CN-224223718-U - Fatigue test fixture for aircraft blade

CN224223718UCN 224223718 UCN224223718 UCN 224223718UCN-224223718-U

Abstract

The utility model discloses an aircraft blade fatigue test fixture, which comprises a clamping mechanism for clamping an engine blade, wherein the clamping mechanism is arranged at the top of a base mechanism, the base mechanism is arranged at the top of a base, and the clamping direction of the clamping mechanism can be adjusted by arranging a positioning base, a sliding base, a limiting block, a fixture positioning frame and other parts in the base mechanism, and by the matching relation of a cross clamping groove formed by the limiting block and a second base and the fixture positioning frame and a positioning column, the fixture positioning frame can be clamped with any group of limiting blocks by rotating 90 degrees. And then reached this device and can pass through the angle modulation function of base mechanism, carried out the effect of different direction fatigue test to aircraft engine blade, promoted the commonality and the test flexibility of anchor clamps.

Inventors

ZHOU XIN
CAO SHAOYI
WEI LAI
LUO CHENYU
HE XIAOJUAN
LI BOHAN
LUO CHUANYUE
FENG YANG
JIN HAO
ZHANG HAO
SHAO JIAQI
SONG ZONGXIAN
ZHENG LANYU
Su Haocheng
SHI TONGYI
WANG JIFENG
WEI YONG
GUO MINGQI
LIU BOHAO
WANG PENG
WANG HAO
LIU JUNJIE
Zhu Angran
ZHANG FUKUAN
DENG JIAXING
GUO XUAN
HAN ZHONGXIAO
JIANG ZHAOWEI
ZHAO CHE
ZHANG JIANQUAN
ZHAN SHENG
CHEN SHUQI
Han Yuehao
GUO QINGYA
ZHOU QIXIANG
LI QIURAN
CHEN XINKUI
WANG XINPENG
LI ZHI
WU JUNJIE
Ruan Peibo
LI JIARUI
YU SONGYANG
WANG DIANQI

Assignees

天津中德应用技术大学

Dates

Publication Date: 20260512
Application Date: 20250616

Claims (7)

1. The aircraft blade fatigue test fixture comprises a clamping mechanism (3) for clamping an engine blade, and is characterized in that the clamping mechanism (3) is arranged at the top of a base mechanism (2), and the base mechanism (2) is arranged at the top of a base (1); Base mechanism (2), base mechanism (2) are including fixed point fixed location base (21) at base (1) top and adjustable fixture (3) clamping direction's slide base (22), slide base (22) are including movable mounting at base (1) top second base (203), be used for restricting reference column (205) of anchor clamps locating rack (207), be used for supporting anchor clamps locating rack (207) of fixture (3) and be used for stopper (206) of firm anchor clamps locating rack (207), stopper (206) include four groups, stopper (206) cooperation second base (203) constitute the cross draw-in groove, anchor clamps locating rack (207) rotatable 90 for adjusting the installation direction of fixture (3).
2. The aircraft blade fatigue test fixture according to claim 1, wherein the clamping mechanism (3) comprises a first transverse clamp (31) arranged at the top of the positioning base (21), a second transverse clamp (32) arranged at the top of the sliding base (22) and a standby longitudinal clamp (33), the first transverse clamp (31), the second transverse clamp (32) and the longitudinal clamp (33) comprise a second side plate (301) for fixedly mounting a sliding seat (302), a sliding seat (302) for movably mounting a clamping plate (304) and a bidirectional bolt rod (303) for driving the clamping plate (304) to clamp a blade, one side of the clamping plate (304) is in threaded connection with a secondary jacking rod (305), the secondary jacking rod (305) comprises a screw rod, a spherical jacking block and an inner hexagon nut, the spherical jacking block is used for clamping a wavy groove of a blade root, one side of the clamping plate (304) is fixedly connected with an inner threaded slider (306), and the inner threaded slider (306) is movably mounted on one side of the sliding seat (302).
3. The aircraft blade fatigue test fixture according to claim 1, wherein the positioning base (21) comprises a first base (201) fixedly installed on the top of the base (1) and first side plates (202) fixedly connected to the left side and the right side of the first base (201), and the first side plates (202) are used for fixedly installing the first transverse fixture (31).
4. The aircraft blade fatigue test fixture according to claim 1, wherein the top of the second base (203) is provided with clamping holes (204) for plugging in clamping blocks at the bottom of the limiting blocks (206), the top of the fixture locating rack (207) is provided with limiting holes (208) in a penetrating mode for being matched with the locating column (205) to fixedly install the fixture locating rack (207), and one side of the fixture locating rack (207) is fixedly connected with a cushion block (209) for being connected with an output end of the fatigue test machine.
5. The aircraft blade fatigue test fixture according to claim 1 or 2, wherein one side of the fixture locating frame (207) is provided with fixture mounting holes (310) for fixedly mounting the second side plate (301) by matching with bolts.
6. An aircraft blade fatigue test fixture according to claim 2, wherein the carriages (302) inside the first and second transverse fixtures (31, 32) are arranged transversely, and the carriages (302) inside the longitudinal fixtures (33) are arranged longitudinally.
7. The aircraft blade fatigue test fixture according to claim 1, wherein the fixture positioning frame (207) is matched with any group of limiting blocks (206) in the cross-shaped clamping groove through rotation selection, so that 90-degree interval angular positioning is realized.

