Turboshaft engine overall design method based onbalance of componentsdifficulty coefficients

张少锋; 陈玉春; 甘晓华

doi:10.13224/j.cnki.jasp.2018.10.019

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Turboshaft engine overall design method based onbalance of componentsdifficulty coefficients

更新时间：2026-07-07

- Turboshaft engine overall design method based onbalance of componentsdifficulty coefficients
- Vol. 33, Issue 10, Pages: 2465-2475(2018)
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2018.10.019
  CLC：
- Published：2018
- 稿件说明：
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张少锋, 陈玉春, 甘晓华. 基于难度系数平衡的涡轴发动机总体设计方法[J]. 航空动力学报, 2018, 33(10): 2465-2475.

doi: 10.13224/j.cnki.jasp.2018.10.019
张少锋, 陈玉春, 甘晓华. 基于难度系数平衡的涡轴发动机总体设计方法[J]. 航空动力学报, 2018, 33(10): 2465-2475. DOI： 10.13224/j.cnki.jasp.2018.10.019.

doi: 10.13224/j.cnki.jasp.2018.10.019 DOI：

摘要

为了实现第5代涡轴发动机从概念至初步设计阶段的总体方案设计，发展一种兼顾涡轴发动机总体性能与尺寸质量的总体设计方法。统计并评估国内外典型型号涡轴发动机的技术参数，建立涉及总体性能、总体结构、部件的气动/结构/强度/材料等数据库；在概念设计阶段，应用难度系数选取涡轴发动机的技术参数，开发涡轴发动机总体性能和尺寸质量设计的计算模型及程序。基于设计准则完成涡轴发动机总体性能以及各转子部件气动、结构、强度、尺寸及质量等总体方案设计。结果表明：所提出的总体设计方法能够快速有效的实现涡轴发动机的总体方案设计，并以此方法设计完成轴动功率为1500kW的第5代涡轮发动机，耗油率为0.248kg/(kW·h)

功质比为10.26kW/kg。

Abstract

In order to complete the design of the fifth-generation turboshaft engine from the conceptual design stage to the preliminary design stage

the integrated design method based on the overall performance and size and mass of the turboshaft engine was studied. Through statistical evaluation of typical models of turboshaft engines at home and abroad

a database of technical parameters such as overall performance

overall structure

and the components aerodynamic/structure/strength/material properties of turboshaft engines was established; the concept of difficulty coefficient was proposed

and the technical parameters of the turboshaft engine were selected in the conceptual design stage using difficulty coefficient. An integrated design calculation model and program for the overall performance and size and mass of the turboshaft engine were developed

the overall performance of the tuboshaft engine was achieved under the constraints of the design criteria. Design of overall performance and other components performance

such as the aerodynamic/structural/strength/size/mass of the rotor components

was completed under the constraints of the design criteria. Results show that this design method can complete the overall design scheme of the turboshaft engine

and in this way

the fifth-generation turboshaft engine with 1500 kW shaft power was designed with specific fuel consumption (SFC) of 0.248kg/(kW·h) and P/W of 10.26kW/kg.

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