CN108106829A - A kind of high-cycle fatigue test method and apparatus of gas turbine large size blade - Google Patents

A kind of high-cycle fatigue test method and apparatus of gas turbine large size blade Download PDF

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Publication number
CN108106829A
CN108106829A CN201711342810.5A CN201711342810A CN108106829A CN 108106829 A CN108106829 A CN 108106829A CN 201711342810 A CN201711342810 A CN 201711342810A CN 108106829 A CN108106829 A CN 108106829A
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China
Prior art keywords
fatigue
support frame
type support
gas turbine
blade
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Pending
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CN201711342810.5A
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Chinese (zh)
Inventor
何卫锋
聂祥樊
李应红
臧顺来
田乐
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Air Force Engineering University of PLA
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Air Force Engineering University of PLA
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Priority to CN201711342810.5A priority Critical patent/CN108106829A/en
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Pending legal-status Critical Current

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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00Testing of machine parts

Abstract

The invention discloses a kind of high-cycle fatigue test method and apparatus of gas turbine large size blade, the experimental rig includes fatigue experimental machine, pressure head and leaf assay part fixture, and wherein fixture is made of L-type support frame, left and right side pressing block, connection and fixing bolt and positioning pin:Leaf assay part is fixed, then is fixed and positions by fixing bolt, positioning pin and L-type support frame side plate by left and right side pressing block, connection bolt;L-type support frame is then fixed by bottom plate kidney slot and bolt with collet under fatigue experimental machine, and upper grip is then by pressure head to carrying out load application at the top of leaf assay part.On the basis of experimental rig, processing, Special Clamps Design, the spectrum design of fatigue experimental machine loaded load are designed by gas turbine blades load spectrum analysis, leaf assay part, the high-cycle fatigue test of gas turbine large size blade fatigue weak part can be carried out using general fatigue experimental machine, more realizes high cycle fatigue Performance Assessment closing to reality working condition.

