position; a plurality of groups of corresponding inner supporting threaded holes and side pressure connecting threaded holes are arranged on the first side ring plate and the second side ring plate in a circumferential direction; the first long supporting screw rod and the second long supporting screw rod are arranged in parallel, and the first long supporting screw rod and the second long supporting screw rod are respectively threaded into two corresponding inner supporting threaded holes; the tenon of the blade is inserted between the first long supporting screw rod and the second long supporting screw rod; the positions of the two sides of the tenon of the blade close to the first side ring plate and the second side ring plate are respectively correspondingly abutted by the first side pressure connecting bolt and the second side pressure connecting bolt, the first side pressure connecting bolt is threaded into the side pressure connecting threaded hole of the first side ring plate, and the second side pressure connecting bolt is threaded into the side pressure connecting threaded hole of the second side ring plate.

[0012] Preferably, the blade mounting seat further comprises two side locking plates, each of the side locking plates corresponds to the first side pressure connecting bolt and the second side pressure connecting bolt; the lower end of the side locking plate is fixedly connected with the first side pressure connecting bolt or the second side pressure connecting bolt, and the upper end of the side locking plate is planarly connected on the upper surface of the corresponding side of the base above the tenon of the blade.

[0013] Preferably, one end of the rotating shaft is fixedly provided with a first flange plate, and the first flange plate is fixedly provided with a rotating handle.

[0014] Preferably, the other end of the rotating shaft away from the first flange plate is fixedly provided with a second flange plate, and the second flange plate is sequentially fixedly connected with a shaft coupling, a driving motor and a speed reducer mechanism; a motor support is fixedly arranged below the driving motor and the speed reducer mechanism.

[0015] Preferably, the sleeve is composed of two halves, and one half of the sleeve is detachably connected with the other half of the sleeve.

[0016] The present application has the following technical effects compared with the prior art:

[0017] The test device for aero-engine bore test simulation provided by the application can simulate the real engine blade damage environment of the third low-pressure, the first four high-pressure, the second high-pressure stator and the third turbine bore by setting the test device including an outer casing, an inner casing, a rotating shaft, a low-pressure compressor support stator, a three-stage low-pressure compressor disc, a high-pressure compressor support stator, a four-stage high-pressure compressor disc, a three-stage turbine disc and a turbine support stator, and the size and shape of the test device are consistent with those of the real engine without a combustion chamber and the third high-pressure compressor; various types of tenon blades can be installed on the blade mounting seat; the positions of the three-stage low-pressure compressor disc, the four-stage high-pressure compressor disc and the three-stage turbine disc on the rotating shaft are adjustable, and various real engine bore environments can be simulated, so that the blade damage preparation and bore simulation test of the aero-engine are met, the development and test of the bore test equipment and the lack of real engine in secondary development are solved, the bore detection technology is beneficial to research, and the limitation of bore test is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor based on these drawings.

[0019] Figure 1 The overall structure schematic diagram of the test device for aero-engine bore test simulation provided by the application is shown in the figure.

[0020] Figure 2 The internal structure schematic diagram of the test device module in the test device for aero-engine bore test simulation provided by the application is shown in the figure.

[0021] Figure 3 The structure schematic diagram of the three-stage low-pressure compressor disc, the four-stage high-pressure compressor disc and the three-stage turbine disc on the rotating shaft in the test device for aero-engine bore test simulation provided by the application is shown in the figure.

[0022] Figure 4 The structure schematic diagram of the inner casing and the outer casing in the test device for aero-engine bore test simulation provided by the application is shown in the figure.

[0023] Figure 5 The structure schematic diagram of the blade mounting seat in the test device for aero-engine bore test simulation provided by the application is shown in the figure.

[0024] Figure 6 The structure schematic diagram of the framework of the test device for aero-engine bore test simulation provided by the application is shown in the figure.

