Power plants – Reaction motor – Air passage bypasses combustion chamber
Patent
1997-08-01
1999-08-31
Casaregola, Louis J.
Power plants
Reaction motor
Air passage bypasses combustion chamber
181220, F02K 304
Patent
active
059438568
ABSTRACT:
A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level. There is a fan at the upstream end of the core engine for generating axial fan air flow through bypass ducts terminating at a common nozzle, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A target thrust reverser includes opposing doors rotatable into position to block and divert the flow of exhaust gas for generating reverse thrust. Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine. An acoustically dampened light bulb-shaped nose cone is provided for coaxial attachment to an upstream end of the core engine. The axial flow front fan is axially separated from the inlet guide vane is extended relatively forwardly. A bleed air valve, selectively operational to bleed air from the core engine when the valve is open, is ducted for directing bleed air to the vicinity of the common nozzle.
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Photocopies of 11 photographs of the Boeing Company 707-320C modified engine in 1971.
Douglas
Lillibridge Robert W.
Matthews Eugene James
McGuire Kenneth R.
Phillips Edward J.
Burbank Aeronautical Corporation II
Casaregola Louis J.
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