发明名称 |
RADIATION SHIELD FOR A GAS TURBINE COMBUSTOR |
摘要 |
<p>A method is disclosed for directing flow to a combustor embedded in a recuperator while shielding the recuperator from radiative heat transfer from the combustor. The radiation heat shield also serves as a structural component to center the combustor within the recuperator core cavity and to allow motion between the combustor and recuperator as temperatures vary. The disclosure is illustrated by the example a gas turbine engine comprising three turbomachinery spools, an intercooler, a recuperator and a combustor. Thermal efficiency of such an engine can be increased by raising the high pressure turbine inlet temperature. It is a specific goal of the present disclosure to reduce radiative heating of a recuperator by a combustor which is housed substantially inside the recuperator.</p> |
申请公布号 |
EP2673490(A1) |
申请公布日期 |
2013.12.18 |
申请号 |
EP20120747787 |
申请日期 |
2012.02.14 |
申请人 |
ICR TURBINE ENGINE CORPORATION |
发明人 |
NASH, JAMES, S.;MOERLEIN, ALEX |
分类号 |
F02C7/08 |
主分类号 |
F02C7/08 |
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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