[0025] In the figure:

[0026] 10-test support;

[0027] 20-tester module; 21-outer casing; 211-hole probe hole; 22-inner casing; 23-rotary shaft; 231-first flange plate; 232-rotary handle; 233-second flange plate; 24-low-pressure compressor support stator; 25-four-stage low-pressure compressor disk; 251-low-pressure first-stage compressor rotor disk; 252-low-pressure second-stage compressor rotor disk; 253-low-pressure third-stage compressor rotor disk; 26-high-pressure compressor support stator; 261-high-pressure compressor spider; 262-first adjusting long hole; 27-four-stage high-pressure compressor disk; 271-high-pressure first-stage compressor rotor disk; 272-high-pressure second-stage compressor rotor disk; 273-high-pressure third-stage compressor rotor disk; 274-high-pressure four-stage compressor rotor disk; 28-three-stage turbine disk; 281-high-pressure turbine rotor disk; 282-low-pressure first-stage turbine rotor disk; 283-low-pressure second-stage turbine rotor disk; 29-turbine support stator; 291-turbine spider; 292-second adjusting long hole;

[0028] 30-blade mounting seat; 31-first side ring plate; 32-second side ring plate; 33-first long support screw; 34-second long support screw; 35-first side press-fit bolt; 36-second side press-fit bolt; 37-side locking plate;

[0029] 40-sleeve;

[0030] 50-coupling;

[0031] 60-driving motor and reduction box mechanism; 61-motor support. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0033] The present application aims to provide a tester for aero-engine hole probe test simulation, to solve the problems in the prior art, to simulate hole probe environments more close to real environments of various aero-engines, to meet aero-engine blade damage preparation and hole probe simulation test, and to reduce the limitations of hole probe test.

[0034] To make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail below with reference to the drawings and specific embodiments. EMBODIMENT

[0035] The embodiment provides a tester for aero-engine bore test simulation, which comprises a test support 10 and a tester module 20, as shown in the figure. Figures 1-6 The tester module 20 is consistent with the size and shape of an aero-engine true machine after removing a combustion chamber and a three-stage high-pressure compressor; the tester module 20 comprises an outer casing 21, an inner casing 22, a rotating shaft 23, a low-pressure compressor supporting stator 24, a three-stage low-pressure compressor disc 25, a high-pressure compressor supporting stator 26, a four-stage high-pressure compressor disc 27, a three-stage turbine disc 28 and a turbine supporting stator 29; the outer casing 21 is fixedly arranged on the test support 10, the inner casing 22 is arranged in the outer casing 21, and the inner casing 22 is arranged outside the rotating shaft 23; a plurality of bore test holes 211 (which are used for inserting a probe of a bore test instrument) consistent with those of the true machine are arranged on the corresponding positions of the outer casing 21 and the inner casing 22; the low-pressure compressor supporting stator 24, the high-pressure compressor supporting stator 26 and the turbine supporting stator 29 are fixedly arranged in the outer casing 21 and are sequentially arranged on the rotating shaft 23 in a rotating manner around the axis of the rotating shaft 23; the three-stage low-pressure compressor disc 25 is fixedly arranged on the rotating shaft 23 between the low-pressure compressor supporting stator 24 and the high-pressure compressor supporting stator 26; the four-stage high-pressure compressor disc 27 and the three-stage turbine disc 28 are sequentially fixedly arranged on the rotating shaft 23 between the high-pressure compressor supporting stator 26 and the turbine supporting stator 29, the four-stage high-pressure compressor disc 27 is located on the side of the three-stage turbine disc 28 close to the three-stage low-pressure compressor disc 25, and the four-stage high-pressure compressor disc 27 and the three-stage turbine disc 28 are located in the inner casing 22; the three-stage low-pressure compressor disc 25, the four-stage high-pressure compressor disc 27 and the three-stage turbine disc 28 can be adjusted in position along the axis direction of the rotating shaft 23 and keep the adjusted relative positions; the blade mounting seat 30 is arranged on the circumferential side wall of the three-stage low-pressure compressor disc 25, the four-stage high-pressure compressor disc 27 and the three-stage turbine disc 28, the corresponding blades are fixedly connected to the blade mounting seat 30, and the positions and shapes of the blades are consistent with those of the true machine.

[0036] The tester, which includes an outer casing 21, an inner casing 22, a rotating shaft 23, a low-pressure compressor support stator 24, a third-stage low-pressure compressor disk 25, a high-pressure compressor support stator 26, a fourth-stage high-pressure compressor disk 27, a third-stage turbine disk 28, and a turbine support stator 29, can simulate the borehole exploration environment of a real engine, where blade damage primarily occurs, including the third-stage low-pressure, first four-stage high-pressure, high-pressure second-stage stators, and third-stage turbine. The tester is identical in size and shape to a real engine, minus the combustion chamber and the third-stage high-pressure compressor. Blades of various tenon types can be installed via a blade mounting seat 30. The positions of the third-stage low-pressure compressor disk 25, fourth-stage high-pressure compressor disk 27, and third-stage turbine disk 28 on the rotating shaft 23 are adjustable, simulating various real-world borehole exploration environments of engines. This satisfies the requirements for prefabrication and borehole exploration simulation testing of aircraft engine blade damage, addresses the lack of real engines in the development, testing, and secondary development of borehole exploration testing equipment, and is beneficial to the research of borehole exploration testing technology and reduces the limitations of borehole exploration testing.

