CN212363633U

CN212363633U - Aircraft engine blade test device

Info

Publication number: CN212363633U
Application number: CN202021312203.1U
Authority: CN
Inventors: 刘升旺; 覃文源; 魏铭瑛; 陈璐璐; 刘�文; 李继保; 王小庆; 杨凌元
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-07-07
Filing date: 2020-07-07
Publication date: 2021-01-15
Anticipated expiration: 2030-07-07

Abstract

The utility model relates to an aeroengine blade test device, it includes: a first mounting seat; the supporting assembly is arranged on the first mounting seat and is configured to support the blade sample; the support assembly comprises a first support and a second support, the first support and the second support both comprise a support part in contact with the blade sample, and the support part of the first support or the second support is configured to be capable of swinging relative to the first mounting seat; the second mounting seat is arranged above the first mounting seat; and the loading assembly is arranged on the second mounting seat and is positioned between the first support and the second support, and the loading assembly is configured to apply load to the blade sample. In the test process, the orientation of the supporting part of at least one supporting part can be automatically adjusted along with the deformation of the blade sample, so that the introduction of additional load caused by the incongruity of the supporting position and the orientation is avoided, and the accuracy of the applied load and the test is improved.

Description

Aircraft engine blade test device

Technical Field

The utility model relates to an aeronautical equipment field especially relates to an aeroengine blade test device.

Background

Jet engines for aircraft have two types of rotor and stator working blades, which work either on the air flow or on the blades during operation. In order to improve the working efficiency of the airflow, the blades are all double-curved profiles. During the work doing process, the blade can bear large loads, such as centrifugal load, temperature load, airflow load and the like, so that high internal stress is generated.

To verify the ability of these blades to resist loads, tests were typically conducted during the design process. For the fan blades, especially for the composite material fan blades, due to the large size and the anisotropy, before the part-level performance test is carried out, an element-level test is generally carried out, that is, the blades are cut to obtain local samples in different areas, and the performance test is carried out on the samples. Since these samples were cut from the blade, they were characterized by the double curved profile of the blade. Therefore, the samples are different from standard flat plate samples, if the test fixture recommended in the test standard is continuously adopted, the position and the orientation of the loading point and the position and the orientation of the supporting point can be changed after the samples are deformed along with the application of the load in the test process, and the position and the orientation of the loading point and the supporting point in the fixture cannot be adjusted at the moment, so that the load beyond the design expectation is introduced into the samples, and the test purpose cannot be realized.

Disclosure of Invention

Some embodiments of the utility model provide an aeroengine blade test device for develop the experiment to the aeroengine blade.

Some embodiments of the utility model provide an aeroengine blade test device, it includes:

a first mounting seat;

the supporting assembly is arranged on the first mounting seat and is configured to support the blade sample; the support assembly comprises a first support and a second support, the first support and the second support both comprise a support part in contact with the blade sample, and the support part of the first support or the second support is configured to be capable of swinging relative to the first mounting seat;

the second mounting seat is arranged above the first mounting seat; and

the loading assembly is arranged on the second mounting seat and located between the first support and the second support, and the loading assembly is configured to apply load to the blade sample.

In some embodiments, a first slide rail sliding groove structure is arranged between the first mounting seat and the support component, and the support component moves on the first mounting seat through the first slide rail sliding groove structure to adjust the position of the support component.

In some embodiments, the first sliding rail and sliding groove structure includes a first sliding groove and a second sliding groove provided in the first mounting seat, and a first sliding rail provided in the first supporting member and a second sliding rail provided in the second supporting member, and the first sliding groove and the second sliding groove are parallel to each other and both extend along the length direction of the blade sample; the first supporting piece moves along the first mounting seat through the matching of the first sliding rail and the first sliding groove so as to adjust the position; the second supporting piece moves along the first mounting seat through the matching of the second sliding rail and the second sliding groove so as to adjust the position.

In some embodiments, the loading assembly comprises a first loading member and a second loading member, each of the first loading member and the second loading member comprising a loading portion in contact with the blade specimen, the loading portion of the first loading member or the second loading member being configured to be swingable relative to the second mount.

In some embodiments, a second slide rail and slide groove structure is disposed between the second mounting seat and the loading assembly, and the loading assembly moves on the second mounting seat through the second slide rail and slide groove structure to adjust the position of the loading assembly.

In some embodiments, the second slide rail and slide groove structure includes a third slide groove and a fourth slide groove provided in the second mounting seat, and a third slide rail provided in the first loading member and a fourth slide rail provided in the second loading member, and the third slide groove and the fourth slide groove are parallel to each other and both extend along the length direction of the blade sample; the first loading piece moves along the second mounting seat through the matching of the third sliding rail and the third sliding groove so as to adjust the position; the second loading piece moves along the second mounting seat through the matching of the fourth sliding rail and the fourth sliding groove so as to adjust the position.

In some embodiments, a limiting assembly is included, the limiting assembly is arranged on the first mounting seat and located between the first support and the second support, and the limiting assembly is configured to limit the blade sample to swing relative to the first mounting seat.

In some embodiments, the limiting assembly includes a first limiting member and a second limiting member, and the tops of the first limiting member and the second limiting member are both provided with a groove for limiting the blade sample.

In some embodiments, a third sliding rail sliding groove structure is arranged between the first mounting seat and the limiting assembly, and the limiting assembly moves on the first mounting seat through the third sliding rail sliding groove structure to adjust the position of the limiting assembly.

