Gas turbine blade with pedestal array

Patent metadata

Field	Value
Publication number	US-10570749-B2
Application number	US-201615004498-A
Country	US
Kind code	B2
Filing date	Jan 22, 2016
Priority date	Jan 22, 2016
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.

First claim

What is claimed is:

1. A component for a gas turbine engine, the component comprising:
a platform;
an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge;
an internal cooling cavity located within the airfoil;
an array of pedestals located adjacent to the platform, the array of pedestals comprising a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals directly adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the entire first row of pedestals are further from the trailing edge than the second row of pedestals and the second row of pedestals are closer to the trailing edge than any other pedestals of the array of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals, wherein the lowermost pedestal of the second row of pedestals is closer to the platform than any other pedestal of airfoil; and
a plurality of cooling openings located between the trailing edge and the second row of pedestals, the plurality of cooling openings being in fluid communication with the internal cooling cavity.

2. The component as in claim 1 , wherein a surface of the pedestals facing the platform is configured to have a flat surface extending between the opposite sides of the internal cavity.

3. The component as in claim 1 , wherein a surface of the pedestals facing the platform is configured to have a curved surface extending between the opposite sides of the internal cavity.

4. The component as in claim 1 , wherein the first row of pedestals are aligned with each other and the array of pedestals only comprises the first row of pedestals and the second row of pedestals.

5. The component as in claim 4 , wherein the second row of pedestals are aligned with each other and parallel to the first row of pedestals.

6. The component as in claim 1 , wherein a surface of the pedestals facing the platform is configured to have either a flat surface extending between the opposite sides of the internal cavity or a curved surface extending between the opposite sides of the internal cavity.

7. The component as in claim 1 , further comprising a third row of pedestals directly adjacent to the first row of pedestals, wherein the third row of pedestals are further from the trailing edge than the first row of pedestals and the lowermost pedestal of the third row of pedestals is further from the platform than a lowermost pedestal of the first row of pedestals.

8. The component as in claim 1 , wherein the component is a rotor blade of a gas turbine engine.

9. The component as in claim 8 , wherein the blade has a plurality of cooling openings in the exterior surface of the blade proximate to the trailing edge, wherein the plurality of cooling openings are in fluid communication with the internal cooling cavity.

10. A blade for a gas turbine engine, the blade comprising:
an airfoil;
a platform secured to the airfoil, the airfoil having an exterior surface extending from a leading edge to a trailing edge;
an internal cooling cavity located within the airfoil; and
an array of pedestals located adjacent to the platform and extending between opposite sides of the internal cavity, the array of pedestals including a first row of pedestals and a second row of pedestals directly adjacent to the first row of pedestals, wherein the entire first row of pedestals are further from the trailing edge than the second row of pedestals and the second row of pedestals are closer to the trailing edge than any other pedestals of the array of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals, wherein the lowermost pedestal of the second row of pedestals is closer to the platform than any other pedestal of the airfoil; and
a plurality of cooling openings located between the trailing edge and the second row of pedestals, the plurality of cooling openings being in fluid communication with the internal cooling cavity.

11. The blade as in claim 10 , wherein a surface of the pedestals facing the platform is configured to have a flat surface extending between the opposite sides of the internal cavity.

12. The blade as in claim 10 , wherein a surface of the pedestals facing the platform is configured to have a curved surface extending between the opposite sides of the internal cavity.

13. The blade as in claim 10 , wherein the first row of pedestals are aligned with each other and the array of pedestals only comprises the first row of pedestals and the second row of pedestals.

14. The blade as in claim 10 , wherein the second row of pedestals are aligned with each other and parallel to the first row of pedestals.

15. The blade as in claim 10 , a surface of the pedestals facing the platform is configured to have either a flat surface extending between the opposite sides of the internal cavity or a curved surface extending between the opposite sides of the internal cavity.

16. The blade as in claim 10 , wherein the array of pedestals further comprises a third row of pedestals directly adjacent to the first row of pedestals, wherein the third row of pedestals are farther from the trailing edge than the first row of pedestals and the lowermost pedestal of the third row of pedestals is further from the platform than a lowermost pedestal of the first row of pedestals.

17. The blade as in claim 10 , wherein the blade has a plurality of cooling openings in the exterior surface of the blade proximate to the trailing edge, wherein the plurality of cooling openings are in fluid communication with the internal cooling cavity.

18. A method of forming a cooling path in a blade of a gas turbine engine, the method comprising:
fluidly coupling an exterior surface of the blade to an internal cooling cavity located in an airfoil via a plurality of openings in the airfoil proximate to a trailing edge of the airfoil; and
locating an array of pedestals within the internal cooling cavity, the array of pedestals extending between opposite sides of the internal cavity and including a first row of pedestals and a second row of pedestals, the second row of pedestals being directly adjacent to the first row of pedestals, wherein the entire first row of pedestals are further from the trailing edge than the second row of pedestals and the second row of pedestals are closer to the trailing edge than any other pedestals of the array of pedestals and a lowermost pedestal of the first row of pedestals is further from a platform secured to the blade than a lowermost pedestal of the second row of pedestals, wherein the lowermost pedestal of the second row of pedestals is closer to the platform than any other pedestal of the airfoil; and wherein the plurality of openings are located between the trailing edge and the second row of pedestals, the plurality of openings being in fluid communication with the internal cooling cavity.

19. The method as in claim 18 , wherein the array of pedestals further comprises a third row of pedestals directly adjacent to the first row of pedestals, wherein the third row of pedestals are further from the trailing edge than the first row of pedestals and the lowermost pedestal of the third row of pedestals is further from the platform than a lowermost pedestal of the first row of pedestals.

20. The met

Assignees

• United Technologies Corp

Inventors

• Thistle Charles
• Xue Yongxiang D

Classifications

• F05D2260/22141

  using fins or ribs · CPC title

• F05D2260/2214

  by increasing the heat transfer surface · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/202

  by film cooling · 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