Description

A kind of high-cycle fatigue test method and apparatus of gas turbine large size blade
Technical field
The invention belongs to high-cycle fatigue test method and technology field, the high cycle fatigue of large-scale blade on gas turbine is referred in particular to Performance test is examined, and is related to a kind of high-cycle fatigue test method and apparatus of gas turbine large size blade.
Background technology
Gas turbine has rapidly developed since the thirties in last century is born, and is not only widely used in power field, and The major impetus device of the world today is become, has had that efficient, power is big, it is fast to start, the low series of advantages of pollution.With The continuous extension in gas turbine application field is proposed its efficiency, power, structural strength and cleanliness etc. higher want It asks.Blade is the very important component of gas turbine, under Airflow Exciting-Vibration Force and the collective effect of vibration, root of blade region work Make stress maximum, fatigue crack can germinate and inwardly extended in root of blade region surface, and it is tired to ultimately result in entire blade high week Labor is broken or even jeopardizes complete machine safety, initiation accident.According to statistics, blade high cycle fatigue failure accounts for gas turbine total failare 42%.Therefore, how Validity Test obtains blade high cycle fatigue performance, and data are provided for blade construction intensity and reliability design It supports, to ensureing that gas turbine security reliability has important value.
Gas turbine is a kind of high-speed rotating machine, and internal gas flow is complicated, and blade working state is changeable.Due to gas turbine Blade dimensions are big, and type face is complicated, and general fatigue testing equipment is difficult the fatigue test for carrying out blade, and it is even more impossible to simulate real load Spectrum carries out tired examination, so main at present carry out fatigue test examination using the material test specimen or simulation blade of blade, but tries It is often larger with the fatigue behaviour gap under gas turbine blades actual condition to test result.In addition, when long using gas turbine Between test run experiment Assessment, not only testing expenses height, system complex, security risk is big, uncertain factor is more, but also be difficult Obtain the specific fatigue test results of gas turbine blades.Therefore, it is necessary to a kind of simple and effective, reasonable gas turbine is big Type blade high-cycle fatigue test method and device.
The content of the invention
It is an object of the invention to provide a kind of high-cycle fatigue test method and apparatus of gas turbine large size blade, with solution Certainly the problems mentioned above in the background art.
To achieve the above object, the present invention provides following technical solution:A kind of high cycle fatigue of gas turbine large size blade Test method and device, including experimental rig and test method, the experimental rig includes high frequency fatigue test system upper grip With collet under high frequency fatigue test system, the lower end of the high frequency fatigue test system upper grip is equipped with pressure head, and the high frequency is tired The upper end of collet is equipped with L-type support frame under labor pilot system, and the level board of the L-type support frame is equipped with waist-shaped hole, the waist Through there is L-type support frame fixing bolt in type hole, the L-type support frame fixing bolt under the high frequency fatigue test system with pressing from both sides Head thread connects, and the side plate of the L-type support frame is equipped with left and right side pressing block bolt hole group and side plate location hole, the L-type branch Left side briquetting and right side briquetting, the left side briquetting and right side are fixedly connected with by side pressing block fixing bolt on the side plate of support It is fixed between briquetting by connecting bolt, leaf assay part tongue-and-groove, the right side is equipped between the left side briquetting and right side briquetting The rear wall of side pressing block is equipped with the positioning pin being used cooperatively with side plate location hole, and leaf is connected on the leaf assay part tongue-and-groove Piece testpieces;
The experimental method includes step in detail below:
1) service load according to gas turbine blades is composed, and root of blade fatigue weak location is determined by finite element analysis And its high cycle fatigue load spectrum, and root front edge area is cut as leaf assay part.
2) by the tenon position of leaf assay part loaded in the tenon slot among two side pressing blocks, by 4 bolts by both sides Briquetting is fastened, and realizes the fixation of leaf assay part.
3) 4 connecting holes and location hole are opened on the side plate of L-type support frame according to leaf assay part torsion angle, and passes through spiral shell It tethers to connect and is fixed on two side pressing blocks on L-type support frame side plate according to certain deflection angle, realize the space orientation of leaf assay part, Ensure that leaf assay part leading edge is horizontal, belong to cantilever beam structure.
4) kidney slot is provided in L-type support frame bottom plate, L-type support frame is fixed on fatigue experimental machine using being bolted Lower collet, while the pressure head on fatigue experimental machine upper grip is made to be contacted with leaf assay part top area, realize load loading.
5) according to the clamping form of leaf assay part and load loading position, fatigue experimental machine is determined by finite element analysis The correspondence of axial load and leaf assay part fatigue examination position working stress, the high cycle fatigue according to root of blade in 1) Loading spectrum reversely determines fatigue tester loaded load spectrum, is examined so as to fulfill the high-cycle fatigue test to gas turbine blades root Core.
Preferably, according to gas turbine blades service load, the weak position of root of blade fatigue is determined by finite element analysis It puts and its high cycle fatigue load is composed, and root front edge area is cut as blade high-cycle fatigue test part.
Preferably, leaf assay part is fastened using two pieces of side pressing blocks and 4 bolts, passes through L-type support frame side plate 4 A connecting hole and location hole carry out space orientation to leaf assay part, ensure that blade inlet edge is horizontal positioned;And pass through L-type support frame Entire fixture is fixed under experimental machine on collet by bottom plate kidney slot and bolt, and the briquetting on experimental machine upper grip then tries blade It tests part top area and carries out fatigue and cyclic load application.
