CN110006636A - A kind of FOD repeated bend test part and its design method - Google Patents
A kind of FOD repeated bend test part and its design method Download PDFInfo
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- CN110006636A CN110006636A CN201910197262.4A CN201910197262A CN110006636A CN 110006636 A CN110006636 A CN 110006636A CN 201910197262 A CN201910197262 A CN 201910197262A CN 110006636 A CN110006636 A CN 110006636A
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- blade
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- leading edge
- fod
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a kind of FOD repeated bend test part and its design method, which includes clamping end and simulation blade.Wherein, clamping end is able to satisfy effectively clamps in FOD simulation test and repeated bend test, and testpieces is avoided to influence test result because loosening；Simulation blade can simulate the up-front shape of real blade feature locations, and blade inlet edge is appropriately curved, bending stress minor issue caused by effectively avoiding because of bending neutral layer.
Description
Technical field
The present invention relates to the vane simulated experimental technique fields of aircraft engine.
Background technique
For aircraft during runway or type aircraft carrier deck landing, the aero-engine of high revolving speed operation can often suck stone, sand
When the hard object such as gravel, bolt, metal fragment, these foreign matters enter engine and the relative velocity of compressor blade is up to 100m/s-
350m/s can cause serious impact injury to damage to the leading edge of preceding what compressor blade especially blade.In the prior art,
The hard objects such as metal, sandstone are hit into the damage of engine bring and are referred to as " foreign object damage " (abbreviation FOD, Foreign
Object Damage)。
In the prior art, almost exist such as FOD test and the plate simulation leaf assay part of high-cycle fatigue test
Lower problem: testpieces generally slab design is divided into without leading edge with two class of leading edge, the former tries the fatigue behaviour for material
It tests, the latter can express influence of the leading edge feature to testpieces fatigue behaviour, but due to the shape of its plate, be tried using stretching
It tests machine and carries out tension and compression high-cycle fatigue test.High-cycle fatigue test is the important research content for disclosing FOD blade fatigue performance.Tension and compression
High-cycle fatigue test can only study influence of the centrifugal load to engine vane fatigue intensity, can not show the shadow of oscillating load
It rings.The engine blade compound action by centrifugal load and oscillating load in actual operation, it is therefore desirable to carry out to starting
The research of machine blade fatigue property, this, which just has to invention, can satisfy the testpieces of repeated bend test requirement, that is, want
Modulus, which intends blade, can show the up-front shape of real blade feature locations, and modulus is intended answering when blade is avoided that bending vibration again
Hypodynamic problem.
Using actual engine blade carry out FOD test and high all repeated bend test be for the model blade most subject to
True research method, but foreign object damage test is destructive testing, will be unable to be restored to the preceding state of test after testpieces is impaired, because
This, which often carries out a test, just needs to scrap a real blade testpieces, and experimentation cost is extremely high.This not carrying out
Large-scale F OD test and high all repeated bend tests, the test data amount of acquisition is limited, is unable to satisfy fatigue behaviour research institute
It needs.
Summary of the invention
Goal of the invention: the present invention provides a kind of FOD repeated bend test parts, can simulate real blade leading edge feature
And effectively avoid the low problem of bending vibration stress.
Invention also provides the above-mentioned FOD design methods of repeated bend test part.
Technical solution: for achieving the above object, the present invention adopts the following technical scheme that.
A kind of FOD repeated bend test part, including clamping end and simulation blade, the rear end and clamping end for simulating blade connect
It connects；The simulation blade has upper surface, lower surface and two sides；And upper surface, lower surface and two sides and clamping end
Junction has arc transition；The front end of the simulation blade is leading edge of a wing structure, and the leading edge of a wing structure includes plate
Section and two leading edges that warpage is bent from flat plate section both ends, and the junction of leading edge and flat plate section is arc transition；Two leading edges
It is symmetrical set in flat plate section two sides.
Further, the clamping end is only arranged one.
Further, the thickness of clamping end is greater than six times of flat plate section thickness.
Further, simulation length of blade is set to 1.5 times of simulation width of blade.
Further, simulation leaf disks section width is three times of leading edge width.
The utility model has the advantages that FOD repeated bend test part provided by the invention can simulate real blade leading edge feature and effective
Avoid the low problem of bending vibration stress.Wherein, clamping end is able to satisfy effectively presss from both sides in FOD simulation test and repeated bend test
It holds, testpieces is avoided to influence test result because loosening；Simulation blade can simulate the up-front shape of real blade feature locations, and handle
Blade inlet edge is appropriately curved, bending stress minor issue caused by effectively avoiding because of bending neutral layer.
