Back to results
US 2015/0176501 A1Published application
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.
Claims19
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 turbine of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft.
1 more element
An aircraft comprising:
- a turbo-compressor comprising:
- a compressor and a turbine, the compressor having a compressor inlet and a compressor outlet, and the turbine having a turbine inlet and a turbine outlet;
- a first passageway to fluidly couple a first bleed air port from a compressor of an engine of the aircraft to the compressor inlet, the first passageway to provide bleed air at a first pressure from the compressor of the engine to the compressor inlet;
- a second passageway to fluidly couple a second bleed air port from a turbine of the engine to the turbine inlet, the second passageway to provide bleed air at a second pressure from the turbine of the engine to the turbine inlet, the second pressure higher than the first pressure;
- and
- a third passageway to fluidly couple the compressor outlet to a system of the aircraft that is to receive compressed air.
3 more elements
A method comprising:
- receiving, at a compressor inlet of a turbo-compressor, a first bleed air from a compressor of an aircraft engine, the turbo-compressor comprising a turbine operatively coupled to a compressor;
- receiving, at a turbine inlet of the turbo-compressor, a second bleed air from a high-pres sure turbine of the aircraft engine to drive the turbine of the turbo-compressor;
- increasing a pressure of the first bleed air in the compressor of the turbo-compressor;
- and
- after increasing the pressure of the first bleed air, discharging the first bleed air through a compressor outlet of the turbo-compressor to a system of the aircraft.
2 more elements
Dependencies are inferred from the claim text.