Patent ID: 6926232
Filing Date: 2005-08-09
Classification: F02K,Y02T

Abstract:
1. A variable cycle propulsion system for a supersonic airplane, the system comprising: at least one low-bypass ratio engine having at least one compressor and configured to generate thrust for supersonic flight speeds; at least one high-bypass ratio auxiliary propulsion assembly separate from said engine, and configured to generate additional horizontal thrust for takeoff, landing, and subsonic cruising speeds; and at least one pipe connecting the engine to the auxiliary propulsion assembly to convey thereto compressed air produced by the compressor to enable the auxiliary propulsion assembly to generate additional horizontal thrust for takeoff, landing, and subsonic cruising flight and to reduce noise during takeoff, landing, and subsonic cruising flight by increasing a bypass ratio of said propulsion system, at least one valve provided for enabling the at least one pipe to be closed off for supersonic cruising flight, wherein the at least one auxiliary propulsion assembly is housed in an airplane fuselage, wherein louvers are provided in the fuselage, wherein said louvers are open as to feed air to the at least one auxiliary propulsion assembly during takeoff, landing, and subsonic cruising flight, and said louvers are closed for supersonic cruising flight, and wherein retractable exhaust nozzles are provided to exhaust the thrust-producing gas during stages of flight.