| 发明名称 |
GAS TURBINE ENGINE AND TURBINE ENGINE COMPONENT |
| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a means minimizing danger of fire of an aircraft engine and reducing possibility of flame propagation. <P>SOLUTION: A gas turbine engine includes an engine casing concentrically disposed around a low pressure compressor, a turbine and a high pressure compressor having at least one bleed tube and at least one joint proximate to the engine casing; and at least one flame prevention device adapted to cover at least a portion of at least one gas turbine engine component. <P>COPYRIGHT: (C)2008,JPO&INPIT</p> |
| 申请公布号 |
JP2008151140(A) |
申请公布日期 |
2008.07.03 |
| 申请号 |
JP20070325361 |
申请日期 |
2007.12.18 |
| 申请人 |
UNITED TECHNOL CORP <UTC> |
发明人 |
SCHLICHTING KEVIN W;BLANKENSHIP DONN R;FRELING MELVIN;MICHAEL J MALONEY |
| 分类号 |
F01D25/00;F02C7/00 |
主分类号 |
F01D25/00 |
| 代理机构 |
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代理人 |
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