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改进型一体化加力燃烧室方案的数值模拟
引用本文:王伟龙,金捷,井文明,刘邓欢,季鹤鸣,游庆江,李江宁.改进型一体化加力燃烧室方案的数值模拟[J].航空动力学报,2015,30(5):1119-1124.
作者姓名:王伟龙  金捷  井文明  刘邓欢  季鹤鸣  游庆江  李江宁
作者单位:1. 北京航空航天大学 能源与动力工程学院, 北京 100191;
摘    要:针对传统加力燃烧室质量过大与非加力状态下流动损失巨大的问题展开了设计研究,提出了一种改进型一体化加力燃烧室方案,取消了常规的钝体稳定器,采用了内突扩中心锥的火焰稳定结构.采用了数值模拟的方法研究方案的性能.结果表明:该方案对入口参数不敏感;在所有研究的工况条件下,3种方案总压恢复系数均高于0.96,加力燃烧室的效率接近0.90;采用波瓣混合器的方案具有最佳的总体性能. 

关 键 词:一体化    加力燃烧室    波瓣混合器    燃烧效率    总体性能
收稿时间:2013/12/10 0:00:00

Numerical simulation on improved integrated afterburner scheme
WANG Wei-long,JIN Jie,JING Wen-ming,LIU Deng-huan,JI He-ming,YOU Qing-jiang and LI Jiang-ning.Numerical simulation on improved integrated afterburner scheme[J].Journal of Aerospace Power,2015,30(5):1119-1124.
Authors:WANG Wei-long  JIN Jie  JING Wen-ming  LIU Deng-huan  JI He-ming  YOU Qing-jiang and LI Jiang-ning
Institution:1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;2. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China
Abstract:An improved integrated afterburner scheme was proposed to solve the problem of too large mass of traditional afterburner and too significant flow loss in non-augmentation condition. This scheme canceled the conventional stabilizer of blunt body, and a sudden expanding structure of central cone for stabilizing the flame was adopted. Numerical simulation was conducted to research its performance. The result indicates that the scheme is not sensitive to inlet parameters; total pressure recovery coefficients of three schemes on all cases are greater than 0.96; afterburner efficiency is close to 0.90; the scheme with lobed mixer has the best overall performance.
Keywords:integrated  afterburner  lobed mixer  combustion efficiency  overall performance
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