CN217237200U - Aero-engine rotor and stator rub-impact test device - Google Patents
Aero-engine rotor and stator rub-impact test device Download PDFInfo
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- CN217237200U CN217237200U CN202220344305.4U CN202220344305U CN217237200U CN 217237200 U CN217237200 U CN 217237200U CN 202220344305 U CN202220344305 U CN 202220344305U CN 217237200 U CN217237200 U CN 217237200U
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Abstract
An aeroengine rotor and stator rub-impact test device is used for improving the accuracy of rub-impact load, wherein a mounting bracket comprises a first hanging point and a second hanging point; the simulation fan case and the simulation intermediary case which are coaxially connected in series are suspended at the first hanging point; the simulated turbine rear casing is suspended at the second hanging point; the simulation low-voltage rotor assembly comprises simulation blades, a simulation wheel disc for mounting the simulation blades and a simulation shaft for mounting the simulation wheel disc, and the simulation shaft extends along the central axis direction of the simulation fan casing; the first support assembly includes a first bearing mounted on the dummy shaft; the second support component comprises a second bearing arranged on the simulation shaft and is arranged on the simulation intermediary casing together with the first support component; the third support assembly includes a third bearing mounted on the dummy shaft and mounted to the dummy turbine aft case.
Description
Technical Field
The utility model relates to an aeroengine rotor-stator bump test device that rubs.
Background
In order to improve the performance of the engine and increase the thrust-weight ratio, it is often considered to reduce the clearance between the rotor and the stator, especially the clearance between the rotating blade and the casing, so that the possibility of rubbing between the blade and the casing is gradually increased. Different from common rotor rubbing, the tangential speed of the blade is high, the collision energy is large, the rigidity of the engine casing is large, when the flying and falling mass is small, the rubbing action load of the blade and the casing is small, and an easily-abraded layer is arranged on the inner wall of part of the casing, so that the influence on the normal operation of the engine is small. When the flying and falling mass is large, the collision and friction action is more severe, and even risks are brought to the safe operation of the engine.
After the mass of the engine blade is lost, the flying and falling mass firstly collides the casing, meanwhile, the rotor system collides the casing under the unbalanced action, and in the rotating and rubbing process, the rotating blade also collides the flying and falling mass, so the collision and rubbing process is a complex nonlinear problem. When the flying mass is small, the vibration of the engine is small, the engine can still run continuously, when the flying mass is large, such as the flying of fan blades, the engine is often shut down within the first time for ensuring safety, and before the engine is shut down, the engine still keeps the previous power running, and the engine cannot have harmful results within the time. It is therefore necessary to verify engine rub-on for various fly-off masses.
Besides, the engine rub-impact load is related to the flying mass, the structure, the number, the structure, the material, the supporting component and the like of the blades, the blade-casing rub-impact process is a highly nonlinear problem, and the analysis result of the rub-impact load by a simulation analysis method has a certain error, so the test device also needs to have a function of verifying the influence of related parameters on the rub-impact load.
In order to solve the problems, the radial feeding of the rubbing bolt is controlled through a transmission mechanism, when the feeding amount is larger than the clearance of a rotor and a stator, the rotor and the rubbing bolt rub against each other, and the applicable scene of the scheme is usually a rotor disc and is not suitable for rubbing the rotor blade; still someone replaces the rub-impact bolt in above-mentioned scheme with one section simulation machine casket structure, and this kind of scheme is applicable in the rub-impact of rotor blade and machine casket, but because the rub-impact region is less, and is different with actual rub-impact condition, is difficult to simulate real rub-impact condition, still someone proposes through heating the rotor for the rotor is heated the inequality and produces the thermal bending, thereby arouses rotor stator rub-impact, and this method can simulate multistage bladed disk rotor thermal bending and the rub-impact trouble that arouses, but is difficult to simulate the engine rub-impact that the blade flew off and arouses.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aeroengine rotor stator bumps test device that rubs for promote and bump the accuracy of grinding the load.
