Variable geometry guide vane for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsNagendra Somanath, Keshava B. Kumar
Life of this patent
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Abstract
A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.
Claims18
A guide vane for a gas turbine engine said guide vane comprising:
- an aerodynamic outer shell, adjustable in shape
- a mechanical load bearing structural spar received within said aerodynamic outer shell and spaced therefrom by an interior gap and
- at least one actuation mechanism disposed within said gap and connected to a portion of said outer shell and structural spar such that when activated, said actuation mechanism displaces said portion of said outer shell with respect to said spar thereby selectively adjusting the shape of said outer shell.
A gas turbine engine comprising:
- high pressure turbine driven by a first shaft;
- a low pressure turbine driven by a second shaft,
- a working medium fluid flowing between said high and low pressure turbines through a gas path,
- said first and second shafts being mounted on a frame intermediate said low and high pressure turbines,
- the mechanical load of said frame being transmitted at least in part to an engine mount by a mechanical load bearing guide vane;
- said guide vane including an outer aerodynamic shell, the outer shape of said guide vane being adjustable to accommodate varying operating parameters of said engine, to counteract thermal distortion thereof and to effect aerodynamic load balancing.
Dependencies are inferred from the claim text.