Description

Fatigue test fixture for aircraft blade Technical Field The utility model relates to the technical field of aerospace manufacturing, in particular to an aircraft blade fatigue test fixture. Background The aircraft engine blade is used as a core component of an aircraft engine and continuously operates under the extreme working conditions of high temperature, high pressure and high rotating speed, so that fatigue damage is very easy to generate. The fatigue test is a key link for evaluating the performance of the blade and guaranteeing the flight safety, and the result directly influences the reliability and the service life of the aircraft engine. At present, the conventional fatigue test clamp for the aircraft blade has a plurality of problems in practical application. Part of the clamps are single in structure, the clamping angle and direction of the blades cannot be flexibly adjusted, complex stress states of the blades in the engine are difficult to simulate, and large deviation exists between a test result and an actual working condition. Meanwhile, the fixing effect of the existing clamping mode on the blade is poor, the condition that the blade loosens or even falls off easily occurs in the fatigue test process of long-time high frequency, the accuracy of test data is affected, and potential safety hazards exist. In addition, the traditional clamp is complex in operation in terms of component replacement and maintenance, so that the testing cost and the time cost are increased, and the testing efficiency is reduced. For the problems in the related art, no effective solution has been proposed at present. Disclosure of utility model Aiming at the problems in the related art, the utility model provides an aircraft blade fatigue test fixture, which aims to overcome the technical problems in the prior art. For this purpose, the utility model adopts the following specific technical scheme: The fixture comprises a clamping mechanism for clamping an engine blade, wherein the clamping mechanism is arranged at the top of a base mechanism, and the base mechanism is arranged at the top of a base; The base mechanism comprises a positioning base fixed on the top of the base and a sliding base capable of adjusting the clamping direction of the clamping mechanism, wherein the sliding base comprises a second base movably installed on the top of the base, a positioning column used for limiting the positioning frame of the clamp, a clamp positioning frame used for supporting the clamping mechanism and a limiting block used for stabilizing the clamp positioning frame, the limiting block comprises four groups, the limiting block is matched with the second base to form a cross clamping groove, and the clamp positioning frame can rotate by 90 degrees and is used for adjusting the installation direction of the clamping mechanism. Optionally, fixture is including setting up at the first horizontal anchor clamps at positioning base top, setting up at the second horizontal anchor clamps and the reserve longitudinal clamp at sliding base top, first horizontal anchor clamps, second horizontal anchor clamps and longitudinal clamp all including the second curb plate that is used for the fixed mounting slide, the slide that is used for movable mounting splint and the two-way bolt pole that is used for driving splint centre gripping blade, the secondary roof pressure pole has been cup jointed to one side screw thread of splint, two-way bolt pole drive splint move in opposite directions or dorsad, realizes the quick clamp and the unclamp of blade, the secondary roof pressure pole includes screw rod, spherical roof pressure piece and hexagon socket head cap, and the spherical roof pressure pole screw rod + spherical roof pressure piece, adaptation blade root wave recess, reinforcing centre gripping stability, spherical roof pressure piece is used for the wave recess of centre gripping blade root, one side fixedly connected with internal thread slider of splint, internal thread slider movable mounting is in one side of slide. Optionally, the positioning base includes the first base of fixed mounting at the base top and the first curb plate of fixed connection in first base left and right sides, first curb plate is used for the first horizontal anchor clamps of fixed mounting. Optionally, the clamping hole has all been seted up at the top of second base for peg graft the fixture block of stopper bottom, the limiting hole has been seted up in the top penetration of anchor clamps locating rack for cooperation reference column fixed mounting anchor clamps locating rack, the reference column restriction anchor clamps locating rack's removal, ensure test position precision, one side fixedly connected with cushion of anchor clamps locating rack is used for connecting the output of fatigue testing machine. Optionally, the anchor clamps mounting hole has all been seted up to one side of anchor clamps locating rack for cooperation bolt fixed mou