The aero-engine rotor and stator rub-impact test device comprises a mounting bracket, a first hanging point and a second hanging point, wherein the mounting bracket comprises a first hanging part and a second hanging part; the simulation fan case and the simulation medium case which are coaxially connected in series are suspended at the first hanging point; the rear casing of the simulated turbine is suspended at the second suspension point; the simulation low-voltage rotor assembly comprises simulation blades, a simulation wheel disc for mounting the simulation blades and a simulation shaft for mounting the simulation wheel disc, and the simulation shaft extends along the central axis direction of the simulation fan casing; the first support assembly includes a first bearing mounted on the dummy shaft; the second support component comprises a second bearing arranged on the simulation shaft and is arranged on the simulation intermediary casing together with the first support component; the third support assembly includes a third bearing mounted on the dummy shaft and mounted to the dummy turbine aft case.
In one or more embodiments, at least one of the simulated blades includes a pre-fabricated defect for initiating a crack when the simulated shaft is accelerated to a predetermined rotational speed.
In one or more embodiments, the simulated low pressure rotor assembly further comprises a simulated low pressure rotor configured as a mass adjuster of the low pressure rotor assembly.
In one or more embodiments, the simulated low pressure rotor is connected to the simulated wheel disc by a tenon-to-mortise connection.
In one or more embodiments, the first support member is a resilient support member.
In one or more embodiments, the first support assembly includes an inner resilient support and an outer resilient support, the first bearing is mounted on the inner resilient support, the inner resilient support is resiliently deformably mounted on the outer resilient support, the outer resilient support is resiliently deformably mounted on a first bearing support cone wall mounted on the simulation interposer cartridge.
In one or more embodiments, the inner elastic support seat and the outer elastic support seat are of a cylindrical structure, and the cylindrical wall of a partial section of the cylindrical structure is a circle of elastic support rib plates.
In one or more embodiments, the dummy shaft is flexibly connected to a transition flexible shaft for connection to a motor via a connection assembly.
In one or more embodiments, the connection assembly is a bellows coupling.
In one or more embodiments, the bellows coupling is connected to the dummy shaft or the flexible connection shaft by a spline connection structure.
The aero-engine rotor and stator rubbing test device well simulates the structure of an engine and comprises a low-pressure rotor system, a fulcrum bearing, support structures, an intermediary casing, a mounting bracket and the like, the device can completely simulate the transmission path of FBO (fiber bulk acoustic resonator) load and simulate the rubbing process of the engine more truly, and therefore the accuracy of rubbing load can be improved.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of an aircraft engine rotor-stator rub-impact test device.
Fig. 2 is a perspective view of a simulation shaft.
Fig. 3 is a cross-sectional view of the resilient support assembly.
Fig. 4 is a perspective view of the outer elastic supporting seat.
Fig. 5 is a perspective view of the inner elastic supporting seat.
Fig. 6 is a schematic diagram of a simulated low pressure rotor assembly.
FIG. 7 is a schematic view of a simulated blade.
FIG. 8 is a schematic view of a simulated wheel disc.
Fig. 9 is a schematic view of a connection assembly.
Fig. 10 is a schematic view of a first support assembly.
Fig. 11 is a schematic view of a second support assembly.
Fig. 12 is a schematic view of a third support assembly.
FIG. 13 is a schematic view of a rotor support assembly.
Fig. 14 is a schematic view of a mounting bracket.
Detailed Description
As shown in fig. 1, the aero-engine rotor-stator rub-impact test device is designed according to the structural characteristics of an engine in a simulation mode, and comprises a mounting bracket 28, a simulation fan casing 29, a simulation intermediary casing, a simulation turbine rear casing 22, a simulation low-pressure rotor assembly 103, a first support assembly 109, a second support assembly 110 and a third support assembly 111, wherein the simulation fan casing 29, the simulation intermediary casing, the simulation turbine rear casing and the simulation low-pressure rotor assembly are coaxially connected in series.
As shown in fig. 14, the mounting bracket 28 includes a first hanging point 281 and a second hanging point 282.
The simulation agent casing is divided into two sections, including simulation agent casings 30, 11. The co-axial fan case and the simulation intermediary case are suspended at a first hanging point 281. The simulated turbine aft case 22 is suspended at a second hang point 282.