[0037] The internal structure of the tester module 20 is as follows:

[0038] Among the optional solutions of this embodiment, it is more preferred that Figure 2 and Figure 3 As shown, the three-stage low-pressure compressor disc 25 includes a low-pressure first-stage compressor disc 251, a low-pressure second-stage compressor disc 252, and a low-pressure third-stage compressor disc 253, which are sequentially fixed on the rotating shaft 23. The end of the low-pressure first-stage compressor disc 251 away from the low-pressure second-stage compressor disc 252 is close to the low-pressure compressor support stator 24. The four-stage high-pressure compressor disc 27 includes a high-pressure first-stage compressor disc 271, a high-pressure second-stage compressor disc 272, a high-pressure third-stage compressor disc 273, and a high-pressure fourth-stage compressor disc 274, which are sequentially fixed on the rotating shaft 23. The end of 271 away from the high-pressure second-stage compressor turntable 272 is close to the high-pressure compressor support stator 26; the three-stage turbine disk 28 includes a high-pressure turbine turntable 281, a low-pressure first-stage turbine turntable 282 and a low-pressure second-stage turbine turntable 283 fixedly arranged on the rotating shaft 23 in sequence, and the end of the high-pressure turbine turntable 281 away from the low-pressure first-stage turbine turntable 282 is close to the high-pressure compressor support stator 26; sleeves 40 for separating the stages are sandwiched between the three-stage low-pressure compressor disks 25, between the four-stage high-pressure compressor disks 27 and between the three-stage turbine disks 28, and the sleeves 40 are fixedly connected to the rotating shaft 23.

[0039] Specifically, the low-pressure first-stage compressor turntable 251, the low-pressure second-stage compressor turntable 252, the low-pressure third-stage compressor turntable 253, the high-pressure first-stage compressor turntable 271, the high-pressure second-stage compressor turntable 272, the high-pressure third-stage compressor turntable 273, the high-pressure fourth-stage compressor turntable 274, the high-pressure turbine turntable 281, the low-pressure first-stage turbine turntable 282 and the low-pressure second-stage turbine turntable 283 can be opened with weight-reducing holes.

[0040] Among them, the relevant setting instructions about the inner casing 22 are as follows:

[0041] Among the optional solutions of this embodiment, it is more preferred that Figure 2 and Figure 4 As shown, the high-pressure compressor support stator 26 is fixedly connected to the inner wall of the outer casing 21 through a plurality of high-pressure compressor spokes 261 fixed on the circumferential side wall; the turbine support stator 29 is fixedly connected to the inner wall of the outer casing 21 through a plurality of turbine spokes 291 fixed on the circumferential side wall; the inner casing 22 is one-fourth of the complete body; one end of the inner casing 22 is fixedly connected to at least one high-pressure compressor spoke 261, and the other end of the inner casing 22 is fixedly connected to at least one turbine spoke 291.

[0042] Specifically, two ends of the inner casing 22 are fixedly connected to the two high-pressure compressor spokes 261 and the two turbine spokes 291 respectively.

[0043] Among the optional solutions of this embodiment, it is more preferred that Figure 2 and Figure 4 As shown, a first adjustment long hole 262 is provided on the high-pressure compressor spoke 261, and a second adjustment long hole 292 is provided on the turbine spoke 291; the extension direction of the first adjustment long hole 262 and the second adjustment long hole 292 is parallel to the radial direction of the outer casing 21; a first fixing hole is provided at one end of the inner casing 22, and a second fixing hole is provided at the other end; the first fixing hole corresponds to the first adjustment long hole 262 and is penetrated by a first fastener; the second fixing hole corresponds to the second adjustment long hole 292 and is penetrated by a second fastener.

[0044] Specifically, the first fastener and the second fastener may both be a bolt-nut combination.

