CN110435924A - Blade of aviation engine bird impact tests simulate fixture - Google Patents
Blade of aviation engine bird impact tests simulate fixture Download PDFInfo
- Publication number
- CN110435924A CN110435924A CN201910736330.XA CN201910736330A CN110435924A CN 110435924 A CN110435924 A CN 110435924A CN 201910736330 A CN201910736330 A CN 201910736330A CN 110435924 A CN110435924 A CN 110435924A
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- bracket
- plate
- blade
- convex shoulder
- lower bracket
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- 238000009863 impact test Methods 0.000 title claims abstract description 20
- 238000012360 testing method Methods 0.000 claims abstract description 26
- 238000003556 assay Methods 0.000 claims abstract description 21
- 238000009434 installation Methods 0.000 claims description 4
- 230000002035 prolonged effect Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 10
- 238000004088 simulation Methods 0.000 abstract description 10
- 230000008569 process Effects 0.000 abstract description 7
- 238000013461 design Methods 0.000 description 7
- 238000011161 development Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000013401 experimental design Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application belongs to aero-engine bird impact tests technical field, and in particular to a kind of blade of aviation engine bird impact tests simulation fixture.The simulation fixture includes that upper bracket, lower bracket, mounting base and convex shoulder bracket, lower bracket are fixedly connected with testing stand, and upper bracket is slidably arranged on the side plate of lower bracket, and for adjusting the height of upper bracket, mounting base is rotatably arranged on lower bracket；Convex shoulder holder pivots are arranged on upper bracket, and convex shoulder bracket has the L-type supporting plate extended at the convex shoulder of leaf assay part two sides, and the end of L-type supporting plate can be acted on to the convex shoulder of leaf assay part, and drive twist blade testpieces.As long as the circumferential setting angle of simulation fixture the adjustment mounting base and lower bracket of the application, blade can be changed and meet angle to bird, it is not required to dismount testpieces blade again, it can be realized quick and easy operation, simultaneously, by adjusting the circumferential setting angle of convex shoulder bracket and upper supporting plate, the torsion situation of blade in the practical work process of blade can be simulated.
Description
Technical field
The application belongs to aero-engine bird impact tests technical field, in particular to a kind of blade of aviation engine bird hits examination
Test simulation fixture.
Background technique
Aero-engine bird hits the major accident for always seriously endangering Flight Safety, after aero-engine bird is hit,
Flying bird can strike the fan rotor blade of engine intake first, and blade is caused to generate recess, deformation, tearing crackle, chip off-falling
It is even broken, and causes a series of secondary damage, blade aerodynamic performance is caused to decline, motor power reduces, and damage is started
Machine, engine misses, broken blade even puncture casing and fly out, directly endanger passenger safety, fatal crass occurs, generate huge
Economic loss.With the promotion of reseach of engine technology, advanced engine blower rotor blade is towards high efficiency thin thickness, whole
The development of body leaf dish, the anti-bird collisions reduced capability of blade, bird hits rear bring maintenance cost and increases, while military-civil aviation industry
Development, environmentally friendly dynamics increase, cause aircraft flight number, when number and bird quantity it is more and more, aero-engine bird is hit
Probability and number be also significantly increased, in order to guarantee flight safety and economy, the engine design phase carry out fan propeller
The anti-bird collisions ability design of blade becomes a content of crucial importance in Modern Engine design with assessment.
In the anti-bird collisions ability design of aero-engine with assessment, bird impact tests are most important means in design evaluation
One of, and bird impact tests include that single blade part grade bird impact tests, whole grade fan part grade bird impact tests and complete machine gulp down bird examination
It tests, ministerial level grade is tested and overall test is at high cost, risk is big, the period is long, limits the number of test, the opposite examination of part grade test
Test that cost is small, risk is low, experimental condition is required it is low, therefore become the anti-bird collisions ability design of aero-engine in assessment
Important means.In actual application, lack single blade part grade bird impact tests energy under rotating condition due to domestic at present
Power, therefore single blade part grade bird impact tests under main development stationary state, test process and method are as follows: by single blade
It is fixed on testing stand, by bird big gun according to certain speed launching simulation bird, strikes with blade and blade.
