Turbine engine with shroud cooling means

Details Turbine engine with shroud cooling means Turbine engine with shroud cooling means

1980-07-30

1982-11-16

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Cooling of auxiliary components

415115, F02C 712

Patent

active

043589260

ABSTRACT:
A turbine engine construction is provided with novel shroud cooling means. The turbine engine includes a compressor having its outlet open to a combustion chamber into which fuel is also introduced. The hot expanding gases resulting from the combustion of the fuel within the combustion chamber exhaust through a plurality of circumferentially spaced and relatively stationary stator vanes and through one or more turbine stages to rotatably drive the same. A portion of the outlet gases from the compressor, however, are diverted from the combustion chamber and impinge upon an annular shroud secured to the support housing around each turbine stage in order to cool the shroud and minimize its thermal expansion. From the shroud, the cooling air flow passes through a fluid passageway formed through one or more stator vanes and is returned to the combustion chamber.

REFERENCES:
patent: 2625013 (1953-01-01), Howard et al.
patent: 2787440 (1957-04-01), Thompson
patent: 3575528 (1971-04-01), Beam
patent: 3903691 (1975-09-01), Szydlowski
patent: 4017207 (1977-04-01), Bell et al.

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