[0045] Among them, the relevant setting instructions for the blade mounting seat 30 are as follows:

[0046] Among the optional solutions of this embodiment, it is more preferred that Figure 5As shown, the blade mounting seat 30 comprises a first side ring plate 31, a second side ring plate 32, a first long support screw 33, a second long support screw 34, a first side pressure connecting bolt 35 and a second side pressure connecting bolt 36; the first side ring plate 31 and the second side ring plate 32 are arranged in parallel and fixed in position; a plurality of groups of inner support threaded holes and side pressure connecting threaded holes corresponding to each other are arranged circumferentially on the first side ring plate 31 and the second side ring plate 32; the first long support screw 33 and the second long support screw 34 are arranged in parallel, and the first long support screw 33 and the second long support screw 34 are respectively threaded into the two inner support threaded holes corresponding to each other; the tenon of the blade is inserted between the first long support screw 33 and the second long support screw 34; the positions of the two sides of the tenon of the blade close to the first side ring plate 31 and the second side ring plate 32 are respectively correspondingly abutted by the first side pressure connecting bolt 35 and the second side pressure connecting bolt 36, the first side pressure connecting bolt 35 is threaded into the side pressure connecting threaded hole of the first side ring plate 31, and the second side pressure connecting bolt 36 is threaded into the side pressure connecting threaded hole of the second side ring plate 32.

[0047] Specifically, taking the low-pressure first-stage compressor rotating disc 251 as an example, the first side ring plate 31 and the second side ring plate 32 are respectively fixedly arranged on the two sides of the low-pressure first-stage compressor rotating disc 251, and the outer diameters of the first side ring plate 31 and the second side ring plate 32 are the same.

[0048] In the optional solution of the embodiment, preferably, as shown in the figure, Figure 5 As shown, the blade mounting seat 30 further comprises two side locking plates 37, each of which corresponds to the first side pressure connecting bolt 35 and the second side pressure connecting bolt 36; the lower end of the side locking plate 37 is fixedly connected with the first side pressure connecting bolt 35 or the second side pressure connecting bolt 36, and the upper end of the side locking plate 37 is planarly connected on the upper surface of the corresponding side of the base (the bottom of the blade is fixedly connected with the base, and the tenon is fixedly arranged below the base) above the tenon of the blade.

[0049] Among them, the other related settings are as follows:

[0050] In the optional solution of the embodiment, preferably, as shown in the figure, Figure 1 As shown, the outer casing 21, the low-pressure compressor supporting stator 24, the high-pressure compressor supporting stator 26 and the turbine supporting stator 29 are all composed of upper and lower half structures; the upper half of the outer casing 21 is detachably connected with the lower half of the outer casing 21; the upper half of the low-pressure compressor supporting stator 24, the high-pressure compressor supporting stator 26 and the turbine supporting stator 29 are fixedly connected with the upper half of the outer casing 21; and the lower half of the low-pressure compressor supporting stator 24, the high-pressure compressor supporting stator 26 and the turbine supporting stator 29 and the inner casing 22 are fixedly connected with the lower half of the outer casing 21, and the lower half of the outer casing 21 is fixedly connected with the test support 10.

[0051] In the optional solution of the embodiment, preferably, as shown in Figure 2 and Figure 6 One end of the rotating shaft 23 is fixedly provided with a first flange plate 231, and the first flange plate 231 is fixedly provided with a rotating handle 232.

[0052] In the optional solution of the embodiment, preferably, as shown in Figure 1 and Figure 2 The other end of the rotating shaft 23 away from the first flange plate 231 is fixedly provided with a second flange plate 233, and the second flange plate 233 is sequentially fixedly connected with a shaft coupling 50 (specifically, a nylon shaft coupling 50) and a driving motor and reduction box mechanism 60; the driving motor and reduction box mechanism 60 is fixedly provided with a motor support 61 below.

[0053] In the optional solution of the embodiment, preferably, as shown in Figure 2 and Figure 6 The sleeve 40 is composed of two halves, and one half of the sleeve 40 is detachably connected with the other half of the sleeve 40.

[0054] Specifically, the half structure of the outer casing 21 is the same as that of the sleeve 40. Taking the half structure of the sleeve 40 as an example, the abutting portions of the two halves of the sleeve 40 are respectively provided with connecting extension plates, and through holes can be formed in the connecting extension plates, and bolts and nuts are arranged in the through holes, so as to realize the fixed connection of the two parts.

[0055] Specifically, the bottom of the experimental support is provided with universal wheels, which can move the position and lock the position after moving. It is prior art and will not be described in detail here.