Blade is fixed on test platform, and the speed of bird and the revolving speed correlation of engine are considered when experimental design, is needed
It will be according to different angle to blade launching simulation bird, since bird big gun is fixed, it is therefore desirable to constantly adjustment blade meets the angle to bird,
That is moving blade, adjustment requires on testing stand disassembly, installs fixture and blade again, process every time under prior art
Complexity, the period is long, while may cause that angle Adjustment precision is insufficient, tenon clamping rigidity changes, and influences test accuracy.Separately
Outside for band convex shoulder fan rotor blade, mid-span shroud is mutually held out against in real process, and blade stiffness increases considerably, and existing
Testing program in, convex shoulder is in free state, can not consider that convex shoulder holds out against the blade stiffness humidification of generation, can not be to leaf
Piece is reversed, and causes test result and actual conditions difference huge.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of blade of aviation engine bird impact tests moulds
Quasi- fixture, comprising:
Lower bracket is fixedly connected with testing stand, two side plates for having bottom plate and upwardly extending perpendicular to the testing stand,
There is first annular hole on the bottom plate；
Upper bracket is slidably arranged on the side plate of the lower bracket, and upper bracket includes the upper plate parallel with the bottom plate, institute
Stating has the second looping pit on upper plate；
Mounting base is rotatably arranged on the bottom plate of the lower bracket, and mounting base passes through the spiral shell across the first annular hole
Bolt is fixed on the lower bracket, and the tongue-and-groove of installation leaf assay part tongue portion is provided in the mounting base；
Convex shoulder bracket is rotatably arranged on the upper plate of the upper bracket, and convex shoulder bracket is by passing through second looping pit
Bolt be fixed on the upper bracket, convex shoulder bracket, which has, extends to two L-type supporting plates at the convex shoulder of leaf assay part two sides,
When the convex shoulder bracket is rotated relative to the upper bracket, the end of the L-type supporting plate can act on convex to leaf assay part
On shoulder, and reverse the leaf assay part.
Preferably, there is strip-shaped hole along the vertical direction, the upper bracket has in institute on the side plate of the lower bracket
The slide plate of the vertical extension in upper plate end is stated, slide plate fitting is arranged on two side plates, by the spiral shell for passing through the strip-shaped hole on side plate
Upper bracket and lower bracket are fixed bolt.
Preferably, the back plate connections of the mounting base and the lower bracket are provided with fin, have on the fin
The mounting base is fixed on the bottom plate by bolt hole after bolt passes through the bolt hole and the first annular hole.
Preferably, lower bracket also has the lower plate for being parallel to the bottom plate, connects by the way that lower plate and the testing stand are fixed
It connects.
Preferably, convex shoulder bracket includes upper ring plate, and two L-type supporting plates respectively include extending downwardly from upper ring plate anchor ring
Vertical plate, and the level board extended from vertical plate end cross, the end abutment of the level board is in the leaf assay part
Convex shoulder on.
Preferably, the end of the level board is fixedly connected with the convex shoulder of the leaf assay part.
As long as the circumferential setting angle of simulation fixture the adjustment mounting base and lower bracket of the application, so that it may change blade and meet
It to the angle of bird, is not required to dismount testpieces blade again, can be realized quick and easy operation, meanwhile, by adjusting convex shoulder branch
The circumferential setting angle of frame and upper supporting plate can simulate the blade twist situation in the practical work process of blade.
The application by convex shoulder bracket be sized to guarantee test part blade install rigidity it is constant.
Detailed description of the invention
Fig. 1 is the blade installation signal of an embodiment of the application blade of aviation engine bird impact tests simulation fixture
Figure.
Fig. 2 is the convex shoulder supporting structure schematic diagram of the application embodiment illustrated in fig. 1.
Wherein, 1- lower bracket, 2- upper bracket, 3- mounting base, 4- convex shoulder bracket, 5- leaf assay part, 11- bottom plate, the side 12-
Plate, 13- lower plate, 21- upper plate, 22- slide plate, 31- tongue-and-groove, 32- fin, 41-L type supporting plate, 42- upper ring plate.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction with the application embodiment
In attached drawing, the technical solution in the application embodiment is further described in more detail.In the accompanying drawings, identical from beginning to end
Or similar label indicates same or similar element or element with the same or similar functions.Described embodiment is
A part of embodiment of the application, rather than whole embodiments.Embodiment below with reference to attached drawing description is to show
Example property, it is intended to for explaining the application, and should not be understood as the limitation to the application.Based on the embodiment in the application,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts belongs to this
Apply for the range of protection.Presently filed embodiment is described in detail with reference to the accompanying drawing.
