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US 8,615,980 B2Granted
Gas turbine engine with noise attenuating variable area fan nozzle
AssigneeUnited Technologies Corporation
InventorsRajendra K. Agrawal, Steven J. Sirica, William F. Schneider
Life of this patent
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Abstract
A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system.
Claims20
A rotary-wing aircraft comprising:
- a rotor system;
- a secondary propulsion system transverse to said rotor system;
- a gas generator operable to generate combustion gases;
- a first power turbine to receive said combustion gases from said gas generator, said first power turbine operable to drive said rotor system;
- an outer duct downstream of said first power turbine;
- an inner duct at least partially within said outer duct to define a bypass passage between said inner duct and said outer duct;
- and
- a retractable port movable between a closed position and an open position to selectively control flow of said combustion gases into said bypass passage to change a power distribution between said rotor system and said secondary propulsion system, wherein said secondary propulsion system is a pusher propeller.
5 more elements
A rotary-wing aircraft comprising:
- a rotor system;
- a secondary propulsion system transverse to said rotor system;
- a first power turbine operable to drive said rotor system;
- a second power turbine downstream of said first power turbine, said second power turbine operable to drive said secondary propulsion system;
- and
- an exhaust system to couple and uncouple said second power turbine and said first power turbine to change a power distribution between said rotor system and said secondary propulsion system, wherein said secondary propulsion system is a pusher propeller.
3 more elements
A rotary-wing aircraft comprising:
- a rotor system;
- a secondary propulsion system transverse to said rotor system;
- a gas generator operable to generate combustion gases;
- a first power turbine to receive said combustion gases, said first power turbine operable to drive said rotor system;
- an outer duct downstream of said first power turbine;
- a second power turbine downstream of said first power turbine, said second power turbine operable to drive said secondary propulsion system;
- an inner duct within said outer duct to define a bypass passage between said inner duct and said outer duct;
- and
- a retractable port movable between a closed position and an open position to selectively control flow of said combustion gases from said first power turbine into said bypass passage and change a power distribution between said rotor system and said secondary propulsion system, wherein said secondary propulsion system is a pusher propeller.
6 more elements
Dependencies are inferred from the claim text.