초록 ▼

A toroidally shaped double-walled gas-cooled inlet manifold for a radial in-flow turbine has a plurality of can-type combustors mounted on one axially facing side of the torous, arrays of coolant gas inlet holes in the outer wall located midway between the individual combustors, coolant gas inlet sl

A toroidally shaped double-walled gas-cooled inlet manifold for a radial in-flow turbine has a plurality of can-type combustors mounted on one axially facing side of the torous, arrays of coolant gas inlet holes in the outer wall located midway between the individual combustors, coolant gas inlet slots distributed circumferentially along the torous on the axial face mounting the combustors, and coolant gas inlet impingement orifices proximate the annular manifold exit duct on both axial facing sides of the outer wall. Annular coolant gas exit ports are provided surrounding the circular combustion gas inlet ducts from the individual combustors to induce a blanketing flow of coolant gas over the entire inner wall.

대표청구항 ▼

A gas-cooled inlet manifold for a radial in-flow turbine, the manifold receiving combustion gases from at least one can-type combustor, the manifold comprising: a first wall in the shape of a hollow torus having an axis, the interior space within said first toroidal wall defining in part the flow pa

A gas-cooled inlet manifold for a radial in-flow turbine, the manifold receiving combustion gases from at least one can-type combustor, the manifold comprising: a first wall in the shape of a hollow torus having an axis, the interior space within said first toroidal wall defining in part the flow path for combustion gas from the combustor to the turbine; a second wall in the shape of a hollow torus and surrounding said first wall, the space between said first and second walls defining in part the flow path of the coolant gas; an annular duct positioned at the inner circle of said first and second toroidal wall and being in flow communication with said interior space, and passing through said second wall, for delivering combustion gases to the turbine, said annular duct being essentially sealed against flow communication with said coolant gas space; a duct positioned in an axial side of said first toroidal wall for receiving combustion gases from the combustor, said duct also passing through said second wall and being in flow communication with said interior space; coolant gas inlet means including (i) a plurality of first coolant gas entry ports, said first ports being positioned in said second wall in an array spaced circumferentially from said combustion gas inlet duct and distributed about the circumference of the generating circle of said second toroidal wall, (ii) a plurality of second coolant gas entry ports, said second ports being elongated slot-shaped and positioned in an axial side of said second wall, said second ports being distributed circumferentially around said second toroidal wall proximate said annular duct with the respective axes of elongation extending circumferentially and (iii) a plurality of orifice means positioned in said second wall proximate said annular duct and evenly distributed circumferentially around said second wall on both axial second wall sides of said annular duct, each of said orifice means for directing a stream of coolant gas to impinge upon a preselected portion of said first wall.