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US 2021/0071576 A1Published application
Gas turbine engine buffer system
AssigneeRaytheon Technologies Corporation
InventorsPeter M. Munsell, Philip S. Stripinis
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.
Claims20
A gas turbine engine, comprising:
- a buffer system that communicates a buffer supply air to a portion of the gas turbine, wherein said buffer system includes:
- a first bleed air supply having a first pressure;
- a second bleed air supply having a second pressure that is greater than said first pressure;
- and
- a valve that selects between said first bleed air supply and said second bleed air supply to communicate said buffer supply air to said portion of the gas turbine engine.
2 more elements
A gas turbine engine, comprising:
- a compressor section;
- a combustor in fluid communication with said compressor section;
- a turbine section in fluid communication with said combustor;
- at least one shaft that interconnects at least a portion of said compressor section and said turbine section;
- a bearing structure that supports said at least one shaft, wherein said bearing structure includes a bearing compartment;
- and
- a buffer system that selectively communicates a buffer supply air to pressurize said bearing compartment, wherein a low pressure bleed air supply is communicated to said bearing compartment in response to a high power condition of the gas turbine engine and a high pressure bleed supply air is communicated to said bearing compartment in response to a low power condition of the gas turbine engine.
4 more elements
A method of cooling a portion of a gas turbine engine, comprising:
- communicating a first bleed air supply to the portion in response to a low power condition of the gas turbine engine;
- and
- communicating a second bleed air supply to the portion in response to a high power condition of the gas turbine engine.
Dependencies are inferred from the claim text.