NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Emission characteristics of a premix combustor fueled with a simulated partial-oxidation product gasA two-stage gas turbine combustor concept employing a very fuel-rich partial oxidation stage is being explored for broadening the combustion margin between ultralow emissions and the lean stability limit. Combustion and emission results are presented for a series of experiments where a simulated partial oxidation product gas was used in a premix combustor operated with inlet air state conditions typical of cruise power for high-performance aviation engines (12 atm and 850 F). Ultralow NOx, CO, and HC emissions and an extended lean burning limit were achieved simultaneously.
Document ID
19790055025
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Clayton, R. M.
(California Institute of Technology, Jet Propulsion Laboratory, Control and Energy Div., Pasadena Calif., United States)
Date Acquired
August 9, 2013
Publication Date
June 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 79-1322
Meeting Information
Meeting: AIAA, SAE, and ASME, Joint Propulsion Conference
Location: Las Vegas, NV
Start Date: June 18, 1979
End Date: June 20, 1979
Sponsors: AIAA, ASME, SAE
Accession Number
79A39038
Funding Number(s)
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available