In some embodiments, the limiting assembly includes a first limiting member and a second limiting member, the third slide rail and slide groove structure includes a first slide groove and a second slide groove provided in the first mounting seat, a fifth slide rail provided in the first limiting member and a sixth slide rail provided in the second limiting member, the first slide groove and the second slide groove are parallel to each other and both extend along the length direction of the blade sample; the first limiting piece moves along the first mounting seat through the matching of the fifth slide rail and the first slide groove so as to adjust the position; the second limiting part moves along the first mounting seat through the matching of the sixth slide rail and the second slide groove so as to adjust the position.

In some embodiments, the second support member includes a mounting portion and a supporting portion, the mounting portion of the second support member is disposed on the first mounting seat, and the supporting portion of the second support member is rotatably disposed relative to the mounting portion of the second support member.

In some embodiments, a first elastic element is arranged between the mounting part and the supporting part of the second supporting part, and the mounting part and the supporting part of the second supporting part are rotatably connected through a first shaft.

In some embodiments, a first support, a first loading member, a second loading member and a second support are sequentially arranged along the length extension direction of the blade sample, the support portion of the second support is configured to be capable of swinging relative to the first mounting seat, and the loading portion of the first loading member is configured to be capable of swinging relative to the second mounting seat.

In some embodiments, the first loading element includes a mounting portion and a loading portion, the mounting portion of the first loading element is disposed on the second mounting seat, and the loading portion of the first loading element is rotatably disposed relative to the mounting portion of the first loading element.

In some embodiments, a second elastic element is arranged between the mounting part and the loading part of the first loading piece, and the mounting part and the loading part of the first loading piece are rotationally connected through a second shaft.

In some embodiments, the support portions of the first and second supports are configured in an arc shape that conforms to the shape of the blade specimen; the loading portions of the first and second loading members are configured in an arc shape that matches the shape of the blade sample.

Based on the technical scheme, the utility model discloses following beneficial effect has at least:

in some embodiments, the blade specimen is supported from the bottom of the blade specimen by a first support and a second support, and a load is applied to the blade specimen from the top of the blade specimen by a loading assembly; the supporting part of the first supporting part or the second supporting part is configured to be capable of swinging relative to the first mounting seat, and the orientation of the supporting part of at least one supporting part can be automatically adjusted along with the deformation of the blade sample in the test process, so that the introduction of additional load caused by the incongruity of the supporting position and the orientation is avoided, and the accuracy of applied load and the accuracy of test are improved.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without undue limitation to the invention. In the drawings:

fig. 1 is a schematic view of an aircraft engine blade testing apparatus provided in accordance with some embodiments of the present invention;

fig. 2(a) is a schematic top view of a first mount provided according to some embodiments of the present invention;

fig. 2(b) is a schematic side view of a first mount provided according to some embodiments of the present invention;

fig. 3(a) is a schematic bottom view of a second mount provided in accordance with some embodiments of the present invention;

fig. 3(b) is a schematic side view of a second mount provided in accordance with some embodiments of the present invention;

fig. 4(a) is a schematic front view of a first support provided according to some embodiments of the present invention;

fig. 4(b) is a left side schematic view of a first support provided in accordance with some embodiments of the present invention;

fig. 4(c) is a schematic top view of a first support provided according to some embodiments of the present invention;

fig. 4(d) is a schematic bottom view of a first support according to some embodiments of the present invention;

fig. 5(a) is a schematic front view of a second support provided according to some embodiments of the present invention;

fig. 5(b) is a schematic right-view of a second support member provided in accordance with some embodiments of the present invention;

fig. 5(c) is a schematic top view of a second support provided in accordance with some embodiments of the present invention;

fig. 5(d) is a schematic bottom view of a second support member provided in accordance with some embodiments of the present invention;

FIG. 5(e) is an enlarged schematic view of the partial structure A in FIG. 5 (b);

fig. 6(a) is a schematic front view of a first carrier provided according to some embodiments of the present invention;

fig. 6(b) is a schematic left side view of a first carrier provided in accordance with some embodiments of the present invention;

fig. 6(c) is a schematic top view of a first load member provided in accordance with some embodiments of the present invention;

fig. 6(d) is a schematic bottom view of a first loading member according to some embodiments of the present invention;

FIG. 6(e) is an enlarged schematic view of the partial structure B in FIG. 6 (B);

fig. 7(a) is a schematic front view of a second carrier provided according to some embodiments of the present invention;

fig. 7(b) is a schematic right-view of a second carrier provided in accordance with some embodiments of the present invention;

fig. 7(c) is a schematic top view of a second load member provided in accordance with some embodiments of the present invention;

fig. 7(d) is a schematic bottom view of a second load member according to some embodiments of the present invention;

fig. 8(a) is a schematic front view of a first limiting member according to some embodiments of the present invention;

fig. 8(b) is a left side view schematically illustrating a first limiting member according to some embodiments of the present invention;

fig. 8(c) is a schematic top view of a first limiting member according to some embodiments of the present invention;

fig. 8(d) is a schematic bottom view of a first limiting member according to some embodiments of the present invention;

fig. 9 is a schematic view of a selected blade sample on an aircraft engine blade according to some embodiments of the present invention.

