AIRCRAFT USING TURBO-ELECTRIC HYBRID PROPULSION SYSTEM
First Claim
1. A method of providing motive power to an aircraft, said method comprising:
- coupling a hybrid propulsion system to a thrust producing device, said hybrid propulsion system comprising;
a gas turbine engine;
an electric storage device configured to deliver an electric current;
an electrical generator responsive to said gas turbine engine such that power produced by the operation thereof is converted into electric current; and
an electric motor selectively responsive to said electrical generator and said electric storage device; and
operating one of said gas turbine engine and said electric storage device such that power produced therefrom causes said electric motor to operate said thrust producing device.
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Accused Products
Abstract
An air vehicle incorporating a hybrid propulsion system. The system includes a gas turbine engine as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to a DC electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engine can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro.
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Citations
18 Claims
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1. A method of providing motive power to an aircraft, said method comprising:
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coupling a hybrid propulsion system to a thrust producing device, said hybrid propulsion system comprising; a gas turbine engine; an electric storage device configured to deliver an electric current; an electrical generator responsive to said gas turbine engine such that power produced by the operation thereof is converted into electric current; and an electric motor selectively responsive to said electrical generator and said electric storage device; and operating one of said gas turbine engine and said electric storage device such that power produced therefrom causes said electric motor to operate said thrust producing device. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A method of reducing the in-flight thermal output of a rotary-winged aircraft propulsion system, said method comprising:
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coupling a hybrid propulsion system to a thrust producing device, said hybrid propulsion system comprising; a gas turbine engine; an electric storage device configured to deliver an electric current; an electrical generator responsive to said gas turbine engine such that power produced by the operation thereof is converted into electric current; and an electric motor selectively responsive to said electrical generator and said electric storage device; and operating one of said gas turbine engine and said electric storage device such that power produced therefrom causes said electric motor to operate said thrust producing device.
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10. An aircraft comprising:
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a fuselage; a thrust-producing device coupled to said fuselage; and a hybrid propulsion system selectively coupled to said thrust-producing device such that cooperation therebetween provides motive power to said aircraft, said hybrid propulsion system comprising; a gas turbine engine configured to operate over at least a first portion of said aircraft'"'"'s flight envelope; an electrical generator cooperative with said gas turbine engine such that mechanical power received therefrom by said electrical generator is converted to electric power; an electric storage device configured to operate over at least a second portion of said aircraft'"'"'s flight envelope; and an electric motor selectively coupled to at least one of said electrical generator and said electric storage device such that during said first portion of the aircraft'"'"'s flight envelope, said gas turbine engine and said thrust-producing device provides at least a majority of said motive power, and during a second portion of the aircraft'"'"'s flight envelope, said electric storage device and said thrust-producing device provides at least a majority of said motive power. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18)
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Specification