Cast in place gas turbine containment ring and method of manufacture专利检索-安全壳混凝土屏蔽层防辐射专利检索查询-专利查询网

Cast in place gas turbine containment ring and method of manufacture

阅读：414发布：2022-01-29

专利汇可以提供Cast in place gas turbine containment ring and method of manufacture专利检索，专利查询，专利分析的服务。并且A cast iron gas turbine engine block has an integrally formed internal wall configuration which defines a centrally located exhaust gas passage through the block and a radially outwardly located cooling air passage for directing cooling gas around the exhaust gas passage, a pair of separate inner walls are spaced apart and each includes a plurality of integrally formed circumferentially arranged posts thereon directed into the passage and having the tip portions thereon formed in situ of side grooves on a steel turbine wheel containment ring: the ring of posts in each of the side wall grooves of the ring locate it radially outwardly of an annular inner wall of the cast iron housing and form air flow openings around the ring to enable the cooling air directed through the cooling air passage to completely surround and circulate around the ring for cooling it during turbine operation.，下面是Cast in place gas turbine containment ring and method of manufacture专利的具体信息内容。

权利要求

1. In a gas turbine engine, a cast iron block having a central bore therethrough including an annular turbine shroud wall, means including a liner defining a burner exhaust gas passage, radially inwardly of said shroud wall, a turbine wheel having a plurality of blades directed radially outwardly of said wheel, each of said blades including a tip portion thereon located in closed spaced relationship to said liner, means for supporting said wheel for high speed rotation relative to said shroud, said block having spaced apart internal wall portions located radially outwardly of said shroud defining an air cooling passage formed in surrounding circumferential relationship to said shroud, a plurality of integral cast iron pins formed on said spaced apart internal wall portions, pins on one of said spaced apart wall portions defining a circular pattern thereon, pins on the opposite internal wall forming a second circular pattern thereon, a metal containment ring located in said cooling passage radially outwardly of said shroud having an inside diameter in spaced relationship to said casting shroud wall to form a circumferential cooling space radially inwardly of each of said first and second circular pattern of pins, said metal containment ring including a pair of side walls thereon each having a continuous circumferential groove formed therearound, each of said posts on said walls having the tip portions thereof formed in situ in one of said grooves to rigidly locate said metal containment ring in said cooling passage in radially spaced surrounding relationship to said turbine wheel.

2. In a gas turbine engine, the combination of a cast iron housing having a pair of open ends thereon and a centrally located annular housing portion arranged colinearly of said pair of open ends, means including an annular shroud located radially inwardly of said annular housing portion defining a burner exhaust passage through the interior of said cast iron housing, means including a ring of turbine blades located within said exhaust passage radially inwardly of said annular shroud for operating at a high speed in response to flow through said burner exhaust gas passage, said cast iron housing including spaced apart interior wall portions located radially outwardly of said annular housing portion to define an open air cooling passage in surrounding relationship to said inner annular portion, means for directing cooling air through said passage, a metal containment ring located within said air cooling passage radially outwardly of said inner annular housing portion, said ring including side walls thereon located in spaced relationship to said spaced apart interior wall portions of said housing, said ring being formed continuously circumferentially around said annular housinG portion with the inside diameter of said ring being in spaced relationship to said annular portion, an annular groove formed in each of said ring side walls continuously around said ring, a first plurality of integrally formed retaining posts on one of said interior wall portions, each post being directed outwardly into said cooling passage and having portions thereon formed in situ within one of said grooves, a second plurality of posts formed integrally on the other of said interior wall portions, each of said second plurality of posts being directed into said cooling passage to have the tip thereof secured in situ within the other of said grooves thereby to retain said ring rigidly with respect to said cast housing, said posts having passages formed therebetween wherein cooling air directed through said cooling passage flows completely around said ring and against the outer surface of said inner annular portion for cooling said exhaust gas shroud and said ring during operation of the turbine engine.

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Cast in place gas turbine containment ring and method of manufacture

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