Preferably, determine that fatigue experimental machine loaded load examines position working stress with blade fatigue by finite element analysis Correspondence, according to actual blade fatigue weak location high cycle fatigue load spectrum reversely determine experimental machine loaded load Spectrum realizes the high-cycle fatigue test examination to gas turbine blades root.
Compared with prior art, the beneficial effects of the invention are as follows:This method passes through blade loading spectrum analysis, leaf assay part Design, Special Clamps Design, the spectrum design of fatigue experimental machine loaded load, can carry out gas turbine using general fatigue experimental machine The high-cycle fatigue test of large-scale blade fatigue weak part more realizes that high cycle fatigue performance is examined closing to reality working condition Core.The present invention has the following advantages:1st, by gas turbine large size blade weariness working stress finite element analysis, blade is determined Tired weak part and its loading spectrum cut blade weak part as blade fatigue test part, solve gas turbine leaf Piece because it is oversized can not on fatigue tester carry out fatigue test examination the problem of;2nd, by design by L-type support frame and The special fixture of side pressing block composition, determines L-type support frame side plate upper Positioning holes position according to blade twist angle, realizes blade The clamping and space orientation of testpieces, and pass through pressure head and apply load in leaf assay part leading edge, effectively reproduce combustion gas wheel The high cycle fatigue process of machine blade;3rd, it is weak by leaf assay part fatigue during analysis of finite element method high-cycle fatigue test The working stress state at position, the loaded load according to blade fatigue weak part loading spectrum conversion design fatigue experimental machine are composed, Solve the problems, such as that gas turbine large size blade fatigue load spectrum can not effectively apply;4th, high-cycle fatigue test method of the invention With good versatility, device design it is simple to operation, can be adapted for aeroengine fan blades, propeller blade and The large complicated type face blade such as ground gas turbine blade.
Description of the drawings
Fig. 1 is the high-cycle fatigue test schematic device of gas turbine large size blade;
Fig. 2 be gas turbine large size blade high-cycle fatigue test device in L-type support frame structure diagram;
Fig. 3 is left briquetting in the high-cycle fatigue test device of gas turbine large size blade and the structural representation of right pressure assembling Figure;
Fig. 4 be gas turbine large size blade high-cycle fatigue test device in left briquetting structure diagram;
Fig. 5 is the high-cycle fatigue test method flow diagram of gas turbine large size blade.
In figure:Collet, 3- pressure heads, 4- blades under 1- high frequency fatigue test systems upper grip, 2- high frequency fatigue test systems Briquetting, 6- right sides briquetting, 7- connections bolt, 8- side pressing blocks fixing bolt, 9-L types supporting rack, 10-L type branch on the left of testpieces, 5- Support fixing bolt, 11- side plates location hole, 12- or so side pressing block bolt hole group, 13- kidney slots, 14- positioning pins, 15- blades Testpieces tongue-and-groove.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.It is based on Embodiment in the present invention, those of ordinary skill in the art are obtained every other without making creative work Embodiment belongs to the scope of protection of the invention.
- 5 are please referred to Fig.1, the present invention provides a kind of technical solution:A kind of high-cycle fatigue test of gas turbine large size blade Method and apparatus, including experimental rig and test method, the experimental rig includes high frequency fatigue test system upper grip 1 and height Collet 2 under frequency fatigue test system, the lower end of the high frequency fatigue test system upper grip are equipped with pressure head 3, the high-cycle fatigue The upper end of collet is equipped with L-type support frame 9 under pilot system, and the level board of the L-type support frame is equipped with waist-shaped hole 13, the waist Running through in type hole has L-type support frame fixing bolt 10, under the L-type support frame fixing bolt and the high frequency fatigue test system Collet is threadedly coupled, and the side plate of the L-type support frame is equipped with left and right side pressing block bolt hole group 12 and side plate location hole 11, described Left side briquetting 5 and right side briquetting 6, the left side pressure are fixedly connected with by side pressing block fixing bolt 8 on the side plate of L-type support frame It is fixed between block and right side briquetting by connecting bolt 7, leaf assay part tenon is equipped between the left side briquetting and right side briquetting Slot 15, the rear wall of the right side briquetting are equipped with the positioning pin 14 being used cooperatively with side plate location hole, the leaf assay part Leaf assay part 4 is connected on tongue-and-groove;
The experimental method includes step in detail below:
1) the real work loading spectrum according to gas turbine large size blade determines root of blade fatigue by finite element analysis Weak location and its high cycle fatigue load spectrum, and root front edge area is cut as leaf assay part.
2) by the tenon position of leaf assay part loaded in the tenon slot among two side pressures, by 4 bolts by two side pressures Block is fastened, and realizes the fixation of leaf assay part.
3) 4 connecting holes and location hole are opened on the side plate of L-type support frame according to leaf assay part torsion angle, and passes through spiral shell It tethers to connect and is fixed on two side pressing blocks on L-type support frame side plate according to certain deflection angle, realize the space orientation of leaf assay part, Ensure that leaf assay part leading edge is horizontal.
4) kidney slot is provided in L-type support frame bottom plate, L-type support frame is fixed on fatigue experimental machine using being bolted On lower collet, while the pressure head of fatigue experimental machine upper grip is made to be contacted with leaf assay part top area, realize load loading.
5) according to the clamping form of leaf assay part and load loading position, fatigue experimental machine is determined by finite element analysis The correspondence of axial load and leaf assay part fatigue examination position working stress, it is reversed according to high cycle fatigue load spectrum in 1) Determine that fatigue experimental machine loaded load is composed, the efficiency test so as to fulfill the high cycle fatigue performance to gas turbine large size blade is examined Core.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with Understanding without departing from the principles and spirit of the present invention can carry out these embodiments a variety of variations, modification, replace And modification, the scope of the present invention is defined by the appended.

