发明名称 |
Method for Designing a Low-Pressure Turbine of an Aircraft Engine, and Low-Pressure Turbine |
摘要 |
A low-pressure turbine of a gas turbine is disclosed. The turbine comprises a number of stages arranged one behind the other in an axial manner in the flow-through direction of the turbine. Each stage is formed from a fixed vane ring having a number of vanes and from a rotating blade ring having a number of blades. Each stage is characterized by a characteristic value vane-to-blade ratio that indicates the ratio of the number of vanes to the number of blades within a stage. One of the stages of the turbine is designed in such a manner that, in the event of noise-critical conditions of the turbine, the characteristic value vane-to-blade ratio of this stage is between a lower cut-off limit for mode k=-1 of the blade-passing frequency (BPF) of said stage and an upper cut-off limit for the mode k=-2 of the blade-passing frequency (BPF) of this stage.
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申请公布号 |
US2008022691(A1) |
申请公布日期 |
2008.01.31 |
申请号 |
US20050547581 |
申请日期 |
2005.03.11 |
申请人 |
MTU AERO ENGINES GMBH |
发明人 |
KENNEPOHL FRITZ;KORTE DETLEF |
分类号 |
F02C3/10;F01D5/10;F01D5/26 |
主分类号 |
F02C3/10 |
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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