Application of Scaling in Afterburner Test and Development PUBLIC ACCESS

[+] Author Affiliations
Li Xiang-yi, Yang Mao-lin, Liu Gao-en, Gu Shan-jian

Beijing Institute of Aeronautics and Astronautics, Beijing, China

Paper No. 81-GT-194, pp. V001T01A009; 7 pages
  • ASME 1981 International Gas Turbine Conference and Products Show
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Houston, Texas, USA, March 9–12, 1981
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7961-0
  • Copyright © 1981 by ASME


Experiments on low pressure combustion performance have been made with three different afterburner models. Tests were carried out in a test rig of 400 mm with inlet temperatures ranging form 898 to 940 K, inlet pressure from 0.77 to 1.51 kg/cm2, and air flow rates from 4.06 to 8.26 kg/sec. The performance data (combustion efficiency and stability) obtained are similar to those obtained with the actual jet engine. Tests of a swirl atomizer and a plain orifice injector with the same fuel flow rates produced similar performance curves. In afterburner development work for a given type of engine, the effect on performance of changing from one type injector to another was less than that of changing stabilizers.

Copyright © 1981 by ASME
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