Project Title:

Rapid-Mix Concepts for Low-Emission Combustors in Gas Turbine Engines

01.02-6576
NAS3-25834
Rapid-Mix Concepts for Low-Emission
	Combustors in Gas Turbine Engines
CFD Research Corporation
	3325-D Triana Boulevard
	Huntsville, AL 35805
		Clifford E. Smith
(205-536-6576)

Abstract:

	Innovative rapid-mix concepts will be studied for rich-burn, quick-quench, and lean-burn
(RQL) gas turbine combustors applicable to future high-speed aircraft. Conventional
quick quench sections for circular flame tube configurations have employed radial
in-flow holes or slots, and little mixing optimization has been performed. Two concepts
are proposed for improved mixing: asymmetric jet penetration (AJP) and a lobe mixer
(LM). In Phase I, the AJP concept will be studied. Two schemes of the AJP concept
will be analyzed: a counter-vortex scheme and a co-vortex scheme. These schemes produce
multiple vortex patterns which are substantially different from the conventional
concepts and have the potential of enhancing overall mixing. Three-dimensional computational
fluid dynamics (CFD) techniques will be employed to analyze and compare the proposed
AJP schemes with a conventional rapid-mix concept. In Phase II, the same CFD methods
would be employed to screen the LM concept. The most promising AJP or LM concept
would be selected, optimized, and experimentally tested to show its potential of
minimizing NOx formation.

Potential Commercial Application:

Potential Commercial Applications: The final optimized and tested RQL combustor design
can be patented and commercialized to gas turbine engine manufacturers.