Variable stator vanes with anti-lock trunnions
AssigneeGeneral Electric Company
InventorsRavindra Shankar Ganiger, Kevin Lee Kirkeng, Vishnu Das K, Reddi Hari Prasad Reddy Mylapalli
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Abstract
Variable stator vanes with anti-lock trunnions are disclosed. An example apparatus disclosed herein includes an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis, an outer trunnion, and an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine.
Claims20
An apparatus comprising:
- an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis;
- an outer trunnion;
- and
- an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine via an opening of a trunnion ring, the trunnion ring including a first component and a second component coupled together via a fastener to form the opening.
An apparatus to be coupled within a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis, the apparatus comprising:
- an inner shroud segment;
- an outer shroud segment;
- a plurality of variable stator vanes (VSVs) extending between the inner shroud segment and the outer shroud segment, a first VSV of the plurality of VSVs including:
- an airfoil;
- an outer trunnion mounted within the outer shroud segment;
- and
- an inner trunnion mounted within the inner shroud segment, the inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to the inner shroud segment via an opening of a trunnion ring, the trunnion ring including a first component and a second component coupled together via a fastener to form the opening.
A gas turbine engine defining an axial axis, a radial axis and a circumferential axis, the gas turbine engine including:
- an inner shroud including a trunnion ring, the trunnion ring including a first component and a second component coupled together via a fastener to form an opening;
- an airfoil to be disposed within a flow path of the gas turbine engine;
- an outer trunnion disposed at a top edge of the airfoil;
- and
- an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to the inner shroud via the opening of the trunnion ring.
Dependencies are inferred from the claim text.