As shown in Figure 1, this application provides a kind of blade of aviation engine bird impact tests to simulate fixture, comprising:
Lower bracket 1, is fixedly connected with testing stand, with bottom plate 11 and two sides upwardly extended perpendicular to the testing stand
Plate 12 has first annular hole on the bottom plate 11；
Upper bracket 2 is slidably arranged on the side plate 12 of the lower bracket 1, and upper bracket 2 includes parallel with the bottom plate 11
Upper plate 21 has the second looping pit on the upper plate 21；
Mounting base 3 is rotatably arranged on the bottom plate 11 of the lower bracket 1, and mounting base 3 is by passing through the first annular hole
Bolt be fixed on the lower bracket 1, be provided in the mounting base 3 installation 5 tongue portion of leaf assay part tongue-and-groove
31；
Convex shoulder bracket 4 is rotatably arranged on the upper plate 21 of the upper bracket 2, and convex shoulder bracket 4 is by passing through second ring
The bolt in shape hole is fixed on the upper bracket 2, and convex shoulder bracket 4 has two L extended at 5 two sides convex shoulder of leaf assay part
Type supporting plate 41, when the convex shoulder bracket 4 is rotated relative to the upper bracket 2, the end of the L-type supporting plate 41 can be acted on to leaf
On the convex shoulder of piece testpieces 5, and reverse the leaf assay part 5.
In the present embodiment, tongue-and-groove is designed according to blade tenon, for fixing testpieces blade.
In the present embodiment, the L-type supporting plate 41 of convex shoulder bracket 4 is connected according to testpieces shoulder form, size with practical convex shoulder
The size of rigidity Design installing arm is held out against with convex shoulder cooperation when test.
During actual tests, mounting base is fixed with leaf assay part, by adjusting mounting base downside and lower bracket
Circumferential setting angle quickly adjusts blade circumferential direction angle；Upper bracket two sides installing arm is connect by bolt with lower bracket, and energy
It is enough that upper supporting plate height is adjusted according to testpieces blade height, if blade does not have convex shoulder structure, bracket and convex can not be installed
Shoulder bracket；By adjusting, with upper bracket circumferential direction angle, the blade torsion simulated in convex shoulder real process fills situation on the upside of convex shoulder bracket,
According to testpieces mid-span shroud shape and size, the shape and size on the downside of convex shoulder bracket are designed.
In addition, the application uses Finite Element Simulation method, the L-type branch board size of convex shoulder bracket is designed, such as Fig. 2 institute
Show, to simulate the coupling stiffness of convex shoulder in real work.
There is strip-shaped hole along the vertical direction in some optional embodiments, on the side plate 12 of the lower bracket 1, it is described
Upper bracket has the slide plate 22 in the vertical extension in 21 end of upper plate, and the fitting of slide plate 22 is arranged on two side plates 12, passes through
Upper bracket and lower bracket are fixed the bolt of strip-shaped hole on side plate 12.
In some optional embodiments, the mounting base 3 and 11 junction of bottom plate of the lower bracket 1 are provided with fin
32, after there is on the fin 32 bolt hole, bolt to pass through the bolt hole and the first annular hole, by the mounting base 3
It is fixed on the bottom plate 11.
In some optional embodiments, lower bracket 1 also has the lower plate 13 for being parallel to the bottom plate 11, passes through lower plate 13
It is fixedly connected with the testing stand.
In some optional embodiments, as shown in Fig. 2, convex shoulder bracket 4 includes upper ring plate 42, two L-type supporting plates 41 are each
From including the vertical plate extended downwardly from upper ring plate anchor ring, and the level board extended from vertical plate end cross, the level
The end abutment of plate is on the convex shoulder of the leaf assay part 5.
In some optional embodiments, the end of the level board is fixedly connected with the convex shoulder of the leaf assay part 5.
As long as the circumferential setting angle of simulation fixture the adjustment mounting base and lower bracket of the application, so that it may change blade and meet
It to the angle of bird, is not required to dismount testpieces blade again, can be realized quick and easy operation, meanwhile, by adjusting convex shoulder branch
The circumferential setting angle of frame and upper supporting plate can simulate the blade twist situation in the practical work process of blade.
The application by convex shoulder bracket be sized to guarantee test part blade install rigidity it is constant.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, should all contain
Lid is within the scope of protection of this application.Therefore, the protection scope of the application should be based on the protection scope of the described claims.
