Bleed air systems for use with aircrafts and related methods
First Claim
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1. An apparatus comprising:
- a turbo-compressor including;
a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft; and
a turbine having a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft, wherein the turbo-compressor is to increase a pressure of bleed air received from the low-pressure compressor, and wherein the high-pressure compressor has a higher pressure than the low-pressure compressor.
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Abstract
Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of the aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft. The turbo-compressor also includes a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft.
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Citations
23 Claims
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1. An apparatus comprising:
a turbo-compressor including; a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft; and a turbine having a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft, wherein the turbo-compressor is to increase a pressure of bleed air received from the low-pressure compressor, and wherein the high-pressure compressor has a higher pressure than the low-pressure compressor. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 23)
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9. An apparatus comprising:
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a turbo-compressor comprising a compressor and a turbine; a first passageway to fluidly couple a low-pressure bleed air port from a low-pressure compressor of an aircraft engine to a compressor inlet of the turbo-compressor, the low-pressure bleed air port to provide bleed air at a first pressure from the low-pressure compressor to the compressor inlet of the turbo-compressor; a second passageway to fluidly couple a high-pressure bleed air port from a high-pressure compressor of the aircraft engine to a turbine inlet of the turbo-compressor, wherein the high-pressure compressor has a higher pressure than the low-pressure compressor; and a third passageway to fluidly couple a compressor outlet of the turbo-compressor to a system of the aircraft, the compressor to increase the pressure of the bleed air received at the compressor inlet to a second pressure at the compressor outlet, the second pressure being higher than the first pressure. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16, 17, 18)
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19. A method comprising:
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fluidly coupling a compressor inlet of a turbo-compressor to a low-pressure bleed air source provided by a low-pressure compressor of an aircraft engine, the turbo-compressor comprising a compressor and a turbine different from a compressor and a turbine, respectively, of the aircraft engine; fluidly coupling a compressor outlet of the turbo-compressor to a first system of the aircraft that receives a bleed air supply; and fluidly coupling a turbine inlet of the turbo-compressor to a high-pressure bleed air source provided by a high-pressure compressor of the aircraft engine, the high-pressure bleed air to drive a turbine operatively coupled to the compressor, wherein the turbo-compressor is to increase a pressure of bleed air received from the low-pressure compressor, wherein the high-pressure compressor has a higher pressure than the low-pressure compressor. - View Dependent Claims (20, 21, 22)
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Specification