Aero-engine five-stage turbine blade vibration fatigue test clamp

Abstract

The utility model relates to a vibration fatigue test fixture for a five-stage turbine blade of an aircraft engine, which belongs to the technical field of fixtures and comprises a blade chuck for clamping the five-stage turbine blade of the aircraft engine, the blade chuck is detachably mounted on a supporting piece and comprises a groove and a clamping groove matched with the five-stage turbine blade of the aircraft engine, and the clamping groove is detachably mounted on the supporting piece. The clamping groove comprises four sets of protrusions matched with the aircraft engine five-stage turbine blade, and the groove is communicated with the clamping groove. The clamp is provided with the blade chuck for clamping the aircraft engine five-stage turbine blade, and the vibration test of clamping the aircraft engine five-stage turbine blade is met. The clamp is provided with the groove communicated with the clamping groove, so that the transverse stress generated in the vibration test process of the aircraft engine five-stage turbine blade is prevented from directly acting on the blade chuck. According to the clamp, the supporting piece and the bottom plate are arranged, the blade chuck is connected with the vibration table, and the blade chuck can be used on different vibration tables in a connected mode.

Description

Technical Field

[0001] The utility model relates to the technical field of fixtures, in particular to a vibration fatigue test fixture for a five-stage turbine blade of an aero-engine. Background Art

[0002] In the prior art, a patent with publication number CN115493784A discloses a turbine blade vibration fatigue test fixture and a method of using the same, including an integrated fixture body dovetail tenon turbine blade, a dovetail tenon turbine blade with a tenon-groove clamp at one end of the integrated fixture body, a tenon-groove clamp dovetail tenon turbine blade with a tenon-groove clamp on the outer side of the dovetail tenon having the same shape as the dovetail tenon and capable of accommodating the dovetail tenon, an adjusting fastening bolt dovetail tenon turbine blade with a top of the integrated fixture body dovetail tenon turbine blade is provided, thereby preventing the blade from breaking at the tenon throat R, thereby successfully completing the test, achieving the test goal, reducing the number of test pieces, and reducing the test cost.

[0003] However, this technical solution cannot perform vibration fatigue tests on the fifth-stage turbine blades of aircraft engines. The heads of the turbine blades are in direct contact with the side walls of the mortise and tenon clamps. During vibration, the turbine blades will apply lateral stress to the mortise and tenon clamps, affecting the stability of the fixture. Utility Model Content

[0004] In order to overcome the above-mentioned defects of the prior art, the utility model provides an aero-engine five-stage turbine blade vibration fatigue test fixture to solve the problems raised in the background technology.

[0005] In order to achieve the above-mentioned purpose of the invention, the utility model provides a vibration fatigue test fixture for aero-engine fifth-stage turbine blades, including a blade clamp for clamping aero-engine fifth-stage turbine blades, wherein the blade clamp is detachably mounted on a support member, and the blade clamp includes a groove and a clamping groove that cooperates with the aero-engine fifth-stage turbine blades, wherein the clamping groove includes four groups of protrusions that cooperate with the aero-engine fifth-stage turbine blades, and the groove is connected to the clamping groove.

[0006] Furthermore, the fifth-stage turbine blade of the aero-engine is clearance-fitted with the clamping groove.

[0007] Furthermore, the fixture also includes a base plate connected to the vibration table, and the support member is detachably connected to the base plate.

[0008] Furthermore, the bottom plate is a disc-shaped bottom plate, and the disc-shaped bottom plate is provided with a plurality of positioning holes evenly distributed along the circumference.

[0009] Furthermore, the support member includes a support plate, the support plate is provided with a mounting hole for connecting to the base plate, and the base plate is provided with a bottom mounting hole aligned with the mounting hole.

[0010] Furthermore, the support member also includes an L-shaped plate, and the L-shaped plate is arranged on the support plate to form a U-shaped groove that cooperates with the blade clamp.

[0011] Furthermore, at least two fixing threaded holes are provided on the L-shaped plate, and fixing bolts are provided in the two fixing threaded holes. The fixing bolts pass through the fixing threaded holes and contact the blade clamp.