The reference numbers in the drawings illustrate the following:

1-a first mount; 11-a first runner; 12-a second runner; 13-a first aperture;

2-a second mounting seat; 21-a third chute; 22-a fourth chute; 23-a second well;

3-a support assembly;

31-a first support; 311-a first slide groove; 312-a support portion of the first support; 313 — a mounting portion of a first support; 314 — a connection portion of a first support; 315-third aperture;

32-a second support; 321-a second slide rail groove; 322-a support portion of the second support; 323-mounting portion of second support; 324 — a connection of a first support; 325-fourth hole;

4-a loading assembly;

41-a first loading member; 411-third slide rail groove; 412-a loading section of a first loader; 413-a mounting portion of the first load member; 414 — a connection portion of the first loading member; 415-fifth hole;

42-a second loading member; 421-a fourth slide rail groove; 422-a loading part of the second loading member; 423-mounting part of the second loading member; 424-the connection of the second load member; 425-sixth hole;

5-a limiting component;

51-a first stop; 511-a limiting part of the first limiting part; 512-mounting part of first limiting member; 513 — a first groove; 514-fifth slide way groove; 515-seventh hole;

52-a second stop;

61-a first elastic member; 62-a second elastic member;

71-a first shaft; 72-a second axis;

8-test bed;

9-a loading arm;

10-blade specimen.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only some of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the invention.

Referring to fig. 1, some embodiments provide an aircraft engine blade testing apparatus comprising a first mount 1, a second mount 2, a support assembly 3 and a loading assembly 4.

The support assembly 3 is provided at the first mount 1 and is configured to support a blade specimen 10. The support assembly 3 includes a first support 31 and a second support 32, each of the first support 31 and the second support 32 includes a support portion that contacts the blade test piece 10, and the support portion of the first support 31 or the second support 32 is configured to be swingable with respect to the first mount 1.

The second mounting base 2 is arranged above the first mounting base 1. The loading assembly 4 is disposed on the second mounting seat 2 and located between the first support 31 and the second support 32, and the loading assembly 4 is configured to apply a load to the blade sample 10.

In some embodiments, the first support 31 and the second support 32 support the blade specimen 10 from the bottom of the blade specimen 10, and the loading assembly 4 applies a load to the blade specimen 10 from the top of the blade specimen 10. And the supporting part of the first supporting part 31 or the second supporting part 32 is configured to be capable of swinging relative to the first mounting seat 1, and the orientation of the supporting part of at least one supporting part can be automatically adjusted along with the deformation of the blade sample 10 in the test process, so that the introduction of additional load caused by the incongruity of the supporting position and the orientation is avoided, and the accuracy of the applied load and the test accuracy are improved.

In some embodiments, a first sliding rail sliding groove structure is arranged between the first mounting seat 1 and the supporting component 3, and the supporting component 3 moves on the first mounting seat 1 through the first sliding rail sliding groove structure to adjust the position of the supporting component 3, and then adjust the supporting position of the blade sample 10, and can be applied to different blade samples 10.

In some embodiments, the first slide rail and slide groove structure includes a first slide groove 11 and a second slide groove 12 provided in the first mounting seat 1, referring to fig. 2(a) and 2(b), and a first slide rail provided in the first support 31 and a second slide rail provided in the second support 32.

Referring to fig. 4(b) and 4(d), the bottom of the first support 31 is provided with a first slide rail slot 311, and the first slide rail slot 311 is used for mounting a first slide rail. Referring to fig. 5(b) and 5(d), a second rail groove 321 is provided at the bottom of the second support member 32, and the second rail groove 321 is used for mounting a second rail.

Referring to fig. 2(a) and 2(b), the first chute 11 and the second chute 12 are parallel to each other and each extend in the longitudinal direction of the blade sample 10. The first supporting member 31 moves along the first mounting seat 1 through the cooperation of the first sliding rail and the first sliding chute 11, so as to adjust the position of the first supporting member 31 on the first mounting seat 1. The second supporting member 32 moves along the first mounting seat 1 through the cooperation of the second sliding rail and the second sliding chute 12, so as to adjust the position of the second supporting member 32 on the first mounting seat 1.

In some embodiments, referring to fig. 1, the loading assembly 4 comprises a first loading member 41 and a second loading member 42, each of the first loading member 41 and the second loading member 42 comprises a loading portion in contact with the blade specimen 10, and the loading portion of the first loading member 41 or the second loading member 42 is configured to be swingable with respect to the second mount 2.

In some embodiments, the blade test specimen 10 is supported by the first support 31 and the second support 32, and loaded by the first loading member 41 and the second loading member 42, for performing a four-point bending test on the blade test specimen 10. And the supporting part of one of the first supporting piece 31 and the second supporting piece 32 can swing relative to the first mounting seat 1, and the loading part of one of the first loading piece 41 and the second loading piece 42 can swing relative to the second mounting seat 2, so that the supporting point position and the loading point position can be automatically adjusted along with the deformation of the blade test sample 10 in the test process, the introduction of improper load is avoided, and the test effectiveness is improved.

In some embodiments, a second slide rail sliding groove structure is arranged between the second mounting seat 2 and the loading assembly 4, and the loading assembly 4 moves on the second mounting seat 2 through the second slide rail sliding groove structure to adjust the position of the loading assembly 4, so as to be suitable for blade samples 10 with different shapes.

In some embodiments, the second slide rail sliding groove structure includes a third sliding groove 21 and a fourth sliding groove 22 provided in the second mounting base 2, referring to fig. 3(a) and 3(b), and a third slide rail provided in the first loader 41 and a fourth slide rail provided in the second loader 42.

Referring to fig. 6(b) and 6(c), the first loader 41 is provided with a third slide rail slot 411, and the third slide rail slot 411 is used to mount a third slide rail. Referring to fig. 7(b) and 7(c), the second loading member 42 is provided with a fourth slide rail groove 421, and the fourth slide rail groove 421 is used for mounting a fourth slide rail.

