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Introducing the VRT gas turbine combustorAn innovative annular combustor configuration is being developed for aircraft and other gas turbine engines. This design has the potential of permitting higher turbine inlet temperatures by reducing the pattern factor and providing a major reduction in NO(x) emission. The design concept is based on a Variable Residence Time (VRT) technique which allows large fuel particles adequate time to completely burn in the circumferentially mixed primary zone. High durability of the combustor is achieved by dual function use of the incoming air. The feasibility of the concept was demonstrated by water analogue tests and 3-D computer modeling. The computer model predicted a 50 percent reduction in pattern factor when compared to a state of the art conventional combustor. The VRT combustor uses only half the number of fuel nozzles of the conventional configuration. The results of the chemical kinetics model require further investigation, as the NO(x) predictions did not correlate with the available experimental and analytical data base.
Document ID
19900014275
Document Type
Conference Paper
Authors
Melconian, Jerry O. (SOL-3 Resources, Inc., Reading MA., United States)
Mostafa, Abdu A. (Textron Lycoming Stratford, CT., United States)
Nguyen, Hung Lee (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
ENGINEERING (GENERAL)
Report/Patent Number
E-5554
NASA-TM-103176
NAS 1.15:103176
AIAA PAPER 90-2452
Meeting Information
Joint Propulsion Conference(Orlando, FL)
Funding Number(s)
PROJECT: RTOP 537-01-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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