典型文献
Design and optimization of supersonic turbines for detonation combustors
文献摘要：
Detonation-based engines offer a potential surge in efficiency for compact thermal power systems.However,these cycles require ad-hoc components adapted to the high outlet velocity from the detonation combustors.This paper presents the design methodology of turbine stages suitable for supersonic inlet conditions and provides a detailed analysis of optimized turbine geometries.A reduced-order solver examines the supersonic blade rows'functional design space,quantifies the turbine's non-isentropic performance,and budgets the turbine loss for different optimized leading-edge designs and chord to pitch ratios.The shock-wave interactions were identified as the predominant contributor to turbine losses,and optimal pitch-chord ratios were determined for various inlet Mach numbers.Finally,with this tool,the specific-power output for a wide range of design configurations was computed;and the metal angle that ensures flow starting and maxi-mizes power extraction was calculated.The detailed numerical study describes the flow interactions in a supersonic turbine and offers new correlations to guide the design of future supersonic turbines.
文献关键词：
中图分类号：
作者姓名：
Jorge SOUSA;Elena COLLADO-MORATA;Guillermo PANIAGUA
作者机构：
Flemish Institute for Technological Research,Mol 2400,Belgium;Commissariat à l'énergie atomique et aux énergies alternatives,Le Barp 33114,France;Mechanical Engineering,Purdue University,West-Lafayette IN 47906,USA
文献出处：
引用格式：
[1]Jorge SOUSA;Elena COLLADO-MORATA;Guillermo PANIAGUA-.Design and optimization of supersonic turbines for detonation combustors)[J].中国航空学报（英文版）,2022(11):33-44
A类：
Detonation,mizes
B类：
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AB值：
0.612978
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