发明名称 |
HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING OUTER DIAMETER GAS EXTRACTION |
摘要 |
A compressor (100) for use in a gas turbine engine comprises a compressor rotor including blades (104) and a disc (102), with a bore (102A) defined radially inwardly of the disc (102). A radially outer housing (107) surrounds an outer diameter of the blades (104). A lower pressure tap (108) and a higher pressure tap (110) tap air from two distinct locations within the compressor (100) and radially outwardly through the outer housing (107). A valve (112) selectively delivers at least one of the lower pressure tap (108) and the higher pressure tap (110) to the bore (102A) of the disc (102). A control (113) for the valve (112) is programmed to move the valve (112) to a position delivering the higher pressure tap (110) at a point prior to take-off when the compressor (100) is mounted in a gas turbine engine on an aircraft. |
申请公布号 |
EP3015645(A1) |
申请公布日期 |
2016.05.04 |
申请号 |
EP20150192455 |
申请日期 |
2015.10.30 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
ACKERMANN, WILLIAM K.;FORCIER, MATTHEW P.;HIESTER, PAUL J. |
分类号 |
F01D5/08;F01D25/08;F04D29/32 |
主分类号 |
F01D5/08 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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