CN109145335A - A method of wheel disc low cycle fatigue life is improved by pre-rotation - Google Patents

A method of wheel disc low cycle fatigue life is improved by pre-rotation Download PDF

Info

Publication number
CN109145335A
CN109145335A CN201710504610.9A CN201710504610A CN109145335A CN 109145335 A CN109145335 A CN 109145335A CN 201710504610 A CN201710504610 A CN 201710504610A CN 109145335 A CN109145335 A CN 109145335A
Authority
CN
China
Prior art keywords
wheel disc
stress
rotation
service life
fatigue
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201710504610.9A
Other languages
Chinese (zh)
Other versions
CN109145335B (en
Inventor
高阳
赵迎春
罗文飞
李亚非
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Study On Guiyang Engine Design China Hangfa
Original Assignee
Study On Guiyang Engine Design China Hangfa
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Study On Guiyang Engine Design China Hangfa filed Critical Study On Guiyang Engine Design China Hangfa
Priority to CN201710504610.9A priority Critical patent/CN109145335B/en
Publication of CN109145335A publication Critical patent/CN109145335A/en
Application granted granted Critical
Publication of CN109145335B publication Critical patent/CN109145335B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Landscapes

  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Engineering & Computer Science (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Computational Mathematics (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The invention belongs to aero-engine structure fatigue life designing techniques, are related to a kind of method for improving wheel disc low cycle fatigue life by pre-rotation.It is characterized in that, the fatigue test under the conditions of different pre-tensile stress is carried out to material standard coupon first, so that it is determined that the optimum prestress of MaLS can be obtained；Then stress-strain analysis is carried out to wheeling disk structure, determines the corresponding pre-rotation revolving speed when its service life examination position generates optimum prestress；On wheel disc rotation test device, pre-rotation is carried out to wheel disc with the pre-rotation revolving speed, so that its service life examination position is entered stretching plastic, due to the effect by surrounding elastomeric region after unloading, service life examination position can bear residual compressive stress, to improve its low cycle fatigue life.Low cycle fatigue life can obtain double raising after S-N curve estimates wheel disc pre-rotation after being pre-stretched according to material.

