Volume 35 Issue 10
Oct.  2020
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Article Navigation >  Journal of Aerospace Power  > 2020  >  35(10): 2195-2204
ZHONG BIN, MA Shaojun, ZHANG Shichao. Calculation of design allowable values for TC11 titanium bar and forging at room temperature[J]. Journal of Aerospace Power, 2020, 35(10): 2195-2204. doi: 10.13224/j.cnki.jasp.2020.10.020
Citation: ZHONG BIN, MA Shaojun, ZHANG Shichao. Calculation of design allowable values for TC11 titanium bar and forging at room temperature[J]. Journal of Aerospace Power, 2020, 35(10): 2195-2204. doi: 10.13224/j.cnki.jasp.2020.10.020
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Calculation of design allowable values for TC11 titanium bar and forging at room temperature

doi: 10.13224/j.cnki.jasp.2020.10.020
  • 1.

    Beijing Institute of Aeronautical Materials,Aero Engine Corporation of China,Beijing 100095,China

  • 2.

    Key Laboratory of Aeronautical Materials Testing and Evaluation,Beijing Institute of Aeronautical Materials,Aero Engine Corporation of China,Beijing 100095,China

  • 3.

    Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation,Beijing Institute of Aeronautical Materials,Aero Engine Corporation of China,Beijing 100095,China

  • Received Date: 2020-04-17
  • Publish Date: 2020-10-28
    Abstract
  • In view of the basic problems and principles of statistics, the elements of direct calculation for design allowable value of metallic material tensile strength at room temperature were briefly analyzed. The design allowable values for TC11 titanium bar and forging were calculated and analyzed. Result showed that the lower limit of series allowable values for TC11 bar with different sizes calculated by regression method was closer to the actual product strength compared with specified S-basis values. The calculated ultimate strengths were 31-85 MPa higher than specified lower limit. The allowable value calculated by non-regression method for TC11 forging ultimate strength was 11 MPa lower than specified S-basis value. Calculated values were higher than A-basis values of TC11 alloy in domestic material data handbooks, ie 15%-72% higher for bars, 39% and 52% higher for forging ultimate strength and yield strength.

     

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    • References(18)
  • [1]
    Federal Aviation Administration.Metallic materials properties development and standardization :Chapter 9 Guidelines for presentation of DATA:MMPDS-11［S］.Columbus:Battelle Memorial Institute,2016:11-144.
    [2]
    PETRAKIS J J.Certifying airworthiness［J］.Aerospace Engineering,2003,23(10):24-26.
    [3]
    NIEDZINSKI M,RUBADUE J,RICE R,et al.MMPDS Handbook:a key element in aircraft and aerospace design［J］.Light Metal Age,2013,71(1):46-49.
    [4]
    PAUL E R.An overview of the MIL-HDBK-5 program［R］.Columbus:Battell Columbus Laboratories,1984.
    [5]
    BRAY M H,ZOOK L M,RALEY R E,et al.Achieving innovation and affordability through standardization of materials development and testing［R］.Huntsville,US:Marshall Space Flight Center,2012.
    [6]
    BAKUCKAS J G Jr,THOMPSON S R,RICE R C.Metallic materials properties development and standardization (MMPDS):continuation and replacement for MIL-HDBK-5［R］.Columbus:Battelle Memorial Institute,2002.
    [7]
    RICE R C,JACKSON J L,BAKUCKAS J,et al,Metallic materials properties development and standardization (MMPDS)［R］.DOT/FAA/AR-MMPDS-01,2003.
    [8]
    沈小明,陈挺,张迎春.民用航空材料适航审定［J］.材料工程,2017,45(11):139-142.SHEN Xiaoming,CHEN Ting,ZHANG Yingchun.Airworthiness certification of civil aviation materials［J］.Journal of Materials Engineering,2017,45(11):139-142.(in Chinese)
    [9]
    United States Department of Defense.Engine structural integrity program (ENSIP):MIL-HDBK-1783B［S］.Washington:United States Air Force,2002:64-65.
    [10]
    马国宇.材料力学设计许用值统计方法研究及软件开发［D］.沈阳:东北大学,2010.MA Guoyu.Statistical methods for allowable values of mechanical design and software development［D］.Shenyang:Northeastern University.(in Chinese)
    [11]
    陈颖.飞机材料设计许用值统计分析方法及实际应用［J］.工艺设计改造及检测检修,2015,223(19):58-59.CHEN Ying.Statistic methodology and application of design allowable for aircraft materials［J］.China Science and Technology Overview,2015,223(19):58-59.(in Chinese)
    [12]
    原鲲,赵熹,叶萍,等.确定GH3128高温拉伸性能设计许用值的方法［J］.清华大学学报(自然科学版),2014,54(9):1236-1239.YUAN Kun,ZHAO Xi,YE Ping,et al.Methodology for determining high temperature ttensile design allowable strengths of alloy GH3128［J］.Tsinghua University (Science and Technology),2014,54(9):1236-1239.(in Chinese)
    [13]
    北京航空材料研究所.航空发动机设计用材料数据手册:第2册［M］.北京:国防工业出版社,1993.
    [14]
    北京航空材料研究院.金属材料力学性能数据处理与表达:GJB18Z/A-2005［S］.北京:国防科学技术工业委员会，2005:9-21.
    [15]
    苑诗松,王静龙.数理统计［M］.上海:华东师范大学出版社,1990.
    [16]
    高镇同,熊峻江.疲劳可靠性［M］.北京:北京航空航天大学出版社,2000.
    [17]
    何晓群,刘文卿.应用回归分析［M］.3版.北京:中国人民大学出版社,2011.
    [18]
    杜宝江,季长芹,郭京敏,等.航空用某复合材料力学特性统计分布的研究［J］.兵器材料科学与工程,2012,35(3):30-33.DU Baojiang,JI Changqin,GUO Jingmin,et al.Statistical distribution of mechanical properties for one aeronautical composite material［J］.Ordnance Material Science and Engineering,2012,35(3):30-33.(in Chinese)
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