Referring to fig. 3(a) and 3(b), the third chute 21 and the fourth chute 22 are parallel to each other and each extend in the longitudinal direction of the blade sample 10. The first loading member 41 moves along the second mounting seat 2 by the cooperation of the third slide rail and the third slide groove 21, so as to adjust the position of the first loading member 41. The second loading member 42 moves along the second mounting seat 2 through the cooperation of the fourth slide rail and the fourth slide groove 22, so as to adjust the position of the second loading member 42.

In some embodiments, referring to fig. 1, the aircraft engine blade testing apparatus further includes a limiting assembly 5, the limiting assembly 5 is disposed on the first mounting base 1 and located between the first support 31 and the second support 32, and the limiting assembly 5 is configured to limit the blade test specimen 10 from swinging relative to the first mounting base 1.

In some embodiments, the limiting assembly 5 includes a first limiting member 51 and a second limiting member 52, and the tops of the first limiting member 51 and the second limiting member 52 are both provided with a groove for limiting the blade sample 10, referring to fig. 8(b), for example: the top of the first limiting member 51 is provided with a first groove 513, the blade sample 10 passes through the first groove 513, and the side walls on both sides of the first groove 513 limit the blade sample 10 from the width direction of the blade sample 10, so as to prevent the blade sample 10 from moving in the width direction.

In some embodiments, a third sliding rail and sliding groove structure is disposed between the first mounting seat 1 and the limiting assembly 5, and the limiting assembly 5 moves on the first mounting seat 1 through the third sliding rail and sliding groove structure to adjust the position of the limiting assembly 5.

In some embodiments, the limiting assembly 5 includes a first limiting member 51 and a second limiting member 52, and the third slide rail and slide rail structure includes a first slide rail 11 and a second slide rail 12 disposed on the first mounting base 1, referring to fig. 2(a) and fig. 2(b), and a fifth slide rail disposed on the first limiting member 51 and a sixth slide rail disposed on the second limiting member 52.

Referring to fig. 8(b) and 8(d), a fifth slide rail groove 514 is disposed at the bottom of the first limiting member 51, and the fifth slide rail groove 514 is used for installing a fifth slide rail. The structure of the second limiting member 52 is similar to that of the first limiting member 51, and similarly, a sixth slide rail groove is disposed at the bottom of the second limiting member 52, and is used for installing a sixth slide rail.

The first sliding groove 11 and the second sliding groove 12 in the third sliding rail sliding groove structure are respectively the same sliding groove as the first sliding groove 11 and the second sliding groove 12 in the first sliding rail sliding groove structure, and referring to fig. 2(a) and 2(b), the first sliding groove 11 and the second sliding groove 12 are parallel to each other and both extend along the length direction of the blade sample 10. The first limiting member 51 moves along the first mounting base 1 through the cooperation of the fifth slide rail and the first slide groove 11, so as to adjust the position of the first limiting member 51. The second limiting member 52 moves along the first mounting base 1 through the cooperation between the sixth slide rail and the second slide groove 12, so as to adjust the position of the second limiting member 52.

Referring to fig. 5(a), 5(b) and 5(c), the second support member 32 includes a mounting portion 323 and a supporting portion 322, the mounting portion 323 of the second support member 32 is provided to the first mounting seat 1, and the supporting portion 322 of the second support member 32 is rotatably provided with respect to the mounting portion 323 of the second support member 32.

The supporting portion 322 of the second support member 32 has a smaller size than the mounting portion 323 along the length direction of the blade sample 10. Optionally, a connecting portion 324 is disposed between the mounting portion 323 and the supporting portion 322 of the second support 32, and the connecting portion 324 is used for transitionally connecting the mounting portion 323 and the supporting portion 322. Of course, the connection portion 324 is provided integrally with the mounting portion 323, and the connection portion 324 may belong to the mounting portion 323.

Referring to fig. 5(b), a first elastic member 61 is disposed between the mounting portion 323 and the supporting portion 322 of the second supporting member 32, and the mounting portion 323 and the supporting portion 322 of the second supporting member 32 are rotatably connected by a first shaft 71.

Optionally, the first elastic member 61 comprises a spring, for example: c-shaped springs are arranged on two sides of the first shaft 71, and the C-shaped springs are fixed on the mounting portion 323 and the supporting portion 322 of the second supporting member 32, referring to fig. 5 (e).

The second supporting member 32 is an adjustable supporting member, the supporting portion 322 of the second supporting member 32 can rotate relative to the mounting portion 323 through the first shaft 71, and the degree of rotation of the supporting portion 322 of the second supporting member 32 is limited by the C-shaped springs on both sides of the first shaft 71.

In some embodiments, referring to fig. 1, the first support 31, the first loading member 41, the second loading member 42, and the second support 32 are sequentially disposed along the length extension direction of the blade sample 10, and the support portion of the second support 32 is configured to be swingable with respect to the first mount 1, and the loading portion of the first loading member 41 is configured to be swingable with respect to the second mount 2.

That is to say, the first supporting member 31 is a fixed supporting member, the second supporting member 32 is an adjustable supporting member, the first loading member 41 is an adjustable loading member, the second loading member 42 is a fixed loading member, and the four-point bending test device is suitable for carrying out a four-point bending test on a non-standard blade sample 10 with hyperboloid characteristics.