Description

A method of wheel disc low cycle fatigue life is improved by pre-rotation
Technical field
The invention belongs to aero-engine structure fatigue life designing techniques, are related to a kind of low by pre-rotation raising wheel disc The method of cycle fatigue life.
Background technique
In the 21st century, is in order to pursue higher thrust ratio, and aero-engine wheeling disk structure is intended to lightweight, and wheel disc is answered Power level is also gradually increased, and wheel disc stress concentration portion position even works in plastic region, this makes wheel disc low-cycle fatigue problem It is very prominent.As aero-engine service life key component, low cycle fatigue life is the key that restrict engine machine life. Modern advanced aero engine not only performance indicators such as demanding thrust ratio, more require high reliability and long-life.It is external first It is alreadyd exceed 3000 hours into aero-engine machine life, and domestic air mail engine life generally rests on 1000 hours left sides The right side, how to improve aero-engine service life becomes the problem of puzzlement aircraft engineer, and improves aero-engine wheel disc class knot The structure service life is then the important prerequisite for improving engine life.
Powder metallurgy high-temperature alloy material because its excellent performance is widely applied in modern aeroengine, FGH4097 is the new levigation powder metallurgy material in China, which has even tissue, crystal grain tiny, good stretching and persistently strong Degree and antifatigue and croop property, mainly for the manufacture of the advanced aero engine turbine disk, high-pressure compressor disk, drum barrel axis With the rotary parts such as force bearing ring.Pre-rotation technical research is carried out for FGH4097 wheel disc, military service shape can be improved by the technology The stress distribution of wheel disc under state, to obtain the longer wheel disc service life, which has extraordinary application prospect, can bring Huge economic benefit.
Summary of the invention
The purpose of the present invention is: a kind of method that wheel disc low cycle fatigue life is improved by pre-rotation is proposed, to obtain Take higher wheel disc low cycle fatigue life.
Technical solution
A method of wheel disc low cycle fatigue life being improved by pre-rotation, its step are as follows:
1, wheel disc service life examination position is determined by calculation, and determines the position fatigue load, temperature；
2, several stress levels are chosen near the wheel disc service life examination position range of stress and carries out the pre- of material standard coupon Stretch processing；
3, be pre-stretched influences to study on fatigue life, determines best pre-tensile stress；
4, material is pre-stretched with best pre-tensile stress, the S-N curve of measurement material pre-stretching front and back；
5, wheel disc pre-rotation revolving speed is determined by calculation；
6, fatigue stress of the wheel disc service life examination position after pre-rotation is calculated；
7, the pre-rotation front and back wheel disc service life is calculated separately according to pre-stretching front and back S-N curve, determines and passes through pre-rotation wheel disc The level that service life examines position low-cycle fatigue projected life to improve.
The invention has the advantages that can be improved to greatest extent in the case where wheeling disk structure, service load condition are constant Wheel disc low cycle fatigue life meets advanced aero engine to the long life requirement of wheel disc.
Detailed description of the invention
Fig. 1 is flow chart of the present invention；
Fig. 2 is that pre-stretching influences FGH4097 fatigue life；
The S-N curve of pre-stretching front and back FGH4097 material when Fig. 3 is R=0 at 400 DEG C.
Specific embodiment
The present invention is described in further details below.A kind of side for improving wheel disc low cycle fatigue life by pre-rotation Method, steps are as follows:
1, according to wheel disk rotating speed, material circulation stress-strain data, material physical and mechanical properties at different temperatures, The parameters such as wheel disc mating blades density of material, be determined by calculation the wheel disc service life examination position, and determine the position fatigue stress, Temperature；
2, three or more stress levels are chosen near the wheel disc service life examination position range of stress and carries out the examination of FGH4097 standard The pre-stretching of stick records tensile stress-strain data；
3, be pre-stretched influences to study on fatigue life, is mainly pre-stretched by testing through different pre-tensile stress Afterwards, the fatigue life of FGH4097 standard coupon, and with without being pre-stretched coupon life span comparison, determine best pre-tensile stress；
4, material is pre-stretched with best pre-tensile stress, the S-N curve of measurement material pre-stretching front and back；
5, by the way that different wheel disk rotating speeds are arranged, the fatigue stress at wheel disc service life examination position under different rotating speeds is calculated.Most preferably After pre-tensile stress is by true stress conversion, calculates and determine that wheel disc pre-selection turns rotational speed omegapre；
6, fatigue stress of the wheel disc service life examination position after pre-rotation is calculated；
7, the pre-rotation front and back wheel disc service life is calculated separately according to pre-stretching front and back S-N curve, pre-rotation wheel disc is passed through in assessment The level that service life examines position low-cycle fatigue projected life to improve.
Embodiment
1, certain aero-engine high-pressure turbine disk service life examination position bolt hole adds and unloads since the position has entered plasticity After load the position fatigue stress be -170MPa -1122MPa, about 400 DEG C of temperature.According to Goodman equation, stress ratio is arrived in conversion The fatigue stress of R=0 is 1151MPa；
2, using 1000MPa, 1100MPa, 1150MPa, 1200MPa, 1250MPa as pre-tensile stress σmax, respectively to 4 FGH4097 standard coupon is pre-stretched；
3, the coupons to 20 of step 2 by pre-stretching and 4 without the coupons by pre-stretching totally 24 coupons into Row fatigue maximum stress is 1150MPa, and the fatigue test of R=0, carrying out prestressing force influences experimental study to fatigue life, is determined The best pre-tensile stress of longest-lived.As shown in Fig. 2, best pre-tensile stress is 1150MPa.
4, by be not pre-stretched and after 1150MPa autofrettage standard coupon stress fatigue test, The FGH4097 S-N Curve of pre-stretching front and back when obtaining R=0 at 400 DEG C, as shown in Figure 3；
5, because prestressing force 1150MPa is engineering stress, it can be determined by coupon strain measurement or FEM calculation True pre-tensile stress should be σpre=1240MPa or so；Stress-strain analysis is carried out to FGH4097 wheel disc, can determine correspondence When bolt position service life examination point stress 1240MPa, pre-rotation rotational speed omegapreAbout 120% working speed.
6, wheel disc is determined by calculation by ωpreIt after pre-rotation, is become apparent partially into plasticity, the service life examines position Fatigue stress is -300MPa -970MPa, and by Goodman equation, the fatigue stress converted as stress ratio R=0 is 1050MPa；
7, fatigue stress before and after wheel disc pre-rotation is substituted into pre-stretching front and back S-N curve respectively, obtains mean value before pre-rotation Service life is 17553 circulations, and the service life of reliability 0.9987 is 9776 circulations；And the mean value service life is followed after pre-rotation for 38121 Ring, the service life 21320 of reliability 0.9987.It calculates assessment and shows that the pre-rotation FGH4097 wheel disc service life examines the position low circulation longevity It orders mean value and increases by 117%, 0.9987 life 118% of reliability.

