发明名称 |
GAS TURBINE ENGINE FLOW PATH GEOMETRY |
摘要 |
A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade. |
申请公布号 |
EP2971521(A2) |
申请公布日期 |
2016.01.20 |
申请号 |
EP20130861517 |
申请日期 |
2013.11.27 |
申请人 |
ROLLS-ROYCE CORPORATION |
发明人 |
POWER, BRONWYN;FULAYTER, ROY DAVID;RIVERS, JONATHAN M. |
分类号 |
F01D5/14 |
主分类号 |
F01D5/14 |
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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