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Gas turbine engine oil buffering

A turbine engine, air flow technology, applied in gas turbine installations, engine components, engine functions, etc., can solve the problems of buffer air overheating, providing sufficient compartment pressurization, etc.

Active Publication Date: 2014-11-05
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In particular, high-pressure buffer air drawn from the high-pressure compressor is utilized, since at least one bearing compartment is located in a high-pressure environment where buffer air from the low-pressure compressor cannot provide sufficient compartment under low-power engine operating conditions pressurized
Unfortunately, the buffer air drawn from the high pressure compressor is too hot and needs to be cooled under higher power engine operating conditions

Method used

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  • Gas turbine engine oil buffering
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Embodiment Construction

[0026] This application describes a new pressurization and ventilation system for bearing compartments and shafts of gas turbine engines. In particular, the present application describes an assembly and method for providing damping and / or ventilation air to a bearing compartment and / or shaft of a gas turbine engine. The described gas turbine engine includes a dedicated centrifugal compressor that compresses discharge air from a low pressure compressor section and / or fan section of the gas turbine engine. Compressed air is delivered to the engine core to cushion the bearing compartment and / or vent one or more shafts. A centrifugal compressor compresses discharge air to a higher pressure more efficiently than a conventional axial compressor array because it avoids the kinetic energy losses and throttling losses experienced with a conventional axial compressor array at the compressor casing. By employing a centrifugal compressor, air is drawn from the fan section and / or low pres...

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Abstract

A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment.

Description

[0001] Cross References to Related Applications [0002] This disclosure is a continuation-in-part of US Patent Application No. 12 / 708,621, filed February 19, 2010. technical field [0003] The present invention relates generally to gas turbine engines, and more particularly to a system for supplying buffer air and ventilation air to bearing compartments and shafts in a gas turbine engine. Background technique [0004] In a typical multi-shaft bypass jet turbine engine, one shaft supports the rotors of the low pressure compressor and low pressure turbine, and the other shaft supports the rotors of the high pressure compressor and high pressure turbine. Typically, each shaft is supported by a bearing, and each bearing is lubricated by a forced lubrication system that circulates lubricating oil fed by a pump. [0005] In a forced lubrication system, high pressure air is drawn from a high pressure compressor and directed outside the oil seal of the bearing compartment to maint...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D15/12
CPCF02C6/08Y02T50/671F02K3/06F05D2260/40311F01D25/16F02C3/107F02C7/36
Inventor J.A.格拉恩F.M.施瓦兹
Owner UNITED TECH CORP