Claims (1)

1. a kind of method for improving wheel disc low cycle fatigue life by pre-rotation, which is characterized in that realized by following steps；
Step 1: wheel disc service life examination position is determined by calculation, and determine the position fatigue stress, temperature；
Step 2: choosing several stress levels near the wheel disc service life examination position range of stress carries out the pre- of material standard coupon Stretch processing, the stress level should be more than the yield strength of material；
Step 3: be pre-stretched influences to study on fatigue life, best pre-tensile stress, the best pre-tensile stress are determined For the most apparent stress value of service life reinforcing effect；
Step 4: being pre-stretched with best pre-tensile stress to material, the S-N curve of measurement material pre-stretching front and back；
Step 5: calculating the fatigue stress at wheel disc service life examination position under different rotating speeds, best pre-tensile stress presses true stress It after conversion, is compared with the fatigue stress being calculated under different rotating speeds, determines that wheel disc pre-selection turns rotational speed omegapre；
Step 6: calculating fatigue stress of the wheel disc service life examination position after pre-rotation；
Step 7: calculating separately the pre-rotation front and back wheel disc service life according to pre-stretching front and back S-N curve, determines and pass through pre-rotation wheel disc The level that service life examines position low-cycle fatigue projected life to improve.
CN201710504610.9A 2017-06-28 2017-06-28 Method for improving low cycle fatigue life of wheel disc through pre-rotation Active CN109145335B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710504610.9A CN109145335B (en) 2017-06-28 2017-06-28 Method for improving low cycle fatigue life of wheel disc through pre-rotation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710504610.9A CN109145335B (en) 2017-06-28 2017-06-28 Method for improving low cycle fatigue life of wheel disc through pre-rotation

Publications (2)

Publication Number Publication Date
CN109145335A true CN109145335A (en) 2019-01-04
CN109145335B CN109145335B (en) 2023-05-30

Family

ID=64805548

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710504610.9A Active CN109145335B (en) 2017-06-28 2017-06-28 Method for improving low cycle fatigue life of wheel disc through pre-rotation

Country Status (1)

Country Link
CN (1) CN109145335B (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111471944A (en) * 2020-05-19 2020-07-31 北京钢研高纳科技股份有限公司 Method for regulating and controlling residual stress of high-temperature alloy blank disc forging through prerotation
CN114323622A (en) * 2022-01-05 2022-04-12 中国航发贵阳发动机设计研究所 Method for verifying service life of powder metallurgy turbine disc through simulation part comparison test
AU2021206812B1 (en) * 2021-07-20 2022-11-03 Aecc Commercial Aircraft Engine Co., Ltd. Method for Internal Stress Regulation in Superalloy Disk forgings by Pre-spinning
CN115356119A (en) * 2022-07-29 2022-11-18 中国航发沈阳发动机研究所 Design method of low-cycle fatigue life test scheme of multistage low-pressure turbine rotor
CN116818555A (en) * 2023-07-25 2023-09-29 中国航发北京航空材料研究院 Method for determining pre-rotation speed of nickel-based superalloy wheel disc blank