[0012] Furthermore, the number of the mounting holes is three, and the three mounting holes are respectively located on both sides of the L-shaped plate and on the side of the L-shaped plate away from the fifth-stage turbine blades of the aero-engine.

[0013] Compared with the prior art, the beneficial effects of the utility model are:

[0014] A blade clamp is provided to clamp the fifth-stage turbine blade of an aero-engine, so as to meet the vibration test of clamping the fifth-stage turbine blade of an aero-engine.

[0015] A groove connected to the clamping groove is provided to prevent the lateral stress generated during the vibration test of the fifth-stage turbine blade of the aero-engine from directly acting on the blade clamp.

[0016] By arranging the support and the bottom plate, the blade clamp is connected to the vibration table and can be connected and used on different vibration tables. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the main structure of an embodiment of the utility model;

[0018] Figure 2 It is a schematic diagram of the top view of the structure of an embodiment of the utility model;

[0019] Figure 3 It is a schematic structural diagram of a blade chuck according to an embodiment of the utility model. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solution and advantages of the embodiment of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described in conjunction with the drawings of the utility model. Obviously, the described embodiment is a part of the embodiment of the invention, not all of the embodiments. The embodiment of the utility model is described below in conjunction with the drawings.

[0021] refer to Figures 1 to 3 The vibration fatigue test fixture of the fifth-stage turbine blade of an aero-engine includes a blade clamp 4 for clamping the fifth-stage turbine blade 5 of the aero-engine. The blade clamp 4 is detachably installed on the support. The blade clamp 4 includes a groove 9 and a clamping groove 10 that cooperates with the fifth-stage turbine blade 5 of the aero-engine. The clamping groove 10 includes four groups of protrusions 11 that cooperate with the fifth-stage turbine blade 5 of the aero-engine. The groove 9 is connected to the clamping groove 10.

[0022] By arranging four groups of protrusions 11 on the clamping groove 10, the four groups of protrusions 11 cooperate with the aero-engine fifth-stage turbine blade 5 to connect and support the aero-engine fifth-stage turbine blade 5. The aero-engine fifth-stage turbine blade 5 and the clamping groove 10 are clearance-matched, and the aero-engine fifth-stage turbine blade 5 is fixedly installed on the blade clamp 4.

[0023] The groove 9 is connected with the clamping groove 10. After the aero-engine fifth-stage turbine blade 5 is installed on the clamping groove 10, the groove 9 is located on one side of the aero-engine fifth-stage turbine blade 5, separating the end of the aero-engine fifth-stage turbine blade 5 from the blade clamp 4, avoiding the lateral stress generated by the aero-engine fifth-stage turbine blade 5 during the test from acting on the blade clamp 4, thereby improving the structural stability of the test fixture.

[0024] The fixture also includes a base plate 1 connected to the vibration table. The support member is detachably connected to the base plate 1. For example, the support member can be installed on the base plate 1 through a threaded connection. The base plate 1 is a disc-shaped base plate. The disc-shaped base plate is provided with a plurality of positioning holes 6 evenly distributed along the circumference. Eight positioning holes 6 can be provided. The eight positioning holes 6 are evenly distributed in a circle in the circumferential direction. The base plate 1 can be fixedly installed on the vibration machine through the eight positioning holes 6.

[0025] The support member includes a support plate 2, which is provided with a mounting hole 7 for connecting to the base plate 1, and the base plate 1 is provided with a bottom mounting hole aligned with the mounting hole 7. The bottom mounting hole can be a threaded hole, and the support plate 2 can be fixedly mounted on the base plate 1 by threaded connection.

[0026] The support member also includes an L-shaped plate 3, which is arranged on the support plate 2 to form a U-shaped groove that cooperates with the blade clamp 4. During installation, the fifth-stage turbine blade 5 of the aircraft engine is installed on the blade clamp 4 through clearance fit, and then the blade clamp 4 is embedded in the above-mentioned U-shaped groove. After adjusting to a suitable position, the blade clamp 4 is fixed to the support member.

