Staggered crossovers for airfoils

Patent metadata

Field	Value
Publication number	US-10145246-B2
Application number	US-201514820786-A
Country	US
Kind code	B2
Filing date	Aug 7, 2015
Priority date	Sep 4, 2014
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane. The passage axis of each of the first set of crossover passages is arranged at a first vertical angle relative to a spanwise axis, and the passage axis of each of the second set of crossover passages is arranged at a second, different vertical angle relative to the spanwise axis. A casting core for an airfoil is also disclosed.

First claim

What is claimed is:

1. An airfoil, comprising:
an airfoil section having an external wall and an internal wall, said internal wall defining a first reference plane extending in a spanwise direction and through a thickness of said internal wall;
a first cavity and a second cavity separated by said internal wall;
a plurality of crossover passages within said internal wall and connecting said first cavity to said second cavity, each of said plurality of crossover passages defining a passage axis, said plurality of crossover passages distributed in said spanwise direction and arranged such that said passage axis of each of said plurality of cooling passages intersects a surface of said second cavity, and said passage axis extending through said first reference plane;
wherein said plurality of crossover passages includes a first set of crossover passages and a second set of crossover passages, said first set of crossover passages including a first set of outlets and said second set of crossover passages including a second set of outlets defined along surfaces of said internal wall defining said second cavity, said first and second sets of outlets positioned on opposite sides of said first reference plane, said passage axis of each of said first set of crossover passages being arranged at a first vertical angle relative to a spanwise axis and said passage axis of each of said second set of crossover passages being arranged at a second, different vertical angle relative to said spanwise axis; and
wherein said internal wall defines a second reference plane perpendicular to said first reference plane, and said first set of crossover passages and said second set of crossover passages are arranged such that a spanwise projection of said passage axis of at least one of said first set of crossover passages onto said second reference plane intersects a spanwise projection of said passage axis of at least one of said second set of crossover passages onto said second reference plane.

2. The airfoil as recited in claim 1 , wherein said passage axis of each of said plurality of crossover passages defines an acute angle relative to said spanwise axis.

3. The airfoil as recited in claim 1 , wherein said first vertical angle extends radially inward relative to said spanwise axis, and said second vertical angle extends radially outward relative to said spanwise axis.

4. The airfoil as recited in claim 3 , wherein said first set of crossover passages and said second set of crossover passages are arranged such that a lateral projection of said passage axis of at least one of said first set of crossover passages onto said first reference plane intersects a lateral projection of said passage axis of at least one of said second set of crossover passages onto said first reference plane.

5. The airfoil as recited in claim 4 , wherein:
said opposite sides include a first side of said first reference plane and a second side of said first reference plane, said first set of crossover passages positioned on said first side, and said second set of crossover passages positioned on said second side; and
wherein said first set of outlets of said first set of crossover passages are offset in said spanwise direction relative to outlets of each and every crossover passage located on said second side.

6. The airfoil as recited in claim 5 , wherein inlets of said first set of crossover passages are offset in said spanwise direction relative to inlets of said each and every crossover passage.

7. The airfoil as recited in claim 6 , wherein said second cavity is bounded by a leading edge of said airfoil section.

8. The airfoil as recited in claim 1 , wherein said first set of crossover passages and said second set of crossover passages are spaced in said spanwise direction between an intermediate set of crossover passages, and a cross-sectional area of each of said intermediate set of crossover passages is different than a cross-sectional area of each of said first set of crossover passages and said second set of crossover passages.

9. The airfoil as recited in claim 8 , wherein said cross-sectional area of said each of said intermediate set of crossover passages is less than said cross-sectional area of said each of said first set of crossover passages and said second set of crossover passages.

10. The airfoil as recited in claim 1 , wherein said first cavity is configured to receive coolant from a second plurality of crossover passages.

11. The airfoil as recited in claim 10 , wherein said second plurality of crossover passages includes a third set of crossover passages and a fourth set of crossover passages arranged such that a spanwise projection of said passage axis of each of said third set of crossover passages onto said second reference plane intersects a spanwise projection of said passage axis of at least one of said fourth set of crossover passages onto said second reference plane.

12. The airfoil as recited in claim 11 , wherein said second cavity is bounded by a trailing edge of said airfoil section.

13. The airfoil as recited in claim 1 , wherein said first cavity is spaced from said external wall.

14. The airfoil as recited in claim 1 , wherein said airfoil section extends from a platform section, said platform section defining at least one of said plurality of crossover passages.

15. The airfoil as recited in claim 1 , wherein at least two of said plurality of crossover passages are aligned in said spanwise direction and are positioned on a common side of said first reference plane.

16. The airfoil as recited in claim 1 , wherein said second cavity is bounded by said external wall.

17. A casting core for an airfoil, comprising:
a first portion corresponding to a first cavity of an airfoil and a second portion corresponding to a second cavity of the airfoil, each of said first portion and said second portion extending in a spanwise direction along a first reference plane;
a plurality of connectors coupling said first portion and said second portion, said plurality of connectors corresponding to a plurality of crossover passages of the airfoil, each of said plurality of connectors defining a first axis, said plurality of connectors being distributed in said spanwise direction, and said first axis extending through said first reference plane;
wherein said plurality of connectors includes a first set of connectors and a second set of connectors, said first set of connectors including a first set of ends and said second set of connectors including a second set of ends defined along said second portion and corresponding to outlets of the plurality of crossover passages, said first and second sets of ends positioned on opposite sides of said first reference plane, said first axis of each of said first set of connectors arranged at a first vertical angle relative to a spanwise axis, and said first axis of each of said second set of connectors arranged at a second, different vertical angle relative to said spanwise axis; and
wherein said first portion and said second portion extend in a chordwise direction along a second reference plane perpendicular to said first reference plane, and said first set of connectors and said second set of connectors are arranged such that a spanwise projection of said first axis of each of said first set of connectors onto said second reference plane intersects a spanwise projection of said first axis of at least one of said second set of connectors onto said second reference plane.

18. A gas turbine engine, comprising:
a rotor carrying an airfoil, and a vane spaced ax

Assignees

• United Technologies Corp

Inventors

• Lewis Scott D
• Girma Yafet
• Corcoran Christopher

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• B22C9/10

  Cores; Manufacture or installation of cores {(breaker cores B22C9/084)} · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title