Citations (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3339237A (en) * 1963-07-31 1967-09-05 Rhodiaceta Apparatus for converting tow into sliver
GB2011552A (en) * 1977-12-27 1979-07-11 United Technologies Corp Rotor blade attachment
GB1593361A (en) * 1977-05-09 1981-07-15 Borg Warner Control system for regulating large capacity rotating machinery
US4325756A (en) * 1978-12-18 1982-04-20 United Technologies Corporation Fatigue resistant nickel superalloy
US4411715A (en) * 1981-06-03 1983-10-25 The United States Of America As Represented By The Secretary Of The Air Force Method of enhancing rotor bore cyclic life
EP0421229A1 (en) * 1989-10-04 1991-04-10 General Electric Company Creep, stress rupture and hold-time fatigue crack resistant alloys
CN101311550A (en) * 2007-05-24 2008-11-26 株式会社泰拉尔极东 Centrifugal blower with backward inclined blade wheel
WO2009155591A1 (en) * 2008-06-20 2009-12-23 Test Devices Inc. Systems and methods for producing thermal mechanical fatigue on gas turbine rotors in a spin test environment
US20100212422A1 (en) * 2009-02-25 2010-08-26 Jeffrey Scott Allen Method and apparatus for pre-spinning rotor forgings
CN202157973U (en) * 2011-08-10 2012-03-07 山东省临风鼓风机有限公司 Large-size double suction centrifugal blower
CN102682208A (en) * 2012-05-04 2012-09-19 电子科技大学 Turbine disk probability failure physical life predicting method based on Bayes information update
CN104034719A (en) * 2014-04-03 2014-09-10 贵州黎阳航空动力有限公司 ICP-AES measuring method for content of elemental hafnium in nickel-based high-temperature alloy
CN104316388A (en) * 2014-07-25 2015-01-28 中国航空工业集团公司北京航空材料研究院 A fatigue lifetime measuring method for anisotropic material structural parts
CN104498804A (en) * 2014-12-04 2015-04-08 北京钢研高纳科技股份有限公司 Preparation method of high-temperature alloy and high-temperature alloy thereof
CN204359514U (en) * 2014-11-20 2015-05-27 中国燃气涡轮研究院 A kind of rotor disk drum syndeton
CN104881543A (en) * 2015-05-28 2015-09-02 重庆大学 Direct-partitioning fuel gas main flow and disk cavity secondary flow coupling calculation method
CN105488252A (en) * 2015-11-22 2016-04-13 沈阳黎明航空发动机(集团)有限责任公司 Burst speed simulative analysis method for bolt-free structure turbine disk baffle
CN105899814A (en) * 2014-02-05 2016-08-24 三菱重工业株式会社 Diaphragm and centrifugal rotating machine
CN106446367A (en) * 2016-09-09 2017-02-22 南京航空航天大学 Arc length method nonlinear finite element analysis-based disc burst speed prediction method
CN106457340A (en) * 2014-04-15 2017-02-22 马克西昂轮毂德国控股公司 Method for producing wheel disc forms on flow-forming machines, vehicle wheel having wheel disc form of said type, and spinning mandrel for flow-forming machines for producing corresponding wheel disc forms
CN106545520A (en) * 2016-10-31 2017-03-29 沈阳鼓风机集团股份有限公司 Compressor impeller and pinion shaft attachment structure and its processing method
CN106644784A (en) * 2016-12-31 2017-05-10 北京航空航天大学 Turbine disc damage tolerance assessment method considering multiple parts and multiple failure modes

