Performance comparison between high temperature rise triple-swirler combustor and double-swirler combustor

LI Feng; GUO Rui-qing; SHANG Shou-tang; CHENG Ming; TANG Zheng-fu; SONG Bo; GAO Xian-zhi

doi:10.13224/j.cnki.jasp.2015.01.002

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Performance comparison between high temperature rise triple-swirler combustor and double-swirler combustor

更新时间：2026-07-07

- Performance comparison between high temperature rise triple-swirler combustor and double-swirler combustor
- Vol. 30, Issue 1, Pages: 10-15(2015)
- 作者机构：
  
  1. 北京航空航天大学能源与动力工程学院,北京,100191
  2. 中国航空工业集团公司沈阳发动机设计研究院燃烧设计室,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2015.01.002
  CLC：
- Published：2015
- 稿件说明：
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李锋, 郭瑞卿, 尚守堂, 程明, 唐正府, 宋博, 高贤智. 高温升三旋流燃烧室与双旋流燃烧室的性能对比[J]. 航空动力学报, 2015, 30(1): 10-15.

doi: 10.13224/j.cnki.jasp.2015.01.002
李锋, 郭瑞卿, 尚守堂, 程明, 唐正府, 宋博, 高贤智. 高温升三旋流燃烧室与双旋流燃烧室的性能对比[J]. 航空动力学报, 2015, 30(1): 10-15. DOI： 10.13224/j.cnki.jasp.2015.01.002.

doi: 10.13224/j.cnki.jasp.2015.01.002 DOI：

摘要

采用参数化建模的方法

保持扩压器尺寸、外机匣最大直径以及燃烧室出口尺寸与单环腔燃烧室(SAC)一致

将燃烧室头部旋流器从双旋流结构设计为三旋流结构

采用三维数值模拟的方法对双旋流燃烧室(DSC)和三旋流燃烧室(TSC)的流动和燃烧过程进行数值模拟.对比研究了两种燃烧室在高温升条件下的性能.结果表明:传统的DSC已不能满足油气比为0.037的高温升燃烧室的燃烧效率等性能需求

TSC可获得比DSC更高的总压恢复系数、燃烧效率以及温升

更低的出口温度分布系数(OTDF)和径向出口温度分布系数(RTDF);在油气比为0.037情况下

设计的高温升TSC总压降在5%以内;OTDF为0.162

RTDF为0.106;燃烧效率大于99%.

Abstract

With use of the parametric modeling method

when the size of diffuser

the maximum dimension of outer case and exit size of combustor were kept the same as single annular combustor (SAC)

the combustor head swirler was redesigned from the double-swirler structure into triple-swirler structure; the three-dimensional flow and combustion processes of double-swirler combustor (TSC) and triple-swirler combustor (TSC) were numerically simulated

and the performance of two high temperature rise combustors were compared. The results indicate that

the traditional DSC cannot meet performance requirement such as combustion efficiency of high temperature rise combustion with fuel air ratio of 0.037; by using the TSC

the total pressure recovery coefficient

combustion efficiency and temperature rise can be improved compared with the DSC; the outlet temperature distribution factor (OTDF) and radial outlet temperature distribution factor (RTDF) of TSC is lower than that of DSC. With fuel air ratio of 0.037

the total pressure drop of designed high temperature rise TSC is less than 5%

OTDF reaching 0.162

RTDF reaching 0.106

and combustion efficiency is more than 99%.

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Combustion Design Office, Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China

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