[0056] Specifically, the upper half of the outer casing 21 is divided into three sections along the axial direction, corresponding to the three-stage low-pressure compressor disc 25, the four-stage high-pressure compressor disc 27 and the three-stage turbine disc 28, and two handles are arranged on the outer side wall of each section.

[0057] Specifically, taking the fixing of the low-pressure first-stage compressor rotating disc 251 in the three-stage low-pressure compressor disc 25 as an example, one sleeve 40 is fixedly arranged on each side of the low-pressure first-stage compressor rotating disc 251, the low-pressure first-stage compressor rotating disc 251 is connected with the rotating shaft 23 through a key to limit the relative rotation in the circumferential direction, and the movement of the low-pressure first-stage compressor rotating disc 251 along the axis of the rotating shaft 23 is limited by the sleeves 40 at both ends; the distance between the adjacent two rotating discs is controlled by the sleeves 40 therebetween; the fixing structures on the four-stage high-pressure compressor disc 27 and the three-stage turbine disc 28 are the same.

[0058] Specifically, the outer diameter of the compressor rotating disc is equal to the lowest point of the original engine tenon groove.

[0059] The principles and implementation manners of the present application are described by using specific examples in the present application, and the above examples are only used for helping to understand the method of the present application and its core idea; meanwhile, for the general technical personnel in the art, the specific implementation manners and application ranges will be changed according to the idea of the present application. In conclusion, the content of the specification should not be understood as the limitation of the present application.

Claims

1. A tester for simulating borescope testing of aircraft engines, characterized by: It includes a test stand and a tester module; the tester module is consistent in size and shape with the real aircraft engine after removing the combustion chamber and the rear three-stage high-pressure compressor; The tester module includes an outer casing, an inner casing, a rotating shaft, a low-pressure compressor support stator, a three-stage low-pressure compressor disk, a high-pressure compressor support stator, a four-stage high-pressure compressor disk, a three-stage turbine disk and a turbine support stator; The outer casing is fixedly mounted on the test stand, the inner casing is sleeved inside the outer casing, and the inner casing is sleeved outside the rotating shaft; a plurality of boreholes consistent with those on the real machine are provided at corresponding positions of the outer casing and the inner casing; The low-pressure compressor support stator, the high-pressure compressor support stator, and the turbine support stator are fixedly arranged in the outer casing and are sequentially rotatably arranged on the rotating shaft around the axis of the rotating shaft; The three-stage low-pressure compressor disc is fixedly arranged on the rotating shaft between the low-pressure compressor support stator and the high-pressure compressor support stator; the four-stage high-pressure compressor disc and the three-stage turbine disc are fixedly arranged in sequence on the rotating shaft between the high-pressure compressor support stator and the turbine support stator, the four-stage high-pressure compressor disc is located on a side of the three-stage turbine disc close to the three-stage low-pressure compressor disc, and the four-stage high-pressure compressor disc and the three-stage turbine disc are both located in the inner casing; The three-stage low-pressure compressor disc, the four-stage high-pressure compressor disc, and the three-stage turbine disc are all capable of adjusting their positions along the axis of the rotating shaft and maintaining their adjusted relative positions; Blade mounting seats are provided on the circumferential side walls of the three-stage low-pressure compressor disk, the four-stage high-pressure compressor disk and the three-stage turbine disk. Corresponding blades are fixedly connected to the blade mounting seats. The position and shape of the blades at each stage are consistent with those of the real machine.

2. The tester for simulating borescope testing of an aircraft engine according to claim 1, characterized in that: The three-stage low-pressure compressor disk includes a low-pressure first-stage compressor turntable, a low-pressure second-stage compressor turntable, and a low-pressure third-stage compressor turntable, which are sequentially fixed on the rotating shaft. The end of the low-pressure first-stage compressor turntable away from the low-pressure second-stage compressor turntable is close to the low-pressure compressor support stator. The four-stage high-pressure compressor disk includes a high-pressure first-stage compressor rotary disk, a high-pressure second-stage compressor rotary disk, a high-pressure third-stage compressor rotary disk, and a high-pressure fourth-stage compressor rotary disk fixedly arranged on the rotating shaft in sequence, and the end of the high-pressure first-stage compressor rotary disk away from the high-pressure second-stage compressor rotary disk is close to the high-pressure compressor support stator; The three-stage turbine disc comprises a high-pressure turbine disc, a low-pressure first-stage turbine disc and a low-pressure second-stage turbine disc fixedly arranged on the rotating shaft in sequence, and the end of the high-pressure turbine disc away from the low-pressure first-stage turbine disc is close to the high-pressure compressor support stator; Sleeves for separating the stages are sandwiched between the three-stage low-pressure compressor disks, between the four-stage high-pressure compressor disks, and between the three-stage turbine disks. The sleeves are fixedly connected to the rotating shaft.

