Introducing the VRT gas turbine combustor
An 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.
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
- OSTI ID:
- 6874396
- Report Number(s):
- N-90-23591; NASA-TM-103176; E-5554; NAS-1.15:103176; AIAA-90-2452; CONF-900720-
- Resource Relation:
- Conference: 26. AIAA/SAE/ASME/ASEE joint propulsion conference and exhibit, Orlando, FL (USA), 16-18 Jul 1990
- Country of Publication:
- United States
- Language:
- English
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