In some embodiments, referring to fig. 6(a) and 6(b), the first loading member 41 includes a mounting portion 413 and a loading portion 412, the mounting portion 413 of the first loading member 41 is provided to the second mounting seat 2, and the loading portion 412 of the first loading member 41 is rotatably provided with respect to the mounting portion 413 of the first loading member 41.

In some embodiments, referring to fig. 6(b), a second elastic member 62 is disposed between the mounting portion 413 and the loading portion 412 of the first loading member 41, and the mounting portion 413 and the loading portion 412 of the first loading member 41 are rotatably connected by a second shaft 72.

Optionally, the second elastic member 62 comprises a spring, for example: c-shaped springs are arranged on two sides of the second shaft 72, and the C-shaped springs are respectively fixed on the mounting part 413 and the loading part 412 of the first loading piece 41, referring to fig. 6 (e).

The first loading member 41 is an adjustable loading member, the loading portion 412 of the first loading member 41 can rotate relative to the mounting portion 413 through the second shaft 72, and the degree of rotation of the loading portion 412 of the first loading member 41 is limited by the C-shaped springs on both sides of the second shaft 72.

In some embodiments, the supporting portions of the first and

second supports

31 and 32 are configured as an arc shape adapted to the profile shape of the blade specimen 10 to facilitate uniform contact of the supporting portions with the blade specimen 10; referring to fig. 4(a) and 4(b), and fig. 5(a) and 5(b), the supporting portions of the first and

second supports

31 and 32 are configured in an arc shape, and the top portions thereof are obliquely arranged to be adapted to the profile of the blade test specimen 10. The loading portions of the first and

second loading members

41 and 42 are configured in an arc shape adapted to the shape of the blade specimen 10 to facilitate uniform contact of the loading portions with the blade specimen 10; referring to fig. 6(a) and 6(b), and fig. 7(a) and 7(b), the loading portions of the first and

second loading members

41 and 42 are configured in an arc shape, and the top portions thereof are obliquely arranged to match the profile of the blade sample 10.

In some embodiments, referring to fig. 1, the aircraft engine blade testing apparatus further comprises a test stand 8, and the first mounting base 1 is provided on the test stand 8.

The aircraft engine blade test device further comprises a loading arm 9, and the second mounting seat 2 is arranged on the loading arm 9.

An embodiment of the aircraft engine blade testing apparatus is described in detail below with reference to fig. 1 to 9.

As shown in fig. 1, the aircraft engine blade testing device includes a test bed 8, a first mounting base 1 is disposed on the test bed 8, and a first supporting member 31, a first limiting member 51, a second limiting member 52, and a second supporting member 32 are sequentially disposed on the first mounting base 1 along a length extending direction of a blade sample 10. The first support 31 and the second support 32 are used to contact the bottom of the blade sample 10 to support the blade sample 10. The first stopper 51 and the second stopper 52 are used to limit the width direction of the blade sample 10, and prevent the blade sample 10 from moving in the width direction.

The aero-engine blade test device further comprises a loading arm 9, the loading arm 9 is arranged above the test bed 8, the second mounting seat 2 is arranged on the loading arm 9, the first loading piece 41 and the second loading piece 42 are arranged on the second mounting seat 2 at intervals, and the first loading piece 41 and the second loading piece 42 are arranged between the first limiting piece 51 and the second limiting piece 52 and are used for being in contact with the top of the blade sample 10 to load the blade sample 10.

Wherein, the supporting part of the first supporting member 31 is fixed, and the supporting part of the second supporting member 2 can swing relative to the first mounting seat 1, so as to adjust the supporting position according to the profile and loading deformation of the blade sample 10, and the like, and fully contact with the surface of the blade sample 10. The loading part of the first loading member 41 can swing relative to the second mounting seat 2, and the loading part of the second loading member 42 is fixed so as to adapt to the profile of the blade sample 10 and be fully contacted with the surface of the blade sample 10 to carry out loading.

As shown in fig. 2(a), the first mounting base 1 has a rectangular parallelepiped structure, and a first sliding groove 11 and a second sliding groove 12 that are parallel to each other are provided on the first mounting base 1. The first sliding chute 11 is used for being matched with the sliding rails at the bottoms of the first supporting member 31 and the first limiting member 51 to guide the movement of the first supporting member 31 and the first limiting member 51. The second sliding chute 12 is used for being matched with the sliding rails at the bottoms of the second supporting member 32 and the second limiting member 52, and guiding the movement of the second supporting member 32 and the second limiting member 52. Set up first hole 13 between first spout 11 and the second spout 12, first hole 13 is used for wearing to establish the bolt in order to install first mount pad 1 on test bench 8.

As shown in fig. 2(b), the first and

second chutes

11 and 12 have a trapezoidal cross section.

As shown in fig. 3(a), the second mounting base 2 has a rectangular parallelepiped structure, and the second mounting base 2 is provided with a third slide groove 21 and a fourth slide groove 22 which are parallel to each other. The third slide groove 21 is used for being matched with a slide rail at the bottom of the first loading member 41 to guide the movement of the first loading member 41. The fourth slide groove 22 is used for cooperating with a slide rail at the bottom of the second loading member 42 to guide the movement of the second loading member 42. A second hole 23 is arranged between the third sliding chute 21 and the fourth sliding chute 22, and the second hole 23 is used for penetrating a bolt to install the second installation seat 2 on the loading arm 9.

As shown in fig. 3(b), the third chute 21 and the fourth chute 22 have a trapezoidal cross section.