Claims (4)

1. a kind of high-cycle fatigue test method and apparatus of gas turbine large size blade, including experimental rig and test method, It is characterized in that:The experimental rig includes collet under high frequency fatigue test system upper grip (1) and high frequency fatigue test system (2), the lower end of the high frequency fatigue test system upper grip (1) is equipped with pressure head (3), collet under the high frequency fatigue test system (2) upper end is equipped with L-type support frame (9), and the level board of the L-type support frame (9) is equipped with waist-shaped hole (13), the waist-shaped hole (13) running through in has L-type support frame fixing bolt (10), the L-type support frame fixing bolt (10) and the high frequency fatigue test Collet (2) is threadedly coupled under system, and the side plate of the L-type support frame (9) is equipped with left and right side pressing block bolt hole group (12) and side Plate location hole (11) is fixedly connected with left side briquetting (5) and right on the side plate of the L-type support frame (9) by fixing bolt (8) Side pressing block (6) is fixed, the left side briquetting (5) between the left side briquetting (5) and right side briquetting (6) by connecting bolt (7) Leaf assay part tongue-and-groove (15) is equipped between right side briquetting (6), the rear wall of the right side briquetting (6) is equipped with to be determined with side plate Position hole (11) positioning pin (14) for being used cooperatively is connected with leaf assay part (4) on the leaf assay part tongue-and-groove (15);
The experimental method includes step in detail below:
1) according to gas turbine blades service load compose, by finite element analysis determine root of blade fatigue weak location and its High cycle fatigue load is composed, and root front edge area is cut as leaf assay part;
2) by the tenon position of leaf assay part loaded in the tenon slot among two side pressing blocks, by 4 bolts by two side pressing blocks It is fastened, realizes the fixation of leaf assay part;
3) 4 connecting holes and location hole are opened on the side plate of L-type support frame according to leaf assay part torsion angle, and is connected by bolt It connects and is fixed on two side pressing blocks on L-type support frame side plate according to certain deflection angle, realize the space orientation of leaf assay part, it is ensured that Leaf assay part leading edge is horizontal, and belongs to cantilever beam structure;
4) kidney slot is provided in L-type support frame bottom plate, is pressed from both sides using being bolted L-type support frame being fixed under fatigue experimental machine Head, while the pressure head on fatigue experimental machine upper grip is made to be contacted with leaf assay part top area, realize load loading;
5) according to the clamping form of leaf assay part and load loading position, fatigue experimental machine axial direction is determined by finite element analysis The correspondence of load and leaf assay part fatigue examination position working stress, the high cycle fatigue load according to root of blade in 1) Spectrum reversely compose by definite fatigue tester loaded load, is examined so as to fulfill to the high-cycle fatigue test of gas turbine blades root.
2. a kind of high-cycle fatigue test method and apparatus of gas turbine large size blade according to claim 1, feature It is:According to gas turbine blades service load, root of blade fatigue weak location and its high week are determined by finite element analysis Fatigue load spectrum, and root front edge area is cut as blade high-cycle fatigue test part.
3. a kind of high-cycle fatigue test method and apparatus of gas turbine large size blade according to claim 1, feature It is:Leaf assay part is fastened using two pieces of side pressing blocks and 4 bolts, by L-type support frame side plate location hole to leaf Piece testpieces carries out space orientation, ensures that blade inlet edge is horizontal positioned;And pass through L-type support frame bottom plate kidney slot and bolt will be whole A fixture is fixed under experimental machine on collet, and the briquetting on experimental machine upper grip then carries out fatigue to leaf assay part top area Cyclic loading applies.
4. a kind of high-cycle fatigue test method and apparatus of gas turbine large size blade according to claim 1, feature It is:Pair of fatigue experimental machine loaded load and leaf assay part fatigue examination position working stress is determined by finite element analysis It should be related to, the high cycle fatigue load spectrum according to actual blade fatigue weak location reversely determines the loaded load spectrum of experimental machine, real Now the high-cycle fatigue test of gas turbine blades root is examined.
CN201711342810.5A 2017-12-14 2017-12-14 A kind of high-cycle fatigue test method and apparatus of gas turbine large size blade Pending CN108106829A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110044585A (en) * 2019-03-05 2019-07-23 中国航发北京航空材料研究院 A kind of spherical shape partition fatigue experimental device and test method
CN110514035A (en) * 2019-08-19 2019-11-29 安徽弘谷激光有限公司 Heat exchanger on laser

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CN205157148U (en) * 2015-11-23 2016-04-13 沈阳黎明航空发动机(集团)有限责任公司 Test device can be assessd to super large fan blade fatigue performance
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CN105352586A (en) * 2015-11-20 2016-02-24 天津大学 Method used for realizing blade fatigue crack detection through resonance frequency detection
CN205157148U (en) * 2015-11-23 2016-04-13 沈阳黎明航空发动机(集团)有限责任公司 Test device can be assessd to super large fan blade fatigue performance
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110044585A (en) * 2019-03-05 2019-07-23 中国航发北京航空材料研究院 A kind of spherical shape partition fatigue experimental device and test method
CN110514035A (en) * 2019-08-19 2019-11-29 安徽弘谷激光有限公司 Heat exchanger on laser

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