Accession Number:

ADA595796

Title:

Parametric Trends in the Combustion Stability Characteristics of a Single-Element Gas-Gas Rocket Engine

Descriptive Note:

Conference paper

Corporate Author:

AIR FORCE RESEARCH LAB EDWARDS AFB CA AEROSPACE SYSTEMS DIRECTORATE

Report Date:

2013-12-01

Pagination or Media Count:

23.0

Abstract:

Combustion instability continues to be a challenge in the design of rocket engines. The use of computational fluid dynamics CFD simulations screen potential designs offers the ability to reduce the number of costly tests and improve understanding of the underlying instability mechanism. In this study a series of axisymmetric CFD simulations are used to investigate the instability sensitivity to four design changes. The design changes are selected in an attempt to reduce the level of instability. The parameters considered are the combustor wall temperature, the effect of adding swirl to the fuel injector and two geometric changes, namely, fuel injector area reduction and the introduction of a chamfer in the injector face. The simulations show that both the wall temperature and swirl are able to significantly lower the amplitude by 70. The results of the geometric changes are mixed with both decreases and increases in the instability amplitude. The parametric study has enhanced the understanding of the instability mechanisms by demonstrating that the when a continuous fuel supply to the combustor is maintained the instability amplitude is decreased.

Subject Categories:

  • Combustion and Ignition
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE