郑华雷,蔡建兵,黄 兴.基于多设计点方法的涡轴发动机热力循环分析[J].航空发动机,2023,49(1):41-46
基于多设计点方法的涡轴发动机热力循环分析
Turboshaft Thermodynamic Cycle Analysis Based on Multi-Design Point Method
  
DOI:
中文关键词:  热力循环分析  单设计点方法  多设计点方法  性能需求  多约束条件  涡轴发动机
英文关键词:thermodynamic cycle analysis  single design point method  multi-design point method  performance requirements  technology limits  turboshaft
基金项目:航空动力基础研究项目资助
作者单位E-mail
郑华雷,蔡建兵,黄 兴 中国航发湖南动力机械研究所湖南株洲 412002 008zheng@163.com 
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中文摘要:
      针对航空发动机设计中涉及多性能需求和多约束条件的热力循环分析问题,提出了多设计点热力循环分析方法。详细 介绍了多设计点热力循环分析方法的构建以及求解过程,用单设计点方法和多设计点方法对单转子燃气发生器带自由式动力涡 轮的涡轴发动机进行热力循环分析,并分析了2种方法得到的设计域。结果表明:在由传统单设计点方法所获得的设计域内的某 些区域,由于性能需求和使用限制的矛盾而不可行,而在这部分不可行区域内,有可能包含性能最优的设计点,从而使最优设计点 不可行;在多设计点方法分析中,采用了多个(或所有)有性能需求和使用限制的工作状态作为其设计点,可以在合适的工作状态 选取正确的设计变量,从而使设计域内的每一设计点都满足所有工作状态的要求。
英文摘要:
      A multi-design point method was developed to investigate the thermodynamic cycle analysis utilizing multiple performance requirements and multiple constraints in the aircraft engine design process. This paper illustrates the construction and solution process to perform on-design cycle analysis at more than one operating conditions. Cycle design spaces of a single rotor gas generator turbshaft engine with a free power turbine created by the two different design methods were examined. Analysis of the design space demonstrates that the conflict between technology limits and performance requirements at off design operating conditions makes some region of design space, maybe contains the optimum candidate engine,created by single design method infeasible,in the meanwhile,multi-design point method, which incorporates multiple(all)operating conditions where performance requirements and constrains are specified,can set the design variables at the appropriate operating conditions while meeting the specified performance requirements and constraints for all operating con? ditions .
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