发明名称 Exhaust liner for gas turbine
摘要 An exhaust nozzle assembly (18) includes an inner liner (22) exposed to hot combustion gases and an outer liner (28) spaced a radial distance from the inner liner (22) to form an annular chamber (25). The inner liner (22) includes a hot side (24) that is directly exposed to the hot combustion gas flow and a cold side (26) that is exposed to cooling air within the chamber (25). The outer liner (28) includes an outer surface (30) exposed to cooling air flow up to a restriction (44) preventing communication of cooling air flow. A plenum (38) is attached to the outer liner (28) to define a plenum chamber (40) that extends into an end portion (45). The plenum chamber (40) receives cooling air flow from a supply opening (43) and communicates that air to the end portion (45) through a plurality of impingement openings (42) that provide impingement flow of cooling air outboard of the restriction (44).
申请公布号 EP1676993(B1) 申请公布日期 2016.04.06
申请号 EP20050256697 申请日期 2005.10.28
申请人 UNITED TECHNOLOGIES CORPORATION 发明人 FARAH, JORGE
分类号 F02K1/82 主分类号 F02K1/82
代理机构 代理人
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