The simulated low-pressure rotor assembly 103 includes a simulated blade 1, a simulated disk 2 on which the simulated blade 1 is mounted, and a simulated shaft 3 on which the simulated disk 2 is mounted, the simulated shaft 3 extending in the direction of the center axis of the simulated fan case 29. Preferably, the simulated low pressure rotor assembly 103 further comprises a simulated low pressure rotor 15, the simulated low pressure rotor 1 being provided as a mass adjuster of the low pressure rotor assembly 103.
The first support assembly 109 includes a first bearing 8 mounted on the dummy shaft 3, the first bearing 8 being referred to in the industry as bearing No. 1, and bearing No. 1 and bearing first refer to the same component hereinafter. The second support assembly 110 includes a second bearing 14 mounted on the dummy shaft 3, and is mounted on the dummy cartridge housing in conjunction with the first support assembly 109, the second bearing 14 being referred to in the industry as a bearing number 2, and the bearing number 2 and the second bearing are referred to hereinafter as the same component. The third support assembly 111 includes a third bearing 18 mounted on the dummy shaft 3 and mounted on the dummy turbine aft case 28. The first support assembly 109 may be a flexible support assembly or a rigid support assembly, and in the following description, the first support assembly 109 is sometimes referred to as a flexible support assembly 109. The second support component 110 and the third support component 111 can also be called as a 2-fulcrum rigid support component and a 3-fulcrum rigid support component.
In the embodiment shown in fig. 1, the simulation disk 2 is connected with the simulation blade 1 and then connected with the simulation shaft 3, the simulation low pressure rotor 15 is connected with the simulation shaft 3 through the simulation low pressure rotor locking nut 16, and the simulation low pressure rotor assembly 103 is formed by the simulation low pressure rotor and the simulation low pressure rotor. The individual simulated engine rotating components are shown in FIG. 6. The engine supporting component is generally divided into an elastic supporting component and a rigid supporting component, the inner elastic supporting seat 5, the outer elastic supporting seat 6, the No. 1 bearing 8 and the limiting block 7 are connected through bolts, and the bearings are compressed through the No. 1 bearing compression nuts 4 to form the elastic supporting component 109. No. 2 bearing support ring 13, No. 2 bearing seat 10, No. 2 bearing 14 are connected, and are compressed through No. 2 bearing compression nut 12, so that a 2-fulcrum rigid support assembly 110 is formed, as shown in FIG. 11. The No. 3 bearing support ring 21, the No. 3 bearing seat 20 and the No. 3 bearing 18 are connected and are pressed through the No. 3 bearing pressing nut 17 to form a 3-fulcrum rigid support assembly 111, as shown in FIG. 12. The rigid members 110 and 111 are used to simulate the rigid support members, and the elastic member 109 together constitute the rotor support member of the rub test apparatus, as shown in fig. 13.
Blade to casing rub loads are related to the structural stiffness, structural characteristics, rub-on rotational speed, and missing mass of the blades and casings. When the missing mass is small, the degree of collision and friction is light, the conventional test device is often used for simulating the collision and friction working condition, and when the missing mass is large, the degree of collision and friction is severe. As shown in fig. 7, the simulated blade 1 achieves mass fly-off at a predetermined rotational speed range through the pre-fabricated defect 104. The defect 104 may be prefabricated on one simulated blade 1 or on a plurality of simulated blades 1. When the rotor is accelerated to a predetermined rotational speed, the blade may crack from the pre-fabricated defect 104 and subsequently break due to insufficient centrifugal loading of the remaining blade material. The quality of the fly-off can be simulated by controlling the position of the pre-made defect 104 and the rotational speed of the fly-off can be controlled by controlling the length of the defect.
The simulated blade 1 simulates the blade tip shape of a real engine blade, and because the rigidity of the structure has certain influence on rubbing load, the rigidity of the blade can be adjusted by changing the thickness of the blade so as to simulate the rigidity of the blade of the real engine. Similarly, the simulated fan case 29 can simulate the structure of the engine case, and the thickness, rigidity and structure of the rub-impact region are changed, so that the simulated fan case 29 is similar to the structure of the real case. As shown in fig. 7 and 8, the simulated blade 1 and the simulated disk 2 are connected by the simulated blade tenons 105 and the mortises 106 of the simulated disk 2, and the number of the simulated blades 1 and the shape of the mortises can be changed by changing the number of the mortises and the shape of the mortises of the simulated disk to adapt to different shapes of the blade tenons 105. The dummy blades 1 and the dummy fan case 29 may be made of metal or composite material to accommodate rotor rub conditions of different materials.
