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US 10,502,135 B2Granted
Buffer system for communicating one or more buffer supply airs throughout a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsWilliam K. Ackermann, Philip S. Stripinis
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a buffer system. The buffer system can include a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the buffer supply air at an acceptable temperature to anti-ice the hardware of said fan section.
Claims16
A gas turbine engine, comprising:
- a buffer system, wherein said buffer system includes:
- a first bleed air supply;
- a conditioning device that conditions said first bleed air supply to render a buffer supply air at an acceptable temperature for pressurizing at least one bearing structure and at least a portion of anti-icing hardware of a fan section of the gas turbine engine, wherein separate buffer supply airs are communicated to said at least one bearing structure and said at least a portion of anti-icing hardware;
- a sensor configured to detect a flight condition of the gas turbine engine;
- and
- a controller configured to control operation of said conditioning device and command communication of said buffer supply air to said anti-icing hardware in response to detection of said flight condition,
- wherein a portion of said buffer supply air is communicated in a downstream direction to condition other portions of the gas turbine engine separate from said at least one bearing structure and said hardware.
4 more elements
A gas turbine engine, comprising:
- a fan section;
- a compressor section in fluid communication with said fan 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;
- and
- a buffer system that communicates a first buffer supply air to at least a spinner of said fan section to anti-ice said spinner and a second buffer supply air separate from said first buffer supply air to at least a portion of said bearing structure, wherein said buffer system includes a first bleed air supply, a conditioning device that conditions said first bleed air supply to render said first buffer supply air and said second buffer supply air at an acceptable temperature, a sensor configured to detect a flight condition of the gas turbine engine, and a controller configured to control operation of said conditioning device to command said second buffer supply air at an adequate differential pressure for sealing said bearing structure and configured to command communication of said first buffer supply air in response to detection of said flight condition,
- wherein a portion of either of said first buffer supply air and said second buffer supply air is communicated in a downstream direction to condition other portions of the gas turbine engine separate from said bearing structure and said spinner.
6 more elements
Dependencies are inferred from the claim text.