发明名称 |
COMPRESSOR AIRFOIL TIP CLEARANCE OPTIMIZATION SYSTEM |
摘要 |
A compressor airfoil tip clearance optimization system for reducing a gap between a tip of a compressor airfoil and a radially adjacent component of a turbine engine is disclosed. The turbine engine may include ID and OD flowpath boundaries configured to minimize compressor airfoil tip clearances during turbine engine operation in cooperation with one or more clearance reduction systems that are configured to move the rotor assembly axially to reduce tip clearance. The configurations of the ID and OD flowpath boundaries enhance the effectiveness of the axial movement of the rotor assembly, which includes movement of the ID flowpath boundary. During operation of the turbine engine, the rotor assembly may be moved axially to increase the efficiency of the turbine engine.
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申请公布号 |
US2013156578(A1) |
申请公布日期 |
2013.06.20 |
申请号 |
US201113326399 |
申请日期 |
2011.12.15 |
申请人 |
LITTLE DAVID A.;PU ZHENGXIANG |
发明人 |
LITTLE DAVID A.;PU ZHENGXIANG |
分类号 |
F04D29/18 |
主分类号 |
F04D29/18 |
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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