The Design and Performance of a High Temperature Rise Combustor for Wind Tunnel

被引：4

作者：

Zhang Rongchun ^{[1
]}

Fan Weijun ^{[1
]}

机构：

[1] Beijing Univ Aeronaut & Astronaut, Sch Jet Prop, Natl Key Lab Aeroengines, Beijing 100191, Peoples R China

来源：

JOURNAL OF THERMAL SCIENCE | 2011年 / 20卷 / 06期

关键词：

high temperature rise; evaporator; wind tunnel; combustor; aviation kerosene;

D O I：

10.1007/s11630-011-0510-5

中图分类号：

O414.1 [热力学];

学科分类号：

摘要：

A high-temperature-rise combustor that can be used in high-temperature wind tunnel is introduced in this study. Aviation kerosene is used in this type of combustor, with division combustion scheme and evaporator fuel-supply device adopted. In the performance test under atmospheric pressure, when the inlet temperature is 500K and air flow is within the range of 1.5-3.0 kg/s, the outlet temperature can be precisely regulated within the range of 1050K-2100K. Moreover, higher uniformity of outlet temperature distribution and higher combustion efficiency can be achieved. After the long-time working in the wind tunnel, various components of the combustor, especially the combustor liners are checked without finding any anomaly such as thermal deformation.

引用

页码：556 / 562

页数：7

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