[0027] At least two fixing threaded holes 8 are provided on the L-shaped plate 3, and fixing bolts are provided in the two fixing threaded holes 8. The fixing bolts pass through the fixing threaded holes 8 and contact the blade clamp 4. The blade clamp 4 is supported by the head of the fixing bolt to fix the blade clamp 4 on the support. By setting two or more fixing bolts, the position of the blade clamp 4 can be better fixed.

[0028] There are three mounting holes 7, which are respectively located on both sides of the L-shaped plate 3 and on the side of the L-shaped plate 3 away from the aero-engine fifth-stage turbine blade 5. The mounting holes 7 are arranged in three directions, which can better fix the support member on the base plate 1. On one side of the position of the aero-engine fifth-stage turbine blade 5, since it is not convenient to fix the aero-engine fifth-stage turbine blade 5 by bolts after installation, three mounting holes 7 are arranged in the other three directions.

[0029] The blade clamp 4 is provided to clamp the fifth-stage turbine blade 5 of the aero-engine, so as to meet the vibration test of clamping the fifth-stage turbine blade 5 of the aero-engine, and solve the problem that the clamp in the prior art cannot clamp the fifth-stage turbine blade 5 of the aero-engine.

[0030] A groove 9 connected to the clamping groove 10 is provided to prevent the lateral stress generated during the vibration test of the fifth-stage turbine blade 5 of the aero-engine from directly acting on the blade clamp 4.

[0031] By providing the support member and the bottom plate 1, the blade clamp 4 is connected to the vibration table and can be connected and used on different vibration tables.

[0032] The technical solution of the present invention is described above in conjunction with specific implementation methods, but it should be noted that the above descriptions are only for explaining the solution of the present invention and cannot be interpreted in any way as a specific limitation on the scope of protection of the invention. Based on the explanation here, those skilled in the art can think of other specific implementation methods or equivalent replacements of the present invention without creative work, and they will all fall within the scope of protection of the present invention.

Claims

1. A vibration fatigue test fixture for a five-stage turbine blade of an aircraft engine, characterized in that: It includes a blade clamp for clamping an aircraft engine fifth-stage turbine blade, the blade clamp is detachably mounted on a support, the blade clamp includes a groove and a clamping groove that cooperates with the aircraft engine fifth-stage turbine blade, the clamping groove includes four groups of protrusions that cooperate with the aircraft engine fifth-stage turbine blade, and the groove is connected to the clamping groove.

2. The vibration fatigue test fixture for the fifth-stage turbine blade of an aircraft engine according to claim 1 is characterized in that: The fifth-stage turbine blade of the aero-engine is clearance-fitted with the clamping groove.

3. The vibration fatigue test fixture for the fifth-stage turbine blade of an aircraft engine according to claim 1, characterized in that: The fixture further comprises a bottom plate connected to the vibration table, and the support member is detachably connected to the bottom plate.

4. The vibration fatigue test fixture for the fifth-stage turbine blade of an aircraft engine according to claim 3 is characterized in that: The bottom plate is a disc-shaped bottom plate, and the disc-shaped bottom plate is provided with a plurality of positioning holes evenly distributed along the circumference.

5. The vibration fatigue test fixture for the fifth-stage turbine blade of an aircraft engine according to claim 3 is characterized in that: The support member comprises a support plate, the support plate is provided with a mounting hole for connecting with the bottom plate, and the bottom plate is provided with a bottom mounting hole aligned with the mounting hole.

6. The vibration fatigue test fixture for the fifth-stage turbine blade of an aircraft engine according to claim 5, characterized in that: The support member further comprises an L-shaped plate, and the L-shaped plate is arranged on the support plate to form a U-shaped groove matched with the blade clamp.

7. The vibration fatigue test fixture for the fifth-stage turbine blade of an aircraft engine according to claim 6, characterized in that: The L-shaped plate is provided with at least two fixing threaded holes, and fixing bolts are provided in the two fixing threaded holes. The fixing bolts pass through the fixing threaded holes and contact the blade clamp.

8. The vibration fatigue test fixture for the fifth-stage turbine blade of an aircraft engine according to claim 7, characterized in that: The number of the mounting holes is three, and the three mounting holes are respectively located on both sides of the L-shaped plate and on the side of the L-shaped plate away from the fifth-stage turbine blade of the aero-engine.

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