A variable flow fan aircraft propulsion system offers the potential for achieving a low specific thrust with high flow and low jet velocity requirement as specified for takeoff, side-line noise, initial climb, and a high specific thrust requirement for climb and acceleration to supersonic cruise. These requirements are conflicting. To achieve this, the operating envelope of a variable flow fan has to be expanded over existing turbofan engines. The variable flow fan concept (i.e., the Variable Fan Exit or “VFX”) can efficiently operate beyond the usual fan (or compressor) stall operating line using novel methods of designing and scheduling the fan geometry as a function of flight Mach Number, fan pressure ratio and corrected speed. Fan geometry is altered by using variable inlet guide vanes (IGV’s), variable stators, and variable outlet guide vanes (OGV’s).
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ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
June 2–5, 1997
Orlando, Florida, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7868-2
PROCEEDINGS PAPER
Variable Flow Turbofan Engine for an HSCT Application
George L. Converse,
George L. Converse
DIVERSITECH Inc., Cincinnati, OH
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Donald K. Dunbar,
Donald K. Dunbar
DIVERSITECH Inc., Cincinnati, OH
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Marlen L. Miller,
Marlen L. Miller
DIVERSITECH Inc., Cincinnati, OH
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Paul D. Hoskins,
Paul D. Hoskins
DIVERSITECH Inc., Cincinnati, OH
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Scott M. Jones
Scott M. Jones
NASA Lewis Research Center, Cleveland, OH
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George L. Converse
DIVERSITECH Inc., Cincinnati, OH
Donald K. Dunbar
DIVERSITECH Inc., Cincinnati, OH
Marlen L. Miller
DIVERSITECH Inc., Cincinnati, OH
Paul D. Hoskins
DIVERSITECH Inc., Cincinnati, OH
Scott M. Jones
NASA Lewis Research Center, Cleveland, OH
Paper No:
97-GT-264, V001T01A009; 6 pages
Published Online:
December 24, 2014
Citation
Converse, GL, Dunbar, DK, Miller, ML, Hoskins, PD, & Jones, SM. "Variable Flow Turbofan Engine for an HSCT Application." Proceedings of the ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. Orlando, Florida, USA. June 2–5, 1997. V001T01A009. ASME. https://doi.org/10.1115/97-GT-264
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