As shown in fig. 4(a), the first support 31 includes a support portion 312 contacting the blade sample 10, and a mounting portion 313 mounted on the first mounting seat 1, and the first support 31 further includes a connecting portion 314, the support portion 312 has a smaller dimension in the length direction of the blade sample 10 than the mounting portion 313, and the connecting portion 314 is used for excessively connecting the support portion 312 and the mounting portion 313. The supporting portion 312, the connecting portion 314, and the mounting portion 313 of the first support 31 are integrally formed. The top of the support 312 is curved to match the profile of the blade specimen 10.

As shown in fig. 4(b), the top of the supporting portion 312 of the first supporting member 31 is inclined to match the profile of the blade specimen 10, so as to facilitate substantially uniform contact with the blade specimen 10. The bottom of the mounting portion 313 of the first support 31 is provided with a first slide rail slot 311, the first slide rail slot 311 is used for mounting a first slide rail, and the first slide rail is matched with the first sliding groove 11 for sliding.

As shown in fig. 4(c), two third holes 315 are spaced from each other in the mounting portion 313 of the first support 31, and after the position of the first support 31 is adjusted, the third holes 315 are used for inserting bolts to fix the first support 31 on the first mounting base 1.

As shown in fig. 4(d), one of the third holes 315 is located in the first rail groove 311.

As shown in fig. 5(a), the second support member 32 includes a support portion 322 contacting the blade sample 10, and a mounting portion 323 mounted on the first mounting seat 1, and the second support member 32 further includes a connecting portion 324, the support portion 322 has a smaller dimension in the length direction of the blade sample 10 than the mounting portion 323, and the connecting portion 324 is used to excessively connect the support portion 322 and the mounting portion 323. The supporting portion 322 of the second support 32 is rotatable with respect to the mounting portion 323. The top of the supporting portion 322 is arc-shaped to match the profile of the blade sample 10.

As shown in fig. 5(b), the top of the supporting portion 322 of the second supporting member 32 is inclined to match the profile of the blade sample 10, so as to facilitate substantially uniform contact with the blade sample 10. The supporting portion 322 and the connecting portion 324 of the second supporting member 32 are rotatably connected by a first shaft 71, first elastic members 61 are disposed on two sides of the first shaft 71, and the first elastic members 61 are located between the supporting portion 322 and the connecting portion 324 of the second supporting member 32. The supporting portion 322 of the second supporting member 32 rotates relative to the mounting portion 323 by the first shaft 71, and the degree of rotation is limited by the first elastic members 61 at both sides of the first shaft 71. This ensures that the orientation of the support portion 322 of the second support 32 is adjusted with changes in the blade specimen 10 during loading, thereby avoiding additional loads introduced by inconsistencies in support position and orientation. The bottom of the mounting portion 323 of the second support member 32 is provided with a second slide rail groove 321, the second slide rail groove 321 is used for mounting a second slide rail, and the second slide rail slides in cooperation with the second sliding groove 12.

As shown in fig. 5(c), two fourth holes 325 are provided at an interval in the mounting portion 323 of the second support member 32, and after the position adjustment of the second support member 32 is completed, the fourth holes 325 are used for inserting bolts to fix the second support member 32 on the first mounting base 1.

As shown in fig. 5(d), one of the fourth holes 325 is located in the second rail groove 321.

As shown in fig. 5(e), the first elastic member 61 disposed between the supporting portion 322 and the connecting portion 324 of the second supporting member 32 is a C-shaped spring, one side of the C-shaped spring is fixed to the supporting portion 322, and the other side of the C-shaped spring is fixed to the connecting portion 324.

As shown in fig. 6(a), the first loading member 41 includes a loading portion 412 contacting with the blade sample 10, and a mounting portion 413 mounted on the second mounting seat 2, and the first loading member 41 further includes a connecting portion 414, the loading portion 412 has a smaller dimension in the length direction of the blade sample 10 than the mounting portion 413, and the connecting portion 414 is used for excessively connecting the loading portion 412 and the mounting portion 413. The loading portion 412 of the first loading member 41 is rotatable with respect to the mounting portion 413. The bottom of the loading part 412 is arc-shaped and is matched with the profile of the blade sample 10.

As shown in fig. 6(b), the bottom of the loading part 412 of the first loading member 41 is provided with an inclined shape to match the profile of the blade sample 10, so as to facilitate substantially uniform contact with the blade sample 10. The loading portion 412 and the connecting portion 414 of the first loading member 41 are rotatably connected through the second shaft 72, the second elastic member 62 is disposed on two sides of the second shaft 72, and the second elastic member 62 is located between the loading portion 412 and the connecting portion 414 of the first loading member 41. The loading portion 412 of the first loading member 41 is rotated relative to the mounting portion 413 by the second shaft 72, and the degree of rotation is limited by the second elastic members 62 on both sides of the second shaft 72. This ensures that the orientation of the loading portion 412 of the first loading member 41 is adjusted with the blade specimen 10 during loading, thereby avoiding additional loads introduced by the inconsistency of the support position and orientation. The bottom of the mounting portion 413 of the first loading member 41 is provided with a third slide rail slot 411, the third slide rail slot 411 is used for mounting a third slide rail, and the third slide rail slides in cooperation with the third slide groove 21.

As shown in fig. 6(d), the mounting portion 413 of the first loading member 41 is provided with two fifth holes 415 at intervals, and after the position adjustment of the first loading member 41 is completed, the fifth holes 415 are used for inserting bolts to fix the first loading member 41 on the second mounting base 2.

