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US 7,815,417 B2Granted
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 guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning a flow of working fluid and an internal spar spaced from the aerodynamic shell by an air gap and reinforced by stiffeners.
Claims5
A guide vane for a gas turbine engine, said guide vane comprising:
- an aerodynamic outer shell;
- a mechanical load carrying spar disposed within said outer shell and separated therefrom by a gap therebetween;
- a plurality of stiffeners mounted on said spar;
- at least a portion of each stiffener including a longitudinal thermal fin for dissipating heat from said outer shell to said gap and said spar;
- and
- at least one of said longitudinal thermal fins extending partially into said gap;
- wherein said stiffeners are generally T-shaped in cross-section, each comprising a base mounted on said structural spar and said longitudinal thermal fin extending outwardly from said base toward said aerodynamic outer shell.
4 more elements
A guide vane for a gas turbine engine, said guide vane comprising:
- an aerodynamic outer shell;
- a mechanical load carrying spar disposed within said outer shell and separated therefrom by a gap therebetween;
- a plurality of stiffeners mounted on said spar;
- at least a portion of each stiffener including a longitudinal thermal fin for dissipating heat from said outer shell to said gap and said spar;
- and
- at least one of said longitudinal thermal fins extending partially into said gap;
- wherein said spar is solid.
4 more elements
Dependencies are inferred from the claim text.