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US 8,967,528 B2Granted
Bleed air systems for use with aircrafts and related methods
AssigneeThe Boeing Company
InventorsSteve G. Mackin, George A. Ludlow
Life of this patent
Estimating the term…
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.
Claims23
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.
1 more element
An apparatus comprising:
- 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.
2 more elements
A method comprising:
- 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.
1 more element
Dependencies are inferred from the claim text.