发明名称 |
GAS TURBINE SPLIT RING |
摘要 |
<p>Gas turbine segmental ring has an increased rigidity to suppress a thermal deformation and enables less cooling air leakage by less number of connecting portions of segment structures. Cooling air (70) from a compressor flows through cooling holes (61) of an impingement plate (60) to enter a cavity (62) and to impinge on a segmental ring (1) for cooling thereof. The cooling air (70) further flows into cooling passages (64) from openings (63) of the cavity (62) for cooling an interior of the segmental ring (1) and is discharged into a gas path from openings of a rear end of the segmental ring (1). Waffle pattern (10) of ribs arranged in a lattice shape is formed on an upper surface of the segmental ring (1) to thereby increase the rigidity. A plurality of slits (6) are formed in flanges (4, 5) extending in the turbine circumferential direction to thereby absorb the deformation and thermal deformation of the segmental ring (1) is suppressed. <IMAGE></p> |
申请公布号 |
EP1178182(B1) |
申请公布日期 |
2013.08.14 |
申请号 |
EP20010906135 |
申请日期 |
2001.02.19 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
SHIOZAKI, SHIGEHIRO;TOMITA, YASUOKI |
分类号 |
F01D25/24;F01D9/04;F01D11/08;F01D25/12 |
主分类号 |
F01D25/24 |
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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