The above-mentioned FOD design method of repeated bend test part provided by the invention, can be used following technical scheme:
Finite element simulation is carried out according to the threedimensional model of real blade, up-front danger position is obtained, is obtained from model
The sectional dimension of danger position therefrom extracts leading-edge radius and leading edge angle, and size when blade thickness is stablized is as simulation leaf
Piece flat plate section thickness, and from leading edge to the length of blade thickness settling position, it is wide as leading edge back side width and leading edge front
Degree；
Simulate three times that leaf disks section width is leading edge width；
Simulation blade inlet edge bending angle is set as 20 °；
It is equal with leading edge width numerical value to simulate the excessive radius of leaf disks section, rounded corner when processing；
Simulation length of blade is set as 1.5 times of simulation width of blade；
Changeover portion draft angle is set as 5 °, and transition section length is set as the one third of simulation length of blade；
Clamping end size is determined that clamping end thickness is greater than six times of flat plate section thickness by simulation blade profile size.
Detailed description of the invention
Fig. 1 is testpieces main view.
Fig. 2 is testpieces left view.
Fig. 3 is A-A sectional view in Fig. 1.
Wherein label is described as follows:
1-clamping end width；2-clamping end length；3-clamping end thickness；4-transition section lengths；5-changeover portion drafts
Angle；6-excessive fillets；7-simulation width of blade；8-simulation length of blade；9-simulation blade inlet edge radiuses；10-simulation leaves
Piece leading edge angle；11-simulation blade inlet edge bending angles；12-simulation excessive the radiuses of leaf disks section；13-simulation leaf disks
Duan Houdu；14-simulation leaf disks section back side width；15-simulation leaf disks section frontal widths；16-simulation blade inlet edges
Back side width；17-simulation blade inlet edge frontal widths；100-simulation blades；200-clamping ends；101-flat plate sections；102—
Leading edge.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
Shown in please referring to Fig.1 to Fig.3, the invention discloses a kind of FOD repeated bend test parts, including clamping end 200
And simulation blade 100, the rear end of simulation blade 100 are connect with clamping end 200；The simulation blade has upper surface, lower surface
And two sides；And upper surface, lower surface and two sides and clamping end junction have arc transition；The simulation blade
Front end is leading edge of a wing structure, and the leading edge of a wing structure includes flat plate section 101 and bends the two of warpage from 101 both ends of flat plate section
A leading edge 102, and the junction of leading edge 102 and flat plate section 101 is arc transition；Two leading edges 102 are in pair in flat plate section two sides
Claim setting.
In present embodiment, clamping end 200 is only arranged one, and is rectangular parallelepiped structure, folder identical as simulation blade material
It holds and is seamlessly transitted between end 200 and simulation blade 100 with arc structure, stress is avoided to concentrate.It simulates blade-section and uses wing
Leading edge design, leading edge dimensional parameters are identical as at real blade feature locations.Bending process is integrally made to leading edge portion, so that mould
Not simple plate, the planform of both sides warpage central flat of quasi- blade, can effectively avoid due in bending
Property layer principle and the problem for causing bending vibration stress small.Testpieces is using whole machining mode, after processing is completed to table
Face is processed by shot blasting, eliminates micro-crack and burr
And present invention simultaneously provides the above-mentioned FOD design methods of repeated bend test part:
Finite element simulation is carried out according to the threedimensional model of real blade, up-front danger position is obtained, is obtained from model
The sectional dimension of danger position therefrom extracts leading-edge radius 9 and leading edge angle 10, and size when blade thickness is stablized is as simulation
Leaf disks section thickness 13, and from leading edge to the length of blade thickness settling position, as leading edge back side width 16 and leading edge
Frontal width 17；
Simulate three times that leaf disks section width is leading edge width；
Simulation blade inlet edge bending angle 11 is set as 20 °, can effectively improve leading edge bending vibration stress；
It is equal with leading edge width numerical value to simulate the excessive radius 12 of leaf disks section, rounded corner when processing；
Simulation length of blade 8 is set as 1.5 times of simulation width of blade；
Changeover portion draft angle 5 is set as 5 °, and transition section length 4 is set as the one third of simulation length of blade 8, excessively circle
Angle 6, which is served, eliminates stress concentration, is arranged on demand；
Clamping end size is determined that clamping end thickness 3 is greater than six times of flat plate section thickness 13, to mention by simulation blade profile size
For the space of fixture positioning.
The advantages of FOD of the invention repeated bend test part design method and good effect are mainly reflected in:
1, FOD can satisfy the demand of FOD test and repeated bend test with repeated bend test part, widen FOD leaf
The research field of piece fatigue behaviour was of great significance for the application in engineering, for tired longevity of the real blade after by FOD
The research of life prediction, which has, pushes value.
2, FOD is determined with repeated bend test part size by the size of real blade dangerouse cross-section, generally will not be very big, is added
Work is convenient, and testpieces is with short production cycle, producing cost is low, materials are few；
3, FOD repeated bend test part test needs place small, and testing expenses are low, and the test period is short.
The above is only a preferred embodiment of the present invention, it should be pointed out that in the case where not departing from concept thereof of the invention,
Several deductions or substitution can also be made, these are deduced or substitution is regarded as protection scope of the present invention.