Patent Citations (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3339237A (en) * 1963-07-31 1967-09-05 Rhodiaceta Apparatus for converting tow into sliver
GB1593361A (en) * 1977-05-09 1981-07-15 Borg Warner Control system for regulating large capacity rotating machinery
GB2011552A (en) * 1977-12-27 1979-07-11 United Technologies Corp Rotor blade attachment
US4191509A (en) * 1977-12-27 1980-03-04 United Technologies Corporation Rotor blade attachment
US4325756A (en) * 1978-12-18 1982-04-20 United Technologies Corporation Fatigue resistant nickel superalloy
US4411715A (en) * 1981-06-03 1983-10-25 The United States Of America As Represented By The Secretary Of The Air Force Method of enhancing rotor bore cyclic life
EP0421229A1 (en) * 1989-10-04 1991-04-10 General Electric Company Creep, stress rupture and hold-time fatigue crack resistant alloys
CN1050743A (en) * 1989-10-04 1991-04-17 通用电气公司 The alloy and the method for making thereof of creep resistance, stress rupture resistant and the repeated stress failure of anti-band hold-time
CN101311550A (en) * 2007-05-24 2008-11-26 株式会社泰拉尔极东 Centrifugal blower with backward inclined blade wheel
WO2009155591A1 (en) * 2008-06-20 2009-12-23 Test Devices Inc. Systems and methods for producing thermal mechanical fatigue on gas turbine rotors in a spin test environment
US20100212422A1 (en) * 2009-02-25 2010-08-26 Jeffrey Scott Allen Method and apparatus for pre-spinning rotor forgings
CN202157973U (en) * 2011-08-10 2012-03-07 山东省临风鼓风机有限公司 Large-size double suction centrifugal blower
CN102682208A (en) * 2012-05-04 2012-09-19 电子科技大学 Turbine disk probability failure physical life predicting method based on Bayes information update
CN105899814A (en) * 2014-02-05 2016-08-24 三菱重工业株式会社 Diaphragm and centrifugal rotating machine
CN104034719A (en) * 2014-04-03 2014-09-10 贵州黎阳航空动力有限公司 ICP-AES measuring method for content of elemental hafnium in nickel-based high-temperature alloy
CN106457340A (en) * 2014-04-15 2017-02-22 马克西昂轮毂德国控股公司 Method for producing wheel disc forms on flow-forming machines, vehicle wheel having wheel disc form of said type, and spinning mandrel for flow-forming machines for producing corresponding wheel disc forms
CN104316388A (en) * 2014-07-25 2015-01-28 中国航空工业集团公司北京航空材料研究院 A fatigue lifetime measuring method for anisotropic material structural parts
CN204359514U (en) * 2014-11-20 2015-05-27 中国燃气涡轮研究院 A kind of rotor disk drum syndeton
CN104498804A (en) * 2014-12-04 2015-04-08 北京钢研高纳科技股份有限公司 Preparation method of high-temperature alloy and high-temperature alloy thereof
CN104881543A (en) * 2015-05-28 2015-09-02 重庆大学 Direct-partitioning fuel gas main flow and disk cavity secondary flow coupling calculation method
CN105488252A (en) * 2015-11-22 2016-04-13 沈阳黎明航空发动机(集团)有限责任公司 Burst speed simulative analysis method for bolt-free structure turbine disk baffle
CN106446367A (en) * 2016-09-09 2017-02-22 南京航空航天大学 Arc length method nonlinear finite element analysis-based disc burst speed prediction method
CN106545520A (en) * 2016-10-31 2017-03-29 沈阳鼓风机集团股份有限公司 Compressor impeller and pinion shaft attachment structure and its processing method
CN106644784A (en) * 2016-12-31 2017-05-10 北京航空航天大学 Turbine disc damage tolerance assessment method considering multiple parts and multiple failure modes

