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ENGINE BLEED SYSTEM WITH MULTI-TAP BLEED ARRAY
专利权人:
Hamilton Sundstrand Corporation
发明人:
Schwarz Frederick M.
申请号:
US201615070462
公开号:
US2017268431(A1)
申请日:
2016.03.15
申请国别(地区):
美国
年份:
2017
代理人:
摘要:
An engine bleed control system for a gas turbine engine of an aircraft is provided. The engine bleed control system includes a multi-tap bleed array including engine bleed taps coupled to a compressor source of a lower pressure compressor section before a highest pressure compressor section of the gas turbine engine. A highest stage of the engine bleed taps has a maximum bleed temperature below an auto-ignition point of a fuel-air mixture of the aircraft at idle engine power at a maximum aircraft altitude and a pressure suitable for pressurizing the aircraft at the maximum aircraft altitude. The engine bleed control system also includes a plurality of valves operable to extract bleed air from each of the engine bleed taps. A controller is operable to selectively open and close each of the valves based on a bleed air demand and control delivery of the bleed air to an aircraft use.
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中国工程科技知识中心
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