Claims (6)
1. blade of aviation engine bird impact tests simulate fixture characterized by comprising
Lower bracket (1), is fixedly connected with testing stand, with bottom plate (11) and two sides upwardly extended perpendicular to the testing stand
Plate (12) has first annular hole on the bottom plate (11)；
Upper bracket (2) is slidably arranged on the side plate (12) of the lower bracket (1), and upper bracket (2) includes and the bottom plate (11)
Parallel upper plate (21) has the second looping pit on the upper plate (21)；
Mounting base (3) is rotatably arranged on the bottom plate (11) of the lower bracket (1), and mounting base (3) is by passing through first ring
The bolt in shape hole is fixed on the lower bracket (1), and installation leaf assay part (5) tenon portion is provided on the mounting base (3)
The tongue-and-groove (31) divided；
Convex shoulder bracket (4) is rotatably arranged on the upper plate (21) of the upper bracket (2), and convex shoulder bracket (4) is by passing through described the
The bolt in second ring hole is fixed on the upper bracket (2), and convex shoulder bracket (4) is convex with leaf assay part (5) two sides are extended to
Two L-type supporting plates (41) at shoulder, when the convex shoulder bracket (4) rotates relative to the upper bracket (2), the L-type supporting plate
(41) end can be acted on to the convex shoulder of leaf assay part (5), and reverse the leaf assay part (5).
2. blade of aviation engine bird impact tests as described in claim 1 simulate fixture, which is characterized in that the lower bracket
(1) there is strip-shaped hole along the vertical direction, the upper bracket, which has, to be prolonged the upper plate (21) end is vertical on side plate (12)
The slide plate (22) stretched, slide plate (22) fitting are arranged on two side plates (12), by the spiral shell for passing through the strip-shaped hole on side plate (12)
Upper bracket and lower bracket are fixed bolt.
3. blade of aviation engine bird impact tests as described in claim 1 simulate fixture, which is characterized in that the mounting base
(3) it is provided with fin (32) with bottom plate (11) junction of the lower bracket (1), there is bolt hole, spiral shell on the fin (32)
After bolt passes through the bolt hole and the first annular hole, the mounting base (3) is fixed on the bottom plate (11).
4. blade of aviation engine bird impact tests as described in claim 1 simulate fixture, which is characterized in that lower bracket (1) is also
With the lower plate (13) for being parallel to the bottom plate (11), it is fixedly connected by lower plate (13) with the testing stand.
5. blade of aviation engine bird impact tests as described in claim 1 simulate fixture, which is characterized in that convex shoulder bracket (4)
Including upper ring plate (42), two L-type supporting plates (41) include respectively the vertical plate extended downwardly from upper ring plate anchor ring, and from vertically
The level board that plate end cross extends, the end abutment of the level board is on the convex shoulder of the leaf assay part (5).
6. blade of aviation engine bird impact tests as claimed in claim 5 simulate fixture, which is characterized in that the level board
End is fixedly connected with the convex shoulder of the leaf assay part (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910736330.XA CN110435924A (en) | 2019-08-09 | 2019-08-09 | Blade of aviation engine bird impact tests simulate fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910736330.XA CN110435924A (en) | 2019-08-09 | 2019-08-09 | Blade of aviation engine bird impact tests simulate fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110435924A true CN110435924A (en) | 2019-11-12 |
Family
ID=68434506
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910736330.XA Pending CN110435924A (en) | 2019-08-09 | 2019-08-09 | Blade of aviation engine bird impact tests simulate fixture |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111579190A (en) * | 2020-04-27 | 2020-08-25 | 南京航空航天大学 | Horizontal ejection-impact type blade bird-cutting test device and test method |
| CN112881203A (en) * | 2021-01-15 | 2021-06-01 | 北京航空航天大学 | Preparation device and method for foreign object damage notch of blade leading edge simulation piece |
| CN113495002A (en) * | 2020-04-03 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Rotary impact test device for non-full-ring fan blade of aero-engine |
| CN115114735A (en) * | 2022-07-26 | 2022-09-27 | 中国航发沈阳发动机研究所 | Bird-strike-resistant design method for aeroengine fan rotor blade shoulder |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113495002A (en) * | 2020-04-03 | 2021-10-12 | 中国航发商用航空发动机有限责任公司 | Rotary impact test device for non-full-ring fan blade of aero-engine |
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| CN112881203A (en) * | 2021-01-15 | 2021-06-01 | 北京航空航天大学 | Preparation device and method for foreign object damage notch of blade leading edge simulation piece |
| CN115114735A (en) * | 2022-07-26 | 2022-09-27 | 中国航发沈阳发动机研究所 | Bird-strike-resistant design method for aeroengine fan rotor blade shoulder |
| CN115114735B (en) * | 2022-07-26 | 2024-03-19 | 中国航发沈阳发动机研究所 | Bird strike resistant design method for aeroengine fan rotor blade shoulder |
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Application publication date: 20191112 |
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