Aircraft engine, gas turbine intake therefore, and method of guiding exhaust gasses
AssigneePratt & Whitney Canada Corp.
InventorsGuy LEFEBVRE, Christopher GOVER, Remy SYNNOTT
Life of this patent
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Abstract
The gas turbine intake can have a swirl housing having an inlet portion fluidly connecting an exhaust conduit, an annular outlet defined around a central axis and fluidly connecting a turbine gas path, a swirl path extending circumferentially around the central axis from the inlet portion to a circumferential outlet, the circumferential outlet fluidly connected back into the inlet portion, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis and located radially inwardly from the swirl path relative the central axis, the swirl path being free of the vanes.
Claims20
An aircraft engine comprising:
- an exhaust conduit;
- at least one combustion engine having an exhaust gas outlet fluidly connected to the exhaust conduit;
- at least one gas turbine having a casing defining a radially outer limit of an annular gas path extending along and around a central axis, and at least one rotor having a shaft concentric to the central axis, a plurality of blades circumferentially interspaced from one another around the central axis and protruding radially from the shaft across the annular gas path;
- and
- a gas turbine intake having a swirl housing having an inlet portion fluidly connecting the exhaust conduit, an annular outlet fluidly connecting the annular gas path, a swirl path extending circumferentially around the central axis from the inlet portion to a circumferential outlet, the circumferential outlet fluidly connected back into the inlet portion, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis and located radially inwardly from the swirl path relative the central axis, the swirl path being free of the vanes.
A gas turbine intake comprising :
- a swirl housing having an inlet portion fluidly connecting an exhaust conduit, an annular outlet defined around a central axis and fluidly connecting a turbine gas path, a swirl path extending circumferentially around the central axis from the inlet portion to a circumferential outlet, the circumferential outlet fluidly connected back into the inlet portion, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis and located radially inwardly from the swirl path relative the central axis, the swirl path being free of the vanes.
A method of guiding exhaust gasses to a gas turbine, the method comprising tangentially receiving the exhaust gasses at a circularly extending swirl path, recirculating a portion of the received exhaust gasses around the swirl path, manifolding the swirl path into a plurality of circumferentially distributed guide paths, each guide path scooping the exhaust gasses at a corresponding portion of the swirl path and redirecting a circumferential velocity of the exhaust gasses to an axial orientation, the guide paths collectively outputting an annular, axially oriented, flow of exhaust gasses.
Dependencies are inferred from the claim text.