Gas turbine engine airfoil with wishbone baffle cooling scheme

Patent metadata

Field	Value
Publication number	US-10487668-B2
Application number	US-201414915513-A
Country	US
Kind code	B2
Filing date	Aug 27, 2014
Priority date	Sep 6, 2013
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

First claim

What is claimed is:

1. A gas turbine engine component comprising:
a structure including spaced apart first and second exterior walls extending in a radial direction to an endwall, the first and second exterior walls are joined at the endwall to provide a cooling cavity, the first and second exterior walls are respectively pressure and suction side walls joined at leading and trailing edges spaced from one another in a chord-wise direction; and
a wishbone baffle arranged in the cooling cavity and including first and second interior walls respectively adjacent to the first and second exterior walls, the first and second interior walls extending in the radial direction and joined by an apex to provide a first cavity, the wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall, first and second passageways respectively arranged between the first interior and exterior walls and the second interior and exterior walls, the first and second passageways generally having a uniform width in a thickness direction; and
wherein the first and second exterior walls are not parallel to one another and provide first and second portions respectively at first and second span positions that are different than one another, the first portion has a first portion width in the thickness direction at a chord-wise location along the chord-wise direction, the second portion has a second portion width in the thickness direction at the chord-wise location, the second portion width is at least twice the first portion width.

2. The gas turbine engine component according to claim 1 , comprising first and second ribs spaced laterally from one another in the chord-wise direction, the wishbone baffle is supported within the cooling cavity by the first and second ribs.

3. The gas turbine engine component according to claim 2 , wherein the first and second ribs extend through the first and second cavities.

4. The gas turbine engine component according to claim 2 , wherein the wishbone baffle includes a recess provided in the first and second interior walls opposite the apex and laterally between the first and second ribs.

5. The gas turbine engine component according to claim 2 , wherein the wishbone baffle includes a peak provided in the first and second interior walls opposite the apex, and a third rib is secured to the peak and arranged laterally between the first and second ribs.

6. The gas turbine engine component according to claim 1 , wherein the apex is provided by a generally flat wall.

7. The gas turbine engine component according to claim 6 , wherein at least one aperture is provided in the apex.

8. The gas turbine engine component according to claim 1 , wherein the component is one of a vane or a blade that includes an airfoil that provides the structure.

9. The gas turbine engine component according to claim 8 , comprising first and second ribs arranged in the first and second cavities and supporting the wishbone baffle, the first and second ribs are spaced laterally between and spaced from the leading and trailing edges.

10. The gas turbine engine component according to claim 9 , wherein the component includes a platform and a tip spaced apart from one another, the first and second exterior walls extend from the platform to the tip, and the wishbone baffle and the second portion is arranged near the platform, and the first portion is arranged closer to the tip than the second portion.

11. The gas turbine engine component according to claim 10 , wherein the wishbone baffle is not arranged near the tip.

12. The gas turbine engine component according to claim 10 , wherein the wishbone baffle is arranged substantially within 0-50 percent span of the airfoil.

13. A method of manufacturing a gas turbine engine component, comprising the steps of:
surrounding a sacrificial wishbone core with ceramic; and
performing one of melting the sacrificial wishbone core after forming the ceramic core or consuming the wishbone core with molten metal to produce a structure including spaced apart first and second exterior walls extending in a radial direction to an endwall, the first and second exterior walls are joined at the endwall to provide a cooling cavity corresponding to the ceramic, the first and second exterior walls are respectively pressure and suction side walls joined at leading and trailing edges spaced from one another in a chord-wise direction, the wishbone core providing a wishbone baffle arranged in the cooling cavity and including first and second interior walls respectively adjacent to the first and second exterior walls, the first and second interior walls extending in the radial direction and joined by an apex to provide a first cavity, the wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall;
wherein the cooling cavity includes first and second passageways respectively arranged between the first interior and exterior walls and the second interior and exterior walls, the first and second passageways generally having a uniform width in a thickness direction, and the first and second exterior walls are not parallel to one another and provide first and second portions respectively at first and second span positions that are different than one another, the first portion has a first portion width in the thickness direction at a chord-wise location along the chord-wise direction, the second portion has a second portion width in the thickness direction at the chord-wise location, the second portion width is at least twice the first portion width.

14. The method according to claim 13 , comprising first and second ribs spaced laterally from one another in a chord-wise direction, the wishbone baffle is supported within the cooling cavity by the first and second ribs.

15. The method according to claim 13 , wherein the component is one of a vane or a blade that includes an airfoil that provides the structure.

16. The method according to claim 15 , wherein the component includes a platform and a tip spaced apart from one another, the first and second exterior walls extend from the platform to the tip, and the wishbone baffle is arranged near the platform, and the wishbone baffle is arranged substantially within 0-50 percent span of the airfoil.

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W
• Otero Edwin

Classifications

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• B22C9/103

  Multipart cores · CPC title

• B22C9/046

  Use of patterns which are eliminated by the liquid metal in the mould · CPC title

• B22C9/04

  Use of lost patterns · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title