Research on Reverse Design of Turboshaft Engine Based on the Balance of Difficulty Factor

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI:10.1109/ICMAE.2018.8467673

Zhang Shao-feng, Cheng Yu-chun

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Abstract

In order to study the overall scheme of turboshaft engine in conceptual phase and preliminary design phase, this paper presents an inverse design method. Firstly, technical parameters of typical models of turboshaft engine are counted and evaluated, the database of technical parameters of turboshaft engine is established. Then the concepts of difficulty factor and generation of the turboshaft engine are proposed, and the technical parameters of the turboshaft engine are chosen in turn. At last, based on the overall performance and size & weight calculation model of the turboshaft engine, the aerodynamic/ structure /strength/ size/ weight design of the components is first completed, then the reverse design of the turboshaft engine’s overall performance calculation is performed. This design method is used for the overall design of the advanced fifth generation turboshaft engine. The overall scheme of the fifth-generation turboshaft engine indicates the turbine entry temperature T4 is 1663K and P/W is 13.75 hp/kg (reaching 12-15 level).

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基于难度系数平衡的涡轮轴发动机反设计研究

为了研究涡轮轴发动机在概念阶段和初步设计阶段的总体方案，本文提出了一种逆设计方法。首先对典型型号涡轮轴发动机的技术参数进行了统计和评价，建立了涡轮轴发动机技术参数数据库。然后提出了涡轴发动机难度系数和生成的概念，并依次选择了涡轴发动机的技术参数。最后，基于涡轮轴发动机的总体性能和尺寸重量计算模型，首先完成各部件的气动/结构/强度/尺寸/重量设计，然后进行涡轮轴发动机总体性能计算的反设计。该设计方法用于先进的第五代涡轮轴发动机的总体设计。第五代涡轴发动机的总体方案表明涡轮入口温度T4为1663K, P/W为13.75 hp/kg(达到12-15级)。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE)

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