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
冯引利: "FGH96涡轮盘低循环疲劳寿命分析技术与试验", 《航空动力学报》 *
杜文军等: "某压气机轮盘低循环疲劳寿命研究", 《燃气涡轮试验与研究》 *
郭晓强: "模拟轴向载荷作用的轮盘低循环疲劳寿命试验研究", 《燃气涡轮试验与研究》 *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111471944A (en) * 2020-05-19 2020-07-31 北京钢研高纳科技股份有限公司 Method for regulating and controlling residual stress of high-temperature alloy blank disc forging through prerotation
CN111471944B (en) * 2020-05-19 2021-07-23 北京钢研高纳科技股份有限公司 Method for regulating and controlling residual stress of high-temperature alloy blank disc forging through prerotation
AU2021206812B1 (en) * 2021-07-20 2022-11-03 Aecc Commercial Aircraft Engine Co., Ltd. Method for Internal Stress Regulation in Superalloy Disk forgings by Pre-spinning
CN114323622A (en) * 2022-01-05 2022-04-12 中国航发贵阳发动机设计研究所 Method for verifying service life of powder metallurgy turbine disc through simulation part comparison test
CN114323622B (en) * 2022-01-05 2024-03-19 中国航发贵阳发动机设计研究所 Method for verifying service life of powder metallurgy turbine disk through simulation piece comparison test
CN115356119A (en) * 2022-07-29 2022-11-18 中国航发沈阳发动机研究所 Design method of low-cycle fatigue life test scheme of multistage low-pressure turbine rotor
CN116818555A (en) * 2023-07-25 2023-09-29 中国航发北京航空材料研究院 Method for determining pre-rotation speed of nickel-based superalloy wheel disc blank
CN116818555B (en) * 2023-07-25 2024-02-02 中国航发北京航空材料研究院 Method for determining pre-rotation speed of nickel-based superalloy wheel disc blank

Also Published As

Publication number Publication date
CN109145335B (en) 2023-05-30

Similar Documents

Publication Publication Date Title
CN109145335A (en) A method of wheel disc low cycle fatigue life is improved by pre-rotation
CN112100766A (en) Fatigue life prediction method for cold extrusion reinforced hole structure
CN109255202A (en) A kind of predictor method for mechanical component fatigue crack initiation life
CN107092728B (en) Fatigue test method for tensioning shaft of turbofan engine
CN108627406B (en) High-strength metal material amplitude variation ultrahigh cycle fatigue life prediction method
JP2008190039A (en) Method and article relating to high strength erosion resistant titanium alloy
CN107122531A (en) A kind of quick runner lifetime estimation method based on accelerated life test
WO2016173567A2 (en) Anti-fracture design method for nickel-based high temperature fasteners
CN110826267B (en) Engine cylinder cover creep fatigue analysis method
CN108254250B (en) Heat engine multi-axis stress-strain relation determination method considering dynamic strain aging
US20090308506A1 (en) Methods for heat treating and manufacturing a thermomechanical part made of a titanium alloy, and thermomechanical part resulting from these methods
Radchenko et al. Experimental and theoretical studies of the influence of a tensile load on the relaxation of residual stresses in a hardened cylindrical specimen under creep conditions
CN107991200B (en) Fatigue life prediction method for titanium alloy impeller
CN107748817B (en) High-temperature multi-axis constitutive relation determination method considering non-proportional additional reinforcement
CN112485118B (en) Method for estimating critical inclusion size of fatigue failure of high-strength steel
CN103797134B (en) For the manufacture of the method for compressor blade
RU2616691C2 (en) METHOD OF MAKING PART MADE OF TITANIUM ALLOY TA6Zr4DE
Nozhnitsky et al. Numerical simulation of spin testing for turbo machine disks using energy-based fracture criteria
Kashyzadeh et al. Fatigue life assessment of unidirectional fibrous composite centrifugal compressor impeller blades based on FEA
CN113011069A (en) Method and system for analyzing stress of main shaft of wind turbine generator
Zheng et al. Failure analysis of a MW-class wind turbine blade root bolt
CN108664716B (en) High-strength titanium alloy heat treatment process evaluation model based on ultrahigh cycle fatigue performance
Tarasenko et al. The analysis of the main structural and mechanical characteristics of EP800 and EI893 alloys to optimize production of the first stage of a GTE-45-3 gas-turbine power plant
Wang et al. Lifetime Prediction of Turbine Blade of Turbocharger for Diesel Engine Based on Fatigue and Creep Damage Model
US20170089816A1 (en) Rig

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant