NUMERICAL EXAMINATION OF A TUBE-TYPE AND DISK-TYPE COMBUSTOR CONFIGURATION

被引：0
|
作者：
PROCTOR, CL [1 ]
MELLOR, AM [1 ]
机构：
[1] DREXEL UNIV,COMBUST,PHILADELPHIA,PA 19104
来源：
AIAA JOURNAL | 1987年 / 25卷 / 05期
关键词：
AIRCRAFT ENGINES; JET AND TURBINE - MATHEMATICAL TECHNIQUES - Numerical Methods;
D O I：
10.2514/3.9696
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
An experimental tube and disk combustor configuration was examined numerically. This configuration is a compromise between the disk-in-duct configuration, the dump ramjet burner and the prevaporizing/premixing fuel feedtube-type turbojet. The tube and disk configuration models prevaporized/premixed-type gas turbine combustors. Nonreacting flowfield calculations were made using the computer code 'CORA2'. This code embodies a numerical procedure for the computation of elliptic, two-dimensional, axisymmetrical flows. Contour plots were developed to interpret the gaseous flowfield.
引用
收藏
页码：762 / 765
页数：4
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