Low pressure loss, convectively gas-cooled inlet manifold for hi

Details Low pressure loss, convectively gas-cooled inlet manifold for hi Low pressure loss, convectively gas-cooled inlet manifold for hi

1984-05-15

1986-03-04

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Plural combustion products generators in ring coaxial with...

60752, F02C 300

Patent

active

045733155

ABSTRACT:
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.

REFERENCES:
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R. J. Mowill et al., "New Radial Engine Technology From Kongsberg" ASME 83-GT-221, paper del. Mar. 1983.

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