Claims (6)
1. a kind of FOD repeated bend test part, it is characterised in that: including clamping end and simulation blade, simulate the rear end of blade
It is connect with clamping end；The simulation blade has upper surface, lower surface and two sides；And upper surface, lower surface and two sides
Face and clamping end junction have arc transition；The front end of the simulation blade is leading edge of a wing structure, and the leading edge of a wing knot
Structure includes flat plate section and two leading edges from flat plate section both ends bending warpage, and the junction of leading edge and flat plate section is circular arc mistake
It crosses；Two leading edges are symmetrical set in flat plate section two sides.
2. FOD according to claim 1 repeated bend test part, it is characterised in that: the clamping end is only arranged one.
3. FOD according to claim 2 repeated bend test part, it is characterised in that: the thickness of clamping end is greater than six times
Flat plate section thickness.
4. FOD according to claim 1 repeated bend test part, it is characterised in that: simulation length of blade is set to simulation
1.5 times of width of blade.
5. FOD according to claim 1 repeated bend test part, it is characterised in that: simulating leaf disks section width is
Three times of leading edge width.
6. a kind of to the FOD described in claim 1 design method of repeated bend test part, it is characterised in that:
Finite element simulation is carried out according to the threedimensional model of real blade, up-front danger position is obtained, danger is obtained from model
The sectional dimension of position therefrom extracts leading-edge radius (9) and leading edge angle (10), and size when blade thickness is stablized is as simulation
Leaf disks section thickness (13), and from leading edge to the length of blade thickness settling position, as leading edge back side width (16) and
Leading edge frontal width (17)；
Simulate three times that leaf disks section width is leading edge width；
Simulation blade inlet edge bending angle (11) is set as 20 °；
Simulate the excessive radius of leaf disks section (12) it is equal with leading edge width numerical value, rounded corner when processing；
Simulation length of blade (8) is set as 1.5 times of simulation width of blade；
Changeover portion draft angle (5) is set as 5 °, and transition section length (4) is set as the one third of simulation length of blade (8)；
Clamping end size is determined that clamping end thickness (3) is greater than six times of flat plate section thickness (13) by simulation blade profile size.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910197262.4A CN110006636A (en) | 2019-03-15 | 2019-03-15 | A kind of FOD repeated bend test part and its design method |
| PCT/CN2020/077925 WO2020187038A1 (en) | 2019-03-15 | 2020-03-05 | Bending fatigue test piece for fod and design method therefor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910197262.4A CN110006636A (en) | 2019-03-15 | 2019-03-15 | A kind of FOD repeated bend test part and its design method |
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| Publication Number | Publication Date |
|---|---|
| CN110006636A true CN110006636A (en) | 2019-07-12 |
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|---|---|---|---|
| CN201910197262.4A Pending CN110006636A (en) | 2019-03-15 | 2019-03-15 | A kind of FOD repeated bend test part and its design method |
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| WO (1) | WO2020187038A1 (en) |
Cited By (6)
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| CN111695286A (en) * | 2020-06-22 | 2020-09-22 | 中国航发沈阳发动机研究所 | Design method of aero-engine turbine blade sampling clamp |
| WO2020187038A1 (en) * | 2019-03-15 | 2020-09-24 | 南京航空航天大学 | Bending fatigue test piece for fod and design method therefor |
| CN112197922A (en) * | 2020-08-25 | 2021-01-08 | 中国航发湖南动力机械研究所 | Turbine blade vibration fatigue simulation piece and design method thereof |
| CN112748008A (en) * | 2020-12-29 | 2021-05-04 | 中国航空工业集团公司西安飞机设计研究所 | I-beam tensile fatigue test piece and tensile fatigue test method |
| CN112881197A (en) * | 2021-01-15 | 2021-06-01 | 北京航空航天大学 | Blade leading edge high cycle fatigue simulation piece and design method |
| 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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| WO2020187038A1 (en) * | 2019-03-15 | 2020-09-24 | 南京航空航天大学 | Bending fatigue test piece for fod and design method therefor |
| 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 |
| CN113495002B (en) * | 2020-04-03 | 2023-01-06 | 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 |
| CN111695286A (en) * | 2020-06-22 | 2020-09-22 | 中国航发沈阳发动机研究所 | Design method of aero-engine turbine blade sampling clamp |
| CN112197922A (en) * | 2020-08-25 | 2021-01-08 | 中国航发湖南动力机械研究所 | Turbine blade vibration fatigue simulation piece and design method thereof |
| CN112748008A (en) * | 2020-12-29 | 2021-05-04 | 中国航空工业集团公司西安飞机设计研究所 | I-beam tensile fatigue test piece and tensile fatigue test method |
| CN112881197A (en) * | 2021-01-15 | 2021-06-01 | 北京航空航天大学 | Blade leading edge high cycle fatigue simulation piece and design method |
| CN112881197B (en) * | 2021-01-15 | 2022-05-03 | 北京航空航天大学 | Blade leading edge high cycle fatigue simulation piece and design method |
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|---|---|
| WO2020187038A1 (en) | 2020-09-24 |
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Application publication date: 20190712 |