TURBOCOMPRESSOR FOR AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM
First Claim
1. A bleed air system for an aircraft comprising:
- a turbocompressor including a turbine portion coupled to drive a compressor portion, the compressor portion including a compressor inlet and a compressor air discharge, the turbine portion including a turbine inlet and a turbine discharge;
a passage delivering air to the compressor inlet from one or more locations of an engine;
a passage delivering air to the turbine inlet from at least one or more locations of the engine;
a passage receiving air from the compressor discharge selectively delivered to one or more locations of the engine;
an outlet passage receiving air from the turbine discharge communicating airflow to an aircraft system; and
a controller to direct inlet and discharge airflow of the compressor portion and the turbine portion to control operation of the turbocompressor.
3 Assignments
0 Petitions
Accused Products
Abstract
A bleed air system for an aircraft includes a turbocompressor including a turbine portion coupled to drive a compressor portion. The compressor portion includes a compressor inlet and a compressor air discharge. The turbine portion includes a turbine inlet and a turbine discharge. A passage delivers air to the compressor inlet from one or more locations of an engine. A passage delivers air to the turbine inlet from at least one or more locations of the engine. A passage receives air from the compressor discharge selectively delivered to one or more locations of the engine. An outlet passage receives air from the turbine discharge communicating airflow to an aircraft system. A controller directs inlet and discharge airflow of the compressor portion and the turbine portion to control operation of the turbocompressor. A gas turbine engine and a method are also disclosed.
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Citations
19 Claims
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1. A bleed air system for an aircraft comprising:
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a turbocompressor including a turbine portion coupled to drive a compressor portion, the compressor portion including a compressor inlet and a compressor air discharge, the turbine portion including a turbine inlet and a turbine discharge; a passage delivering air to the compressor inlet from one or more locations of an engine; a passage delivering air to the turbine inlet from at least one or more locations of the engine; a passage receiving air from the compressor discharge selectively delivered to one or more locations of the engine; an outlet passage receiving air from the turbine discharge communicating airflow to an aircraft system; and a controller to direct inlet and discharge airflow of the compressor portion and the turbine portion to control operation of the turbocompressor. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A gas turbine engine assembly comprising:
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a core engine including a compressor section disposed about an engine axis; and a bleed air system for supplying airflow from the compressor section to at least one aircraft system, the bleed air system comprising; a turbocompressor including a turbine portion coupled to drive a compressor portion, the compressor portion including a compressor inlet and a compressor air discharge, the turbine portion including a turbine inlet and a turbine discharge; a passage delivering air to the compressor inlet from one or more locations of the core engine; a passage delivering air to the turbine inlet from at least one or more locations of the compressor section; a passage receiving air from the compressor discharge selectively delivered to one or more locations of the core engine; an outlet passage receiving air from the turbine discharge communicating airflow to an aircraft system; and a controller to direct inlet and discharge airflow of the compressor portion and the turbine portion to control operation of the turbocompressor. - View Dependent Claims (12, 13, 14, 15, 16)
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17. A method of operating a bleed air system comprising:
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providing air from a first source at a first temperature and a first pressure through a first inlet; providing air from a second source at a second temperature and a second pressure through a second inlet, wherein the second temperature and the second pressure are higher than the first pressure and the first temperature; receiving airflow from the first inlet at a compressor portion of a turbocompressor, and receiving airflow in a turbine portion of the turbocompressor, the received airflow from the turbine portion communicated from one of the first inlet and the second inlet; and outputting airflow from the turbine portion to an outlet passage communicating airflow to an aircraft system. - View Dependent Claims (18, 19)
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Specification