RAPID MIX CONCEPTS FOR LOW EMISSION COMBUSTORS IN GAS TURBINE ENGINES

Award Information
Agency:
National Aeronautics and Space Administration
Amount:
$50,000.00
Program:
SBIR
Contract:
N/A
Solitcitation Year:
N/A
Solicitation Number:
N/A
Branch:
N/A
Award Year:
1990
Phase:
Phase I
Agency Tracking Number:
11932
Solicitation Topic Code:
N/A
Small Business Information
Cfd Research Corpon
3325-d Triana Boulevard, Huntsville, AL, 35805
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
N/A
Principal Investigator
 H. Q. Yang
 Project Engineer
 (205) 536-6576
Business Contact
 ASHOK K. SINGHAL
Title: PRESIDENT & TECHNICAL DIRECTOR
Phone: (205) 536-6576
Research Institution
N/A
Abstract
INNOVATIVE RAPID MIX CONCEPTS ARE PROPOSED FOR RICK BURN/QUICK QUENCH/LEAN BURN (RQL) GAS TURBINE COMBUSTORS APPLICABLE TO FUTURE HIGH-SPEED AIRCRAFT. CONVENTIONAL QUICK QUENCH SECTIONS FOR CIRCULAR FLAMETUBE CONFIGURATIONS HAVE EMPLOYED RADIAL INFLOW HOLES OR SLOTS, AND LITTLE MIXING OPTIMIZATION HAS BEEN PERFORMED. TWO CONCEPTS ARE PROPOSED FOR IMPROVED MIXING: 1) ASYMMETRIC JET PENETRATION (AJP); AND 2) LOBE MIXER (LM). IN PHASE I, THE AJP CONCEPT WILL BE STUDIED. TWO SCHEMES OF THE AJP CONCEPT WILL BE ANALYZED: 1) COUNTER-VORTEX SCHEME; AND 2) CO-VORTEX SCHEME. THESE SCHEMES PRODUCE MULTIPLE VORTEX PATTERNS WHICH ARE SUBSTANTIALLY DIFFERENT FROM THE CONVENTIONAL CONCEPT 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 WILL BE EMPLOYED TO SCREENTHE LM CONCEPT. THE MOST PROMISING AJP OR LM CONCEPT WILL BE SELECTED, OPTIMIZED, AND EXPERIMENTALLY TESTED TO SHOW ITS POTENTIAL OF MINIMIZING NOX FORMATION.

* information listed above is at the time of submission.

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