Airfoil having internal hybrid cooling cavities

Patent metadata

Field	Value
Publication number	US-10626734-B2
Application number	US-201715723473-A
Country	US
Kind code	B2
Filing date	Oct 3, 2017
Priority date	Oct 3, 2017
Publication date	Apr 21, 2020
Grant date	Apr 21, 2020

Abstract

Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, the airfoil comprising:
an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending in an axial direction between a leading edge and a trailing edge;
a first core cavity within the airfoil body, the first core cavity being one of the plurality of cavities formed in the airfoil body;
a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall opposing the first cavity wall, a first exterior wall, and a second exterior wall opposing the first exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body, the second core cavity being another of the plurality of cavities formed in the airfoil body;
wherein the first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall;
at least one first cavity impingement hole formed within the first surface, wherein a first impingement flow flows from the first core cavity through the at least one first cavity impingement hole and impinges upon the first exterior wall to form a first high momentum jet of impingement air thereon;
at least one second cavity impingement hole formed within the second surface, wherein a second impingement flow flows from the first core cavity through the at least one second cavity impingement hole and impinges upon the second exterior wall to form a second high momentum jet thereon; and
a forward central ridge extending into the second core cavity from the first cavity wall,
an aft central ridge extending into the second core cavity from the second cavity wall,
wherein the forward central ridge and the aft central ridge at least partially divide the second core cavity into a two-vortex chamber.

2. The airfoil of claim 1 , wherein the first impingement flow separates into the first high momentum jet flowing along the first exterior wall and a first portion of a radial cooling flow within the second core cavity and the second impingement flow separates into the second high momentum jet flowing along the second exterior wall and a second portion of the radial cooling flow within the second core cavity, wherein the first and second portions of the radial cooling flow flow radially within the two-vortex chamber.

3. The airfoil of claim 1 , further comprising at least one circuit exit in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall.

4. The airfoil of claim 3 , further comprising a funneling feature extending from the second core cavity along the first exterior wall to the at least one circuit exit.

5. The airfoil of claim 3 , further comprising at least one heat transfer augmentation feature within the at least one circuit exit.

6. The airfoil of claim 1 , further comprising at least one film exit in the first exterior wall, the at least one film exit arranged to expel air from the second core cavity through the first exterior wall.

7. The airfoil of claim 6 , further comprising a funneling feature extending from the second core cavity along the first exterior wall to the at least one film exit.

8. The airfoil of claim 1 , wherein the at least one first cavity impingement hole has one of a radial orientation in the radial direction, an axial orientation in the axial direction, or an angular orientation relative to at least one of the radial direction and the axial direction within the first cavity wall.

9. A gas turbine engine comprising:
an airfoil having an airfoil body having a plurality of cavities formed therein, the airfoil extending in a radial direction between a first end and a second end, and extending axially between a leading edge and a trailing edge;
a first core cavity within the airfoil body, the first core cavity being one of the plurality of cavities formed in the airfoil body;
a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall opposing the first cavity wall, a first exterior wall, and a second exterior wall opposing the first exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body, the second core cavity being another of the plurality of cavities formed in the airfoil body;
wherein the first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall;
at least one first cavity impingement hole formed within the first surface, wherein a first impingement flow flows from the first core cavity through the at least one first cavity impingement hole and impinges upon the first exterior wall to form a first high momentum jet of impingement air thereon;
at least one second cavity impingement hole formed within the second surface, wherein a second impingement flow flows from the first core cavity through the at least one second cavity impingement hole and impinges upon the second exterior wall to form a second high momentum jet thereon; and
a forward central ridge extending into the second core cavity from the first cavity wall,
an after central ridge extending into the second core cavity from the second cavity wall,
wherein the forward central ridge and the aft central ridge at least partially divide the second core cavity into a two-vortex chamber.

10. The gas turbine engine of claim 9 , wherein the first impingement flow separates into the first high momentum jet flowing along the first exterior wall and a first portion of a radial cooling flow within the second core cavity and the second impingement flow separates into the second high momentum jet flowing along the second exterior wall and a second portion of the radial cooling flow within the second core cavity, wherein the first and second portions of the radial cooling flow flow radially within the two-vortex chamber.

11. The gas turbine engine of claim 9 , further comprising at least one circuit exit in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall.

12. The gas turbine engine of claim 11 , further comprising a funneling feature extending from the second core cavity along the first exterior wall to the at least one circuit exit.

13. The gas turbine engine of claim 11 , further comprising at least one heat transfer augmentation feature within the at least one circuit exit.

14. The gas turbine engine of claim 9 , further comprising at least one film exit in the first exterior wall, the at least one film exit arranged to expel air from the second core cavity through the first exterior wall.

15. The gas turbine engine of claim 14 , further comprising a funneling feature extending from the second core cavity along the first exterior wall to the at least one film exit.

16. The gas turbine engine of claim 9 , wherein the at least one first cavity impingement hole has one of a radial orientation in the radial direction, an axial orientation in an axial direction, or an angular orientation relative to at least one of the radial direction and the axial direction within the first cavity wall.

Assignees

• United Technologies Corp

Inventors

• Propheter-Hinckley Tracy A
• Clum Carey
• Jennings Timothy J

Classifications

• B22C9/10

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

• F05D2260/221

  Improvement of heat transfer · CPC title

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title