3. The tester for simulating borescope testing of an aircraft engine according to claim 1, characterized in that: The high-pressure compressor support stator is fixedly connected to the inner wall of the outer casing through a plurality of high-pressure compressor spokes fixed on the circumferential side wall; the turbine support stator is fixedly connected to the inner wall of the outer casing through a plurality of turbine spokes fixed on the circumferential side wall; The inner casing is one quarter of the complete body; one end of the inner casing is fixedly connected to at least one high-pressure compressor spoke, and the other end of the inner casing is fixedly connected to at least one turbine spoke.

4. The tester for simulating borescope testing of an aircraft engine according to claim 3, characterized in that: A first adjustment slot is formed on the high-pressure compressor disc, and a second adjustment slot is formed on the turbine disc; the first adjustment slot and the second adjustment slot extend in parallel with the radial direction of the outer casing; A first fixing hole is formed at one end of the inner casing, and a second fixing hole is formed at the other end; The first fixing hole corresponds to the first adjusting long hole and is penetrated by a first fastener; the second fixing hole corresponds to the second adjusting long hole and is penetrated by a second fastener.

5. The tester for simulating borescope testing of an aircraft engine according to claim 1, characterized in that: The outer casing, the low-pressure compressor support stator, the high-pressure compressor support stator and the turbine support stator are all composed of upper and lower half structures; The upper half of the outer casing is detachably connected to the lower half of the outer casing; The upper parts of the low-pressure compressor support stator, the high-pressure compressor support stator and the turbine support stator are all fixedly connected to the upper part of the outer casing; and the lower parts of the low-pressure compressor support stator, the high-pressure compressor support stator and the turbine support stator and the inner casing are all fixedly connected to the lower part of the outer casing, and the lower part of the outer casing is fixedly connected to the test bracket.

6. The tester for simulating borescope testing of an aircraft engine according to claim 1, characterized in that: The blade mounting seat includes a first side ring plate, a second side ring plate, a first long support screw, a second long support screw, a first side pressing bolt and a second side pressing bolt; The first side ring plate and the second side ring plate are arranged in parallel and spaced apart and fixed relative to each other; the first side ring plate and the second side ring plate are circumferentially provided with a plurality of groups of one-to-one corresponding internal support threaded holes and side crimping threaded holes; The first long support screw and the second long support screw are arranged in parallel, and the first long support screw and the second long support screw are respectively threadedly inserted into the two corresponding inner support threaded holes, and the tenon of the blade is inserted between the first long support screw and the second long support screw; The first side compression bolt and the second side compression bolt are respectively abutted against the positions on both sides of the tenon of the blade close to the first side ring plate and the second side ring plate. The first side compression bolt is threadedly connected to the side compression threaded hole of the first side ring plate, and the second side compression bolt is threadedly connected to the side compression threaded hole of the second side ring plate.

7. The tester for simulating borescope testing of an aircraft engine according to claim 6, characterized in that: The blade mounting seat also includes two side locking plates, each of which corresponds to the first side pressing bolt and the second side pressing bolt respectively; the lower end of the side locking plate is fixedly connected to the first side pressing bolt or the second side pressing bolt, and the lower plane of the upper end of the side locking plate is pressed onto the upper plane of the corresponding side of the base above the tenon of the blade.

8. The tester for simulating borescope testing of an aircraft engine according to claim 1, characterized in that: A first flange is fixedly provided at one end of the rotating shaft, and a rotating handle is fixedly provided on the first flange.

9. The tester for simulating aerospace engine borescope testing according to claim 8, characterized in that: A second flange is fixedly provided on one end of the rotating shaft away from the first flange, and the second flange is fixedly connected in sequence to a coupling, a drive motor and a reduction gearbox mechanism; A motor bracket is fixedly arranged below the driving motor and the reduction box mechanism.

10. The tester for simulating borescope testing of an aircraft engine according to claim 2, characterized in that: The sleeve is composed of a half structure, and one half of the sleeve is detachably connected to the other half of the sleeve.

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