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A Low NO(x) Lean-Direct Injection, Multipoint Integrated Module Combuster Concept for Advanced Aircraft Gas TurbinesA low NO(x) emissions combustor has been demonstrated in flame-tube tests. A multipoint, lean-direct injection concept was used. Configurations were tested that had 25- and 36- fuel injectors in the size of a conventional single fuel injector. An integrated-module approach was used for the construction where chemically etched laminates, diffusion bonded together, combine the fuel injectors, air swirlers and fuel manifold into a single element. Test conditions were inlet temperatures up to 810 K, inlet pressures up to 2760 kPa, and flame temperatures up to 2100 K. A correlation was developed relating the NO(x) emissions with the inlet temperature, inlet pressure, fuel-air ratio and pressure drop. Assuming that 10 percent of the combustion air would be used for liner cooling and using a hypothetical engine cycle, the NO(x) emissions using the correlation from flame-tube tests were estimated to be less than 20 percent of the 1996 ICAO standard.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Tacina, Robert
(NASA Glenn Research Center Cleveland, OH United States)
Wey, Changlie
(QSS Group, Inc. Cleveland, OH United States)
Laing, Peter
(Parker-Hannifin Corp. Andover, OH United States)
Mansour, Adel
(Parker-Hannifin Corp. Andover, OH United States)
Date Acquired
September 7, 2013
Publication Date
April 1, 2002
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:211347
Meeting Information
Meeting: Conference on Technologies and Combustion for a Clean Environment
Location: Oporto
Country: Portugal
Start Date: July 9, 2001
End Date: July 12, 2001
Sponsors: Instituto Superior Tecnico
Funding Number(s)
PROJECT: RTOP 714-02-20
Distribution Limits
Public Use Permitted.
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