As shown in fig. 3 to 5 and 10, the first supporting assembly 109 includes an inner elastic support base 5 and an outer elastic support base 6, and in conjunction with fig. 1, the first bearing 8 is mounted on the inner elastic support base 5, the inner elastic support base 5 is elastically deformable mounted on the outer elastic support base 6, the outer elastic support base 6 is elastically deformable mounted on the first bearing supporting cone wall 9, and the first bearing supporting cone wall 9 is mounted on the dummy cartridge.
The inner elastic support seat 5 and the outer elastic support seat 6 are of a cylindrical structure, and the cylinder wall of a partial section of the cylindrical structure is provided with a circle of elastic support rib plates 101 and 102.
The rigidity of the elastic support can be changed by changing the thickness and the number of the outer elastic support ribs 101 and the inner elastic support ribs 102, so as to obtain the support rigidity expected by the test, and the rigid support component can be used to replace the outer elastic support seat 6 and the inner elastic support seat 5, so that the support component at the bearing No. 1 bearing 8 is the rigid support. The influence of different supporting rigidity on the collision and friction load can be conveniently realized through the change of the structure. The hoisting rigidity can be changed by changing the size of the mounting bracket 28, and the influence of different mounting rigidities on the rubbing load is realized.
As shown in fig. 1 and 9, the simulation shaft 3 of the simulation low-voltage rotor assembly 103 is connected with the motor connection flexible shaft 26 through the connection assembly 108 so as to be connected with the motor, and the motor rotates to drive the simulation low-voltage rotor assembly 103, so that the transmission of the rotating speed is realized. During the rubbing process, the simulated low-pressure rotor assembly 103 usually rotates eccentrically, and the center of mass of the simulated wheel disc 2 is no longer on the symmetry axis, but rotates eccentrically with a certain rule. In order to avoid the influence of the motor transmission on the eccentric motion of the wheel disc, the switching flexible shaft 25 is firstly adopted for connection, the shaft inner diameter of the switching flexible shaft 25 is smaller, the rigidity is smaller, and the smaller constraint effect is realized on the eccentric motion of the wheel disc. In one embodiment, the connection assembly 108 is connected by a bellows coupling 24, the bellows coupling 24 enables the connection structure to move freely in multiple directions, and the bellows coupling 24 is connected with the simulation shaft 3 by a sleeve gear connection structure 113. The set tooth connection structure, as shown in fig. 2 and 9, includes a coupler adapter 23 and an internal spline at the right end of the simulation shaft 3, the coupler adapter 23 is correspondingly of an external spline structure, and the coupler adapter 23 is in spline connection with the internal spline at the right end of the simulation shaft 3, so that certain movement is not coordinated and torque can be continuously transmitted. The restraining effect of the linkage assembly 108 on the simulated low pressure rotor assembly 103 is minimized by the less rigid transition flexible shaft 25, the bellows coupling 24 that allows free movement in multiple directions, and the cog attachment structure 113. In another embodiment, the bellows coupling and the flexible connecting shaft are connected by a sleeve tooth connecting structure.
The foregoing embodiment may be used for the simulation of the rub-on process under large missing masses, simulating the mass of the fly-off by controlling the position of the pre-made defect 104, and controlling the rotational speed of the fly-off by controlling the length of the defect. Meanwhile, the test device is externally provided with a protective cover 27, so that the safety of test personnel can be guaranteed.
