Multi-mode combined cycle propulsion engine
AssigneeATRX, Inc.
InventorsJohn A Bossard, John L Bergmans
Life of this patent
Estimating the term…
Abstract
A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.
Claims18
A turbojet engine capable of operation in a turbojet mode or an Air Turbo Rocket (ATR) mode or a combination thereof, said turbojet engine comprising:
- an air inlet;
- a compressor;
- a turbine assembly, said turbine assembly comprising a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, and a turbine shaft configured to power said compressor;
- and
- a first combustor located between the compressor and the turbine assembly, said first combustor configured to burn fuel from a fuel supply in compressed air from the compressor when operating in said turbojet mode to generate combustion products that expand through the turbine assembly to provide shaft power to drive the compressor;
- a gas generator configured to generate a hot, fuel rich gas;
- and
- a second combustor positioned downstream of the turbine assembly and configured to combust said hot, fuel rich gas in air compressed by said compressor when operating in said ATR mode,
- wherein said hot, fuel rich gas from the gas generator is directed onto the turbine blades and wherein the turbojet engine is configured for transitioning between said turbojet mode in which the gas generator is inactive and fuel is supplied to the first combustor and said ATR mode in which the gas generator is active and no fuel is supplied to the first combustor.
A method for modifying a turbojet engine to make said turbojet engine capable of operating in a first turbojet mode or an Air Turbo Rocket (ATR) mode or both, said turbojet engine comprising a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, and a first combustor located between the compressor and the non-rotating guide vane ring, said method comprising:
- providing a gas generator configured to produce a hot, fuel rich gas;
- connecting an effluent gas manifold to said gas generator to receive said hot, fuel rich gas;
- connecting said effluent gas manifold to a means for directing said hot, fuel rich gas onto the turbine blades;
- positioning a second combustor aft of the rotatable turbine wheel and configuring the second combustor to combust said hot, fuel rich gas in air compressed by said compressor when the turbojet engine is operating in said ATR mode;
- and
- providing the turbojet engine with controls configured to control a fuel flow into the first combustor and operation of the gas generator to transition between said first turbojet operating mode in which the gas generator is inactive and fuel is supplied to the first combustor and said ATR mode in which the gas generator is active and no fuel is supplied to the first combustor.
A method for modifying an afterburning turbojet engine to make said afterburning turbojet engine capable of operating in a first turbojet mode, an afterburning turbojet mode, an Air Turbo Rocket (ATR) mode or any combination of these, said turbojet engine comprising a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor located between the compressor and the non-rotating guide vane ring, and an afterburner, said method comprising:
- providing a gas generator configured to produce a hot, fuel rich gas;
- connecting an effluent gas manifold to said gas generator to receive said hot, fuel rich gas;
- connecting said effluent gas manifold to a means for directing said hot, fuel rich gas onto the turbine blades to combust said hot, fuel rich gas in air compressed by said compressor in the afterburner when the turbojet engine is operating in said ATR mode;
- and
- providing the turbojet engine with controls configured to control a fuel flow into the combustor and operation of the gas generator to transition between said first turbojet operating mode in which the gas generator is inactive and fuel is supplied to the combustor and said ATR mode in which the gas generator is active and no fuel is supplied to the combustor and between said afterburning turbojet mode and said ATR mode.
Dependencies are inferred from the claim text.