초록 ▼

An axial flow gas turbine is provided with a shroud ring which is defined by two axially adjacent heat pipes. The radially inner face of the shroud ring has a plurality of axially extending cooling air passages located adjacent to it. Cooling air, which in operation is directed through the passages

An axial flow gas turbine is provided with a shroud ring which is defined by two axially adjacent heat pipes. The radially inner face of the shroud ring has a plurality of axially extending cooling air passages located adjacent to it. Cooling air, which in operation is directed through the passages serves to provide cooling of the shroud ring and the substantial elimination of any radial heat flux in the shroud ring.

대표청구항 ▼

An axial flow gas turbine comprising: structure defining an annular gas passage extending therethrough, an annular array of radially extending rotary aerofoil blades located such that said rotary aerofoil blades extend radially across said annular gas passage; a shroud ring having a radially inwardl

An axial flow gas turbine comprising: structure defining an annular gas passage extending therethrough, an annular array of radially extending rotary aerofoil blades located such that said rotary aerofoil blades extend radially across said annular gas passage; a shroud ring having a radially inwardly facing circumferential face which surrounds said annular array of aerofoil blades in radially spaced apart relationship and constituting an axial portion of the radially outer extent of said annular gas passage, said shroud ring being defined by at least one heat pipe proximate the outer ends of said rotary aerofoil blades and having a plurality of passages extending therethrough which are located adjacent said radially inwardly facing circumferential face and being adapted for the passage of cooling fluid therethrough; means for directing cooling fluid into said passages at such a rate that any heat flux through said shroud ring in a radially outward direction is substantially eliminated; means cooperating with said shroud ring for defining an annular chamber located generally radially outwardly of said shroud ring and adjacent said at least one heat pipe, said annular chamber being adapted to receive a supply of said cooling fluid; and duct means adjacent said at least one heat pipe for interconnecting said annular chamber with said passages adjacent said radially inwardly facing circumferential face of said shroud ring to direct said cooling fluid from said annular passage into said passages, said cooling fluid being subsequently exhausted from said passages.