The assembly process of the test rotor was as follows:
1. the inner elastic supporting seat 5, the outer elastic supporting seat 6, the No. 1 bearing 8 and the limiting block 7 are connected through bolts in sequence and then are compressed through the No. 1 bearing compression nut 4 to form an elastic supporting assembly 109;
2. sequentially connecting a No. 2 bearing support ring 13, a No. 2 bearing seat 10 and a No. 2 bearing 14, and compressing through a No. 2 bearing compression nut 19 to form a No. 2 fulcrum rigid support assembly 111;
3. assembling the elastic support component 109 on the simulation shaft 3, and after the installation conical wall 9 is connected with the elastic support component 109, installing the 2-fulcrum rigid support component 111 on the installation conical wall 9;
4. the simulation fan casing 29 is connected with the simulation intermediary casing 30 through a bolt, the simulation intermediary casing 30 is connected with the simulation intermediary casing 11 through a bolt, and the simulation intermediary casing 11 is connected with the No. 2 bearing seat 10 through a bolt;
5. the simulation disk 2 is connected to the simulation blade 1 and then connected to the simulation shaft 3. The dummy low pressure rotor 15 is attached to the dummy shaft 3 and is locked by a compression nut 16. The simulation wheel disc 2, the simulation blades 1, the simulation shaft 3 and the simulation low-pressure rotor 15 jointly form a simulation low-pressure rotor assembly 103;
6. sequentially connecting a bearing support ring No. 3 21, a bearing seat No. 3 20 and a bearing No. 3 18, compressing through a bearing compression nut No. 3 17 to form a rigid support assembly 111 with a fulcrum 3, connecting the rigid support assembly 111 with the fulcrum 3 to the simulation shaft 3, and locking through a bearing locking nut No. 3 19; the 3-fulcrum rigid support component 111, the 2-fulcrum rigid support component 110, the elastic support component 109 and the mounting conical wall 9 form a rotor support component;
7. connecting the simulated turbine rear casing 22 with the 3-fulcrum rigid support assembly 112 through bolts;
8. the coupling adaptor 23, the bellows coupling 24, and the adaptor flexible shaft 25 are connected to form the connection assembly 108. The coupling adapter 23 is matched and connected with a spline of the simulation shaft 3, and the adapter flexible shaft 2 is connected with the motor connecting flexible shaft 26;
9. the test device is secured to the mounting bracket 28 and the test device and mounting bracket are placed into the protective cover 27 to complete the assembly of the entire rub-on test device assembly 31.
The rub-impact test device has the beneficial effects as described later.
The rub-impact test device simulates the structural characteristics of an engine completely, the supporting rigidity is adjustable by adopting the supporting modes of elastic supporting and rigid supporting, the simulated blade 1 simulates the shape of the blade tip of a real engine blade, the simulated fan casing 29, the simulated intermediate casing 30 and the like can simulate the casing structure of the engine, the simulated low-pressure rotor 15 can simulate the mass of the blade and a wheel disc, and the mounting bracket 28 can simulate the hanging of an airplane.
The rub-impact test device can simulate the rub-impact load change condition after the mass of the blade is lost at a preset rotating speed, can prefabricate the defect 104 on one simulated blade 1, and can also prefabricate on a plurality of simulated blades 1. The quality of the fly-off can be simulated by controlling the position of the pre-made defect 104 and the rotational speed of the fly-off can be controlled by controlling the length of the defect.
The rub-impact test device can perform rub-impact tests under different support rigidities, the rigidity of the blade can be adjusted by changing the thickness of the simulation blade 1, the thickness, the rigidity and the structure of a rub-impact area of the simulation fan case 29 are changed, and the rigidity of the simulation fan case 29 is adjusted. The rigidity of the elastic support can be changed by changing the thickness and number of the outer elastic support rib 101 and the inner elastic support rib 102, and the outer elastic support seat 6 and the inner elastic support seat 5 can be replaced by a rigid support component, so that the support component at the bearing No. 18 is rigid support. The stiffness of the hanger can be varied by varying the thickness of the mounting bracket 28.
The rub-impact test device is used for carrying out rub-impact tests on different blade structures and materials, and the number of the simulated blades 1 and the shapes of the mortises can be changed by changing the number of the mortises of the simulated wheel disc and the shapes of the mortises so as to adapt to different shapes of the blade tenons 105. The dummy blades 1 and the dummy fan case 29 may be made of metal or composite material to accommodate rotor rub conditions of different materials.
The rub-impact test device can perform rub-impact tests on low-pressure rotors with different rotational inertia, and the rotational inertia of the rotor assembly can be changed by changing the mass of the simulated low-pressure rotor 15, so that the control on the rub-impact time and the investigation on the rub-impact influence of the rotational inertia of the rotor on an engine are realized.
