Aircraft and airborne electrical power and thermal management system
First Claim
1. An airborne electrical power and thermal management system, comprising:
- a first gas turbine engine having a first combustor, a first turbine and a bleed air port, the first gas turbine engine operable for producing propulsive power for an aircraft;
a second gas turbine engine including;
a second combustor in fluid communication with the first gas turbine engine bleed air port; and
a second turbine in fluid communication with the second combustor;
a generator powered by the second turbine and configured to provide electrical power to an electrical load;
a refrigerant compressor powered by the second turbine;
a condenser in fluid communication with the refrigerant compressor; and
at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract heat from at least one heat source;
wherein the second gas turbine engine, the generator, the refrigerant compressor and the condenser are disposed in an aircraft external pod;
wherein the at least one evaporator is disposed in the aircraft external pod or an aircraft fuselage.
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Accused Products
Abstract
A unique airborne electrical power and thermal management system and a unique aircraft having a unique airborne electrical power and thermal management system are provided. The electrical power and thermal management system includes a turbine, which may power loads, for example but not limited to, a generator and a refrigerant compressor. The turbine may be in fluid communication with a gas turbine engine bleed air source to extract power from bleed air for powering the loads. A combustor may be fluidly disposed between the bleed air source and the turbine. The turbine may be part of a gas turbine engine distinct from a propulsion gas turbine engine. In one aspect, at least a portion of the electrical power and thermal management system may be disposed within an aircraft external pod. The pod may be configured to appear similar to a conventional external fuel tank pod employed by the aircraft.
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Citations
20 Claims
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1. An airborne electrical power and thermal management system, comprising:
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a first gas turbine engine having a first combustor, a first turbine and a bleed air port, the first gas turbine engine operable for producing propulsive power for an aircraft; a second gas turbine engine including; a second combustor in fluid communication with the first gas turbine engine bleed air port; and a second turbine in fluid communication with the second combustor; a generator powered by the second turbine and configured to provide electrical power to an electrical load; a refrigerant compressor powered by the second turbine; a condenser in fluid communication with the refrigerant compressor; and at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract heat from at least one heat source; wherein the second gas turbine engine, the generator, the refrigerant compressor and the condenser are disposed in an aircraft external pod; wherein the at least one evaporator is disposed in the aircraft external pod or an aircraft fuselage. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. An aircraft, comprising:
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a fuselage; a wing coupled to the fuselage; an empennage coupled to at least one of the fuselage and the wing; a first gas turbine engine propulsion system having a first combustor and a first turbine coupled to the aircraft and having a bleed air port; an external pod coupled to the aircraft; and an electrical power and thermal management system including a second gas turbine engine comprising a; second combustor in fluid communication with the bleed air port; and a second turbine in fluid communication with the second combustor; a generator powered by the second turbine and configured to provide electrical power to an aircraft electrical load; a refrigerant compressor powered by the second turbine; a condenser in fluid communication with the refrigerant compressor; and at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract heat from at least one heat source wherein the second gas turbine engine, the generator, the refrigerant compressor and the condenser are disposed in the external pod; wherein the at least one evaporator is disposed in the external pod or the fuselage. - View Dependent Claims (9, 10, 11, 12, 13, 14, 15, 16)
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17. An aircraft, comprising:
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a fuselage; a wing coupled to the fuselage; an empennage coupled to at least one of the fuselage and the wing; a fuel tank; a first gas turbine engine propulsion system having a bleed air port and a first combustor to provide energy for aircraft propulsion; an electrical power and thermal management system including a second gas turbine engine, at least one evaporator, a refrigerant compressor, and a condenser, wherein the second gas turbine engine has a second combustor to provide energy for electrical power and thermal management, and wherein the second combustor is in fluid communication with the bleed air port of the first gas turbine engine and the fuel tank; and an external pod, wherein the second gas turbine engine, the refrigerant compressor, and the condenser of the electrical power and thermal management system are disposed in the external pod; wherein the at least one evaporator is disposed in the external pod or the fuselage. - View Dependent Claims (18)
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19. An aircraft, comprising:
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a fuselage; a wing coupled to the fuselage; an empennage coupled to at least one of the fuselage and the wing; a first gas turbine engine propulsion system having a first combustor and a first turbine coupled to the aircraft for providing propulsive thrust to the aircraft; an external pod coupled to the aircraft; and an electrical power and thermal management system including a second gas turbine engine having a second combustor and a second turbine; a generator powered by the second gas turbine engine and configured to provide electrical power to an aircraft electrical load; a refrigerant compressor powered by the second gas turbine engine; a condenser in fluid communication with the refrigerant compressor; and at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract heat from at least one heat source wherein the second gas turbine engine, the generator, the refrigerant compressor and the condenser are disposed in the external pod; wherein the at least one evaporator is disposed in either the external pod or the fuselage wherein the aircraft electrical load and the at least one heat source are disposed in the fuselage. - View Dependent Claims (20)
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Specification