Lightweight annular interturbine duct
AssigneePratt & Whitney Canada Corp.
InventorsEric Durocher, John Walter Pietrobon
Life of this patent
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Abstract
An interturbine duct for channelling combustion gases between two axial turbine stages. The interturbine duct is made of sheet material to provide a relatively lightweight construction.
Claims16
A gas turbine interturbine duct comprising a pair of annular spaced-apart sheet metal inner and outer walls extending from a first upstream axial turbine stage to a second downstream axial turbine stage of the engine, and holes defined in a transition area between the inner wall and a baffle adjacent the first turbine stage, the holes adapted to receive secondary cooling air and direct it around an exterior portion of the inner wall.
A gas turbine interturbine duct comprising a pair of annular spaced-apart sheet metal walls extending from a first upstream axial turbine stage to a second downstream axial turbine stage of the engine, wherein an outer one of the annular walls is mounted at a downstream end to a vane stator of the second turbine stage and cantilevered at an upstream end, the downstream end having a radially inwardly facing surface brazed to a radially outwardly facing surface of the vane stator.
A gas turbine interturbine duct comprising a pair of annular spaced-apart sheet metal walls extending from a first upstream axial turbine stage to a second downstream axial turbine stage of the engine, wherein at least one of the annular walls includes an axially-oriented cylindrical flange portion adapted for mounting thereto a vane platform of the second turbine stage, the axially-oriented cylindrical flange portion having a radially facing mounting surface axially overlapping and brazed to a corresponding radially facing surface of the vane platform of the second turbine stage.
A gas turbine interturbine duct comprising a pair of annular spaced-apart sheet metal walls extending from a first upstream axial turbine stage to a second downstream axial turbine stage of the engine, wherein an upstream end of an outer one of the annular walls is bent to provide a radially outwardly extending lip adapted for placement adjacent but unmounted to the first turbine stage, and wherein the outer wall is provided at a downstream end thereof with a radially surface mounted in axially overlapping relation to a vane platform of the second downstream turbine stage.
Dependencies are inferred from the claim text.