Turbine vane for gas turbine engine
AssigneeRolls-Royce North American Technologies Inc.
InventorsRichard C. Uskert, Ted Joseph Freeman, David J. Thomas
Life of this patent
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Abstract
The present invention provides a turbine vane for a gas turbine engine. The turbine vane may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.
Claims25
A turbine vane for a gas turbine engine, comprising:
- a ceramic-matrix composite (CMC) airfoil structure having an opening extending in a spanwise direction therethrough;
- a metallic spar having a body disposed within said opening and defining a gap between said body and an internal surface of said CMC airfoil structure defined by said opening;
- a standoff disposed within said gap;
- and
- wherein said CMC airfoil structure releasably is disposed on said metallic spar.
A turbine vane for a gas turbine engine, comprising:
- a composite airfoil structure having an opening extending in a spanwise direction at least partially therethrough;
- a spar having a body disposed within said opening and defining a gap between said body and an internal surface of said composite airfoil structure defined by said opening;
- and
- means for spacing said body apart from an internal surface of said composite airfoil structure.
An airfoil, comprising:
- a composite airfoil structure having an opening extending at least partially therethrough in a spanwise direction and structured to releasably receive a body of a spar and to receive means for spacing said body apart from an internal surface of said composite airfoil structure defined by said opening.
A gas turbine engine comprising:
- a plurality of turbine vanes, each turbine vane of said plurality of turbine vanes including:
- a ceramic-matrix composite (CMC) airfoil structure having an opening extending in a spanwise direction therethrough;
- a metallic spar having a body disposed within said opening and defining a gap between said body and an internal surface of said CMC airfoil structure defined by said opening;
- and
- a standoff disposed within said opening,
- wherein said CMC airfoil structure is releasably disposed on said metallic spar.
Dependencies are inferred from the claim text.