Aircraft engine having a scroll case with integrated vanes
AssigneePratt & Whitney Canada Corp.
InventorsGuy LEFEBVRE, Remy SYNNOTT
Life of this patent
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Abstract
An aircraft engine including a scroll case extending around a central axis and having an inlet fluidly connected to a source of combustion gases and an outlet, and a conduit extending around the central axis from the inlet to the outlet. The conduit includes an outer wall and a radially inward inner wall, the outlet defined radially between the inner wall and the outer wall. A turbine is downstream of the outlet of the scroll case relative to a flow of the combustion gases. Vanes are circumferentially distributed around the central axis, the vanes being removably mounted to the scroll case proximate to the outlet of the conduit and radially between the inner wall and the outer wall.
Claims22
An aircraft engine, comprising:
- a scroll case extending around a central axis and having an inlet fluidly connected to a source of combustion gases and an outlet, a conduit extending around the central axis from the inlet to the outlet, the conduit including an outer wall and an inner wall located radially inwardly of the outer wall relative to the central axis, the outlet defined radially between the inner wall and the outer wall;
- a turbine downstream of the outlet of the scroll case relative to a flow of the combustion gases;
- and
- vanes circumferentially distributed around the central axis, the vanes removably mounted to the scroll case proximate to the outlet of the conduit and radially between the inner wall and the outer wall, the vanes located upstream of the outlet of the scroll case relative to the flow of the combustion gases, a vane of the vanes has an inner shroud and an outer shroud, the inner shroud being removably mounted to the inner wall of the conduit via an inner shroud mounting interface, and the outer shroud being removably mounted to the outer wall of the conduit via an outer shroud mounting interface.
(canceled)
A turbine assembly, comprising:
- a scroll case extending around a central axis and having an inlet fluidly connected to a source of combustion gases and an outlet, and a conduit extending around the central axis from the inlet to the outlet, the conduit having an inner wall and an outer wall disposed radially outwardly of the inner wall relative to the central axis;
- a turbine downstream of the outlet of the scroll case relative to a flow of the combustion gases;
- and
- vanes circumferentially distributed around the central axis and axially overlapping the conduit, the vanes removably mounted within the conduit of the scroll case, the vanes located upstream of the outlet of the scroll case relative to the flow of the combustion gases, a vane of the vanes having an inner shroud removably mounted to the inner wall via an inner shroud mounting interface and an outer shroud removably mounted to the outer wall via an outer shroud mounting interface.
(canceled)
The turbine assembly of claim , comprising a locking member secured to the inner wall, axial movements of the vanes towards the turbine blocked by the locking member.
An aircraft engine, comprising:
- an internal combustion engine having an exhaust for outputting combustion gases;
- a scroll case extending around a central axis and having an inlet fluidly connected to the exhaust of the internal combustion engine and an outlet, and a conduit extending around the central axis from the inlet to the outlet, the conduit having a non-axisymmetric portion converging towards the central axis;
- a turbine downstream of the outlet of the scroll case relative to a flow of the combustion gases;
- and
- vanes circumferentially distributed around the central axis and axially overlapping the conduit, the vanes removably mounted within the conduit of the scroll case, the vanes located upstream of the outlet of the scroll case relative to the flow of the combustion gases.
Dependencies are inferred from the claim text.