Airfoil turn caps in gas turbine engines

Patent metadata

Field	Value
Publication number	US-10480329-B2
Application number	US-201715496093-A
Country	US
Kind code	B2
Filing date	Apr 25, 2017
Priority date	Apr 25, 2017
Publication date	Nov 19, 2019
Grant date	Nov 19, 2019

Abstract

Turn caps for airfoils of gas turbine engines having exterior side walls, an exterior top wall extending between the exterior side walls, a first turn cap divider extending from the exterior top wall and positioned between the exterior side walls and defining a first turning feature between the first turn cap divider and the exterior side walls, the first turning feature comprising a first suction-side turn passage and a first pressure-side turn passage wherein the first turn cap divider fluidly separates the first pressure-side turn passage from the first suction-side turn passage within the turn cap, and a merging chamber is formed in the turn cap wherein fluid flows passing through the first suction side turn passage and the first pressure side turn passage are merged at the merging chamber.

First claim

What is claimed is:

1. A vane of a gas turbine engine comprising:
a hollow body having a pressure side and a suction side and the hollow body having a first up-pass cavity and a first down-pass cavity, the hollow body having an inner diameter end and an outer diameter end, the first up-pass cavity including a first pressure side airfoil passage arranged along the pressure side of the hollow body and a first suction side airfoil passage arranged along the suction side of the hollow body, the first up-pass cavity having a flow direction from the inner diameter end toward the outer diameter end and the first down-pass cavity having a flow direction from the outer diameter end toward the inner diameter end, the first down-pass cavity defined between external walls of the pressure side and the suction side of the hollow body;
a first airfoil platform arranged at the outer diameter end of the hollow body, the first airfoil platform having a gas path surface and a non-gas path surface, wherein the hollow body extends from the gas path surface of the first airfoil platform;
a first up-pass cavity opening formed in the non-gas path surface of the first airfoil platform fluidly connected to the first up-pass cavity;
a first down-pass cavity opening formed in the non-gas path surface of the first airfoil platform fluidly connected to the first down-pass cavity; and
a first turn cap fixedly attached to the first airfoil platform on the non-gas path surface covering the first up-pass cavity opening and the first down-pass cavity opening of the first airfoil platform, the first turn cap having:
exterior side walls, the exterior side walls extending between a forward-end of the turn cap and an aft-end of the turn cap;
an exterior top wall extending between the exterior side walls and between the forward-end and the aft-end of the turn cap; and
a first divider located within the first turn cap extending from the exterior top wall and positioned between the exterior side walls and defining a first suction-side turn passage between the exterior side wall and the first divider and a first pressure-side turn passage between the exterior side wall and the first divider, wherein the first divider fluidly separates the first pressure-side turn passage from the first suction-side turn passage within the first turn cap, wherein the first divider extends from the forward-end of the turn cap toward the aft-end of the turn cap and separates the first pressure-side turn passage and the first suction-side turn passage,
wherein a merging chamber is formed in the turn cap proximate the aft-end of the turn cap,
wherein, in operation, a fluid flow passes radially through the first pressure side airfoil passage of the first up-pass cavity into the first pressure-side turn passage proximate the forward-end of the turn cap and fluid flows radially through the first suction side airfoil passage of the first up-pass cavity into the first suction-side turn passage proximate the forward-end of the turn cap,
wherein, in operation, the fluid flow flows axially once entering the respective first pressure-side turn passage and first suction-side turn passage toward the aft-end of the turn cap,
wherein, in operation, the fluid flow passing-flows axially through the first suction side turn passage and the first pressure side turn passage and are merged at the merging chamber in an axial direction proximate the aft-end of the turn cap, and
wherein, in operation, the fluid flow is turned from an axial flow to a radial flow within the merging chamber and directed radially into the first down-pass cavity of the hollow body.

2. The vane of claim 1 , further comprising:
a second up-pass cavity within the hollow body having a second pressure-side airfoil passage and a second suction-side airfoil passage and a second up-pass cavity opening is formed in the non-gas path surface of the first airfoil platform, wherein the second up-pass cavity is arranged between the first up-pass cavity and the first down-pass cavity,
a second divider within the first turn cap and extending from the exterior top wall and positioned between the exterior side walls and the first divider and defining a second suction side turn passage fluidly connected with the second suction-side airfoil passage and a second pressure side turn passage fluidly connected with the second pressure-side airfoil passage, wherein fluid flows through the second suction side turn passage and the second pressure side turn passage are fluidly separated from each other and the fluid flows through the second pressure side turn passage and the second suction side turn passage and are merged at the merging chamber.

3. The vane of claim 1 , wherein the first pressure-side turn passage and the first suction-side turn passage are each fluidly connected to a respective one of the radially extending up-pass cavities, wherein each radially extending up-pass cavity has a low aspect ratio, and wherein the first pressure-side turn passage and first suction-side turn passage each define axially extending turn passages having the same aspect ratios as the respective one of the radially extending up-pass cavities.

4. The vane of claim 1 , wherein the hollow body further includes a second up-pass cavity having a second pressure side airfoil passage and a second suction side airfoil passage, wherein the second up-pass cavity is arranged between the first up-pass cavity and the first down-pass cavity within the hollow body, a second up-pass cavity opening is formed in the non-gas path surface of the first airfoil platform, and the first turn cap comprises:
a second pressure-side turn passage fluidly connecting the second pressure side airfoil passage to the merging chamber when the turn cap is attached to the first airfoil platform; and
a second suction-side turn passage fluidly connecting the first suction side airfoil passage to the merging chamber when the turn cap is attached to the first airfoil platform,
wherein each of the second suction-side turn passage and the second pressure-side turn passage are configured, during operation, to turn a direction of fluid flow from a radial direction to an axial direction such that a fluid flow exiting the second suction-side turn passage and the second pressure-side turn passage are aligned in an axial direction when entering the merging chamber.

5. The vane of claim 1 , wherein the hollow body, the first airfoil platform, and the first turn cap are integrally formed.

6. The vane of claim 1 , wherein the first up-pass cavity defines a first geometry within the hollow body such that an airfoil external wall of the hollow body is uniform in thickness at a first radial position and a second geometry within the hollow body such that the airfoil external wall of the hollow body is non-uniform in thickness at a second radial position.

7. The vane of claim 6 , wherein the second radial position is proximate the first airfoil platform.

8. The vane of claim 1 , further comprising a baffle positioned in the first up-pass cavity, the baffle defining the first pressure side airfoil passage along the pressure side of the hollow body and the first suction side airfoil passage along the suction side of the hollow body between the baffle and respective airfoil external walls.

9. The vane of claim 1 , wherein the first pressure-side turn passage and the first suction-side turn passage are angled inward from the exterior side walls toward each other within the turn cap in a direction from the forward-end of the turn cap toward the aft-end of the turn cap.

10. The vane of claim 9 , wherein the turn cap further comprises a second pressure-side turn passage and a second suction-side turn passage, wherein a s

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W
• Mongillo Dominic J

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title