As shown in fig. 6(c), one of the fifth holes 415 is located in the third slide rail slot 411.

As shown in fig. 6(e), the second elastic member 62 disposed between the loading portion 412 and the connecting portion 414 of the first loading member 41 is a C-shaped spring, one side of which is fixed to the loading portion 412 and the other side of which is fixed to the connecting portion 414.

As shown in fig. 7(a), the second loading member 42 includes a loading portion 422 contacting the blade sample 10, and a mounting portion 423 mounted on the second mounting seat 2, and the second loading member 42 further includes a connecting portion 424, the loading portion 422 has a smaller dimension in the length direction of the blade sample 10 than the mounting portion 423, and the connecting portion 424 is used for excessively connecting the loading portion 422 and the mounting portion 423. The loading portion 422, the connecting portion 424 and the mounting portion 423 of the second loading member 42 are integrally formed. The bottom of the loading part 422 is arc-shaped and is matched with the profile of the blade sample 10.

As shown in fig. 7(b), the bottom of the loading part 422 of the second loading member 42 is provided with an inclined shape to match the profile of the blade sample 10, so as to facilitate substantially uniform contact with the blade sample 10. The mounting portion 423 of the second loading member 42 is provided with a fourth slide rail groove 421, the fourth slide rail groove 421 is used for mounting a fourth slide rail, and the fourth slide rail slides in cooperation with the fourth slide groove 22.

As shown in fig. 7(d), the mounting portion 423 of the second carrier 42 is provided with two sixth holes 425 at intervals, and after the position adjustment of the second carrier 42 is completed, the sixth holes 425 are used for inserting bolts to fix the second carrier 42 on the second mounting base 2.

As shown in fig. 7(c), one of the sixth holes 425 is located in the fourth rail groove 421.

As shown in fig. 8(a), the first stopper 51 includes a stopper portion 511 for stopping the blade sample 10 and a mounting portion 512 for mounting on the first mounting base 1, and the stopper portion 511 has a smaller dimension in the longitudinal direction of the blade sample 10 than the mounting portion 512.

As shown in fig. 8(b), the size of the limiting portion 511 in the width direction of the blade sample 10 is smaller than that of the mounting portion 512, the limiting portion 511 is provided with a first groove 513, and the width of the first groove 513 is slightly larger than that of the blade sample 10 for limiting the normal movement of the blade sample 10. The bottom of installation portion 512 sets up fifth slide rail groove 514, and fifth slide rail groove 514 is used for installing the fifth slide rail, and the fifth slide rail slides with first spout 11 cooperation.

As shown in fig. 8(c), two seventh holes 515 are provided at intervals in the mounting portion 512 of the first limiting member 51, and after the position of the first limiting member 51 is adjusted, the seventh holes 515 are used for inserting bolts to fix the first limiting member 51 on the first mounting base 1.

As shown in fig. 8(d), one of the seventh holes 515 is located in the fifth rail groove 514.

The structure of the second limiting member 52 is similar to that of the first limiting member 51, the second groove provided in the second limiting member 52 limits the position of the blade sample 10, the mounting portion of the second limiting member 52 is provided with a sixth slide rail groove, the sixth slide rail groove is used for mounting a sixth slide rail, and the sixth slide rail slides in cooperation with the second slide groove 12.

As shown in fig. 9, a blade specimen 10 was taken from an aircraft engine blade. For example: jet engine rotor blade for an aircraft.

The aero-engine blade test device provided by the embodiment of the disclosure can carry out a four-point bending test on a non-standard sample with hyperboloid characteristics, and the positions of the supporting points and the loading points in the clamp can be automatically adjusted along with the deformation of the sample in the test process, so that the introduction of additional loads caused by the incongruity of the supporting positions and the positions is avoided, and the accuracy of the loads is ensured.

Wherein, four-point bending test: four-point bend test, a test method for measuring bending properties, has two symmetrical load points above the test specimen and two symmetrical support points below.

In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are only used for the convenience of distinguishing the components, and if not stated otherwise, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.

Furthermore, the technical features of one embodiment may be combined with one or more other embodiments advantageously without explicit negatives.

Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and not for limiting the same; although the present invention has been described in detail with reference to preferred embodiments, it should be understood by those skilled in the art that: the invention can be modified or equivalent substituted for some technical features; without departing from the spirit of the present invention, it should be understood that the scope of the claims is intended to cover all such modifications and variations.

Claims

1. An aircraft engine blade test device, characterized by includes:

a first mounting base (1);

the supporting assembly (3) is arranged on the first mounting seat (1) and is configured to support a blade sample (10); the support assembly (3) comprises a first support (31) and a second support (32), the first support (31) and the second support (32) each comprise a support part in contact with the blade specimen (10), and the support parts of the first support (31) or the second support (32) are configured to be swingable relative to the first mounting seat (1);

the second mounting seat (2) is arranged above the first mounting seat (1); and

a loading assembly (4) provided at the second mount (2) and located between the first support (31) and the second support (32), the loading assembly (4) being configured to apply a load to a blade specimen (10).

2. The aircraft engine blade test device according to claim 1, characterized in that a first slide rail and sliding groove structure is arranged between the first mounting seat (1) and the support component (3), and the support component (3) moves on the first mounting seat (1) through the first slide rail and sliding groove structure to adjust the position of the support component (3).

