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US 2019/0376395 A1Published application
Gas turbine engine airfoil with tip leading edge shelf discourager
AssigneeUnited Technologies Corporation
InventorEmma J. Place
Life of this patent
Estimating the term…
Abstract
An airfoil including a pressure sidewall and a suction sidewall extending from a root section of the airfoil to a tip region of the airfoil and a leading edge and a trailing edge defines a chord length of the airfoil therebetween. A tip shelf is formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall with a tip shelf discourager that extends from the tip shelf.
Claims20
An airfoil for a gas turbine engine, comprising:
- a pressure sidewall and a suction sidewall extending to a tip region of the airfoil;
- a leading edge and a trailing edge defining a chord length of the airfoil therebetween;
- a tip shelf formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall;
- and
- a tip shelf discourager that extends from the tip shelf.
2 more elements
A method of directing a cooling flow from an airfoil for a gas turbine engine, comprising:
- discouraging a tip shelf cooling air from being mixed with core gas path air and pushed over a blade tip region.
An airfoil for a gas turbine engine, comprising:
- a pressure sidewall and a suction sidewall extending to a tip region of the airfoil;
- a leading edge and a trailing edge defining a chord length of the airfoil therebetween;
- a tip shelf formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall;
- a tip shelf discourager that extends from the tip shelf, wherein the tip shelf extends from the leading edge to an intersection of the pressure sidewall and the suction sidewall at the trailing edge such that the tip shelf communicates with both the pressure sidewall and the suction sidewall proximate to the trailing edge, wherein the tip shelf extends around the leading edge and onto the suction sidewall to terminate on the suction sidewall between the leading edge and the trailing edge of the airfoil.
1 more element
Dependencies are inferred from the claim text.