The limit effect of the friction test device on the simulation low-pressure rotor assembly 103 is minimum, the eccentric rotation of the simulation low-pressure rotor assembly 103 is not influenced, the friction test device is connected by the aid of the switching flexible shaft 25 with low rigidity, the corrugated pipe coupler 24 enables the connecting structure to move freely in multiple directions, the coupler adapter 23 is connected with the simulation shaft 3 through the sleeve teeth, and certain movement incompatibility can be allowed due to the sleeve teeth connection.
The rub-impact test device can be used for simulating a rub-impact process under large missing mass, simulating the flying mass by controlling the position of the prefabricated defect 104, and controlling the rotating speed of the flying by controlling the length of the defect. Meanwhile, the test device is externally provided with a protective cover 27, so that the safety of test personnel can be guaranteed.
Claims (10)
1. Aeroengine rotor stator bumps friction test device, its characterized in that includes:
the mounting bracket comprises a first hanging point and a second hanging point;
the simulation fan casing and the simulation medium casing are coaxially connected in series and suspended at the first hanging point;
simulating a turbine rear casing, and suspending at the second hanging point;
the simulation low-pressure rotor assembly comprises simulation blades, a simulation wheel disc for mounting the simulation blades and a simulation shaft for mounting the simulation wheel disc, wherein the simulation shaft extends along the central axis direction of the simulation fan casing;
a first support assembly including a first bearing mounted on the dummy shaft;
a second support assembly including a second bearing mounted on a simulation shaft, mounted on said simulation intermediary cartridge housing in cooperation with said first support assembly; and
a third support assembly, including a third bearing mounted on the dummy shaft, is mounted to the dummy turbine aft case.
2. The aircraft engine rotor rub test apparatus of claim 1, wherein at least one of the simulated blades comprises a pre-fabricated defect configured to create a crack when the simulated shaft is accelerated to a predetermined rotational speed.
3. The aircraft engine rotor-stator rub-impact test apparatus of claim 1, wherein the simulated low pressure rotor assembly further comprises a simulated low pressure rotor configured as a mass adjuster of the low pressure rotor assembly.
4. The aircraft engine rotor-stator rub-impact test apparatus according to claim 1, wherein the simulated low pressure rotor is connected to the simulated wheel disc by a tenon-to-mortise connection.
5. The aircraft engine rotor-stator rub-impact test apparatus according to claim 1, wherein the first support member is an elastic support member.
6. The aircraft engine rotor-stator rub impact test apparatus according to claim 5, wherein the first support assembly includes an inner resilient support and an outer resilient support, the first bearing being mounted on the inner resilient support, the inner resilient support being resiliently deformably mounted on the outer resilient support, the outer resilient support being resiliently deformably mounted on a first bearing support cone wall mounted on the simulation interposer cartridge.
7. The aero-engine rotor-stator rub test device according to claim 6, wherein the inner elastic support seat and the outer elastic support seat are of a cylindrical structure, and a cylindrical wall of a partial section of the cylindrical structure is a circle of elastic support rib plates.
8. The aircraft engine rotor-stator rub-impact test apparatus according to claim 1, wherein the simulation shaft is flexibly connected to a flexible shaft through a connection assembly, the flexible shaft being adapted to be connected to a motor.
9. The aircraft engine rotor-stator rub-impact test apparatus according to claim 8, wherein the connecting assembly is a bellows coupling.
10. The aircraft engine rotor-stator rub-impact test device according to claim 9, wherein the bellows coupling is connected to the dummy shaft or the flexible connection shaft through a sleeve tooth connection structure.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202220344305.4U CN217237200U (en) | 2022-02-21 | 2022-02-21 | Aero-engine rotor and stator rub-impact test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202220344305.4U CN217237200U (en) | 2022-02-21 | 2022-02-21 | Aero-engine rotor and stator rub-impact test device |
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| CN217237200U true CN217237200U (en) | 2022-08-19 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115235782A (en) * | 2022-09-21 | 2022-10-25 | 中国航发上海商用航空发动机制造有限责任公司 | Turbine rotor stator axial collision and abrasion detection device and method |
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2022
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115235782A (en) * | 2022-09-21 | 2022-10-25 | 中国航发上海商用航空发动机制造有限责任公司 | Turbine rotor stator axial collision and abrasion detection device and method |
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