3. The aircraft engine blade testing device according to claim 2, wherein the first sliding rail and sliding groove structure comprises a first sliding groove (11) and a second sliding groove (12) which are arranged on the first mounting seat (1), a first sliding rail which is arranged on the first supporting piece (31) and a second sliding rail which is arranged on the second supporting piece (32), and the first sliding groove (11) and the second sliding groove (12) are parallel to each other and both extend along the length direction of the blade test piece (10); the first supporting piece (31) moves along the first mounting seat (1) through the matching of the first sliding rail and the first sliding groove (11) so as to adjust the position; the second supporting piece (32) moves along the first mounting seat (1) through the matching of the second sliding rail and the second sliding chute (12) so as to adjust the position.

4. The aircraft engine blade testing device according to claim 1, characterized in that the loading assembly (4) comprises a first loading member (41) and a second loading member (42), the first loading member (41) and the second loading member (42) each comprising a loading portion in contact with the blade specimen (10), the loading portion of the first loading member (41) or the second loading member (42) being configured to be swingable with respect to the second mount (2).

5. The aircraft engine blade testing device according to claim 4, characterized in that a second slide rail and sliding groove structure is arranged between the second mounting seat (2) and the loading assembly (4), and the loading assembly (4) moves on the second mounting seat (2) through the second slide rail and sliding groove structure to adjust the position of the loading assembly (4).

6. The aircraft engine blade testing device according to claim 5, wherein the second sliding rail and sliding groove structure comprises a third sliding groove (21) and a fourth sliding groove (22) which are arranged on the second mounting seat (2), a third sliding rail which is arranged on the first loading piece (41) and a fourth sliding rail which is arranged on the second loading piece (42), and the third sliding groove (21) and the fourth sliding groove (22) are parallel to each other and extend along the length direction of the blade sample (10); the first loading piece (41) moves along the second mounting seat (2) through the matching of the third sliding rail and the third sliding groove (21) so as to adjust the position; the second loading piece (42) moves along the second mounting seat (2) through the matching of the fourth sliding rail and the fourth sliding groove (22) so as to adjust the position.

7. The aircraft engine blade testing device according to claim 1, comprising a limiting assembly (5), wherein the limiting assembly (5) is arranged on the first mounting seat (1) and is located between the first support member (31) and the second support member (32), and the limiting assembly (5) is configured to limit the blade test piece (10) from swinging relative to the first mounting seat (1).

8. The aircraft engine blade testing device according to claim 7, wherein the limiting assembly (5) comprises a first limiting member (51) and a second limiting member (52), and the tops of the first limiting member (51) and the second limiting member (52) are provided with grooves for limiting the blade test sample (10).

9. The aircraft engine blade testing device according to claim 7, wherein a third sliding rail and sliding groove structure which is matched with each other is arranged between the first mounting seat (1) and the limiting assembly (5), and the limiting assembly (5) moves on the first mounting seat (1) through the third sliding rail and sliding groove structure so as to adjust the position of the limiting assembly (5).

10. The aircraft engine blade testing device according to claim 9, wherein the limiting component (5) comprises a first limiting member (51) and a second limiting member (52), the third sliding rail and sliding groove structure comprises a first sliding groove (11) and a second sliding groove (12) which are arranged on the first mounting seat (1), a fifth sliding rail which is arranged on the first limiting member (51) and a sixth sliding rail which is arranged on the second limiting member (52), and the first sliding groove (11) and the second sliding groove (12) are parallel to each other and both extend along the length direction of the blade test sample (10); the first limiting piece (51) moves along the first mounting seat (1) through the matching of the fifth slide rail and the first slide groove (11) so as to adjust the position; the second limiting part (52) moves along the first mounting seat (1) through the matching of the sixth sliding rail and the second sliding groove (12) so as to adjust the position.

11. The aircraft engine blade testing device according to claim 1, wherein the second support member (32) comprises a mounting portion (323) and a support portion (322), the mounting portion (323) of the second support member (32) being provided at the first mounting seat (1), the support portion (322) of the second support member (32) being rotatably provided with respect to the mounting portion (323) of the second support member (32).

12. The aircraft engine blade testing device according to claim 11, wherein a first elastic member (61) is arranged between the mounting portion (323) and the supporting portion (322) of the second supporting member (32), and the mounting portion (323) and the supporting portion (322) of the second supporting member (32) are rotatably connected through a first shaft (71).

13. The aircraft engine blade testing device according to claim 4, wherein a first support member (31), a first loading member (41), a second loading member (42) and a second support member (32) are arranged in this order along the length extension direction of the blade test piece (10), and the support portion of the second support member (32) is configured to be swingable with respect to the first mount (1), and the loading portion of the first loading member (41) is configured to be swingable with respect to the second mount (2).

14. The aircraft engine blade testing device according to claim 4, characterized in that the first loading member (41) comprises a mounting portion (413) and a loading portion (412), the mounting portion (413) of the first loading member (41) being provided at the second mounting seat (2), the loading portion (412) of the first loading member (41) being rotatably provided with respect to the mounting portion (413) of the first loading member (41).

15. The aircraft engine blade testing device according to claim 14, wherein a second elastic member (62) is arranged between the mounting portion (413) and the loading portion (412) of the first loading member (41), and the mounting portion (413) and the loading portion (412) of the first loading member (41) are rotatably connected through a second shaft (72).

16. The aircraft engine blade testing device according to claim 4, characterized in that the support portions of the first support (31) and the second support (32) are configured as arcs adapted to the shape of the blade test specimen (10); the loading portions of the first loading member (41) and the second loading member (42) are configured in an arc shape that matches the shape of the blade sample (10).