Transverse mounted gas turbine engine
First Claim
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1. A propulsion engine of an aircraft comprising:
- a compressor, a combustor and a turbine mounted in flow series about a turbine axis;
a shaft coupled to the turbine along the turbine axis; and
first and second propulsion fans rotationally coupled to the turbine at opposite ends of the shaft;
wherein the first and second propulsion fans rotate about axes that are substantially parallel to one another, and wherein the axes of the first and second propulsion fans are also transverse with respect to the turbine axis;
wherein the propulsion engine is mounted transversely in a fuselage of the aircraft.
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Abstract
A propulsion engine comprises a compressor, a combustor and a turbine arranged in flow series about a turbine axis. A shaft is coupled to the turbine along the turbine axis, and first and second propulsions fans are rotationally coupled to the turbine at opposite ends of the shaft. The first and second propulsion fans rotate substantially parallel to one another, and transversely with respect to the turbine axis.
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Citations
18 Claims
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1. A propulsion engine of an aircraft comprising:
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a compressor, a combustor and a turbine mounted in flow series about a turbine axis; a shaft coupled to the turbine along the turbine axis; and first and second propulsion fans rotationally coupled to the turbine at opposite ends of the shaft; wherein the first and second propulsion fans rotate about axes that are substantially parallel to one another, and wherein the axes of the first and second propulsion fans are also transverse with respect to the turbine axis; wherein the propulsion engine is mounted transversely in a fuselage of the aircraft. - View Dependent Claims (2, 3, 4, 5)
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6. A gas turbine engine of an aircraft having a fuselage comprising:
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a single power core comprising a compressor, a combustor and a power turbine rotationally coupled about a turbine axis; two propulsion fans transversely coupled to the single power core via a power shaft, wherein the power shaft is oriented along the turbine axis; and
gearboxes rotationally coupling the two propulsion fans to the power shaft;
wherein the two propulsion fans each rotate about axes that are transverse to the turbine axis;wherein the single power core is mounted transversely to the fuselage and the two propulsion fans rotate longitudinally with respect to the fuselage. - View Dependent Claims (7, 8, 9, 10, 11)
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12. An aircraft comprising:
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a fuselage having a nose section and a tail section separated along a longitudinal axis; a wing mounted to the fuselage between the nose section and the tail section; a compressor, a combustor and a turbine mounted in the fuselage, the compressor and turbine rotationally coupled about a turbine axis that is transverse to the longitudinal axis of the fuselage; and twin fan assemblies mounted on opposites sides of the fuselage, each of the twin fan assemblies comprising a propulsion fan rotational coupled to the turbine; wherein each of the twin fan assemblies rotates about an axis that is transverse with respect to the turbine axis and longitudinal with respect to the fuselage axis. - View Dependent Claims (13, 14, 15, 16, 17, 18)
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Specification