Article having cooling passage with undulating profile

Patent metadata

Field	Value
Publication number	US-10030523-B2
Application number	US-201514622000-A
Country	US
Kind code	B2
Filing date	Feb 13, 2015
Priority date	Feb 13, 2015
Publication date	Jul 24, 2018
Grant date	Jul 24, 2018

Abstract

An article for gas turbine engine includes a body that has a gaspath side for exposure in a core gaspath of a gas turbine engine. The gaspath side has an undulating surface. A cooling passage is in the body. The cooling passage has a undulating profile that corresponds to the undulating surface.

First claim

What is claimed is:

1. An article for a gas turbine engine, comprising:
a cast body defining a gaspath side for exposure in a core gaspath of a gas turbine engine, a non-gaspath side, leading and trailing ends, and first and second mateface sides, the gaspath side having an undulating surface defining body peaks and valleys; and
a cooling passage in the cast body between the gaspath side and the non-gaspath side, the cooling passage having an undulating profile that corresponds to the undulating surface, wherein the undulating profile is defined by a radially outer surface of the cooling passage and a radially inner surface of the cooling passage such that the radially outer surface and the radially inner surface have passage peaks and valleys that align in a one-for-one correspondence with the body peaks and valleys.

2. The article as recited in claim 1 , wherein the undulating surface has body peaks and valleys, and the undulating profile has passage peaks and valleys that substantially align with the body peaks and valleys such that a wall defined between the cooling passage and the undulating surface has a substantially constant thickness.

3. The article as recited in claim 1 , wherein the undulating surface has body peaks and valleys, and the undulating profile has passage peaks and valleys that align with the body peaks and valleys such that a wall defined between the cooling passage and the undulating surface has a thickness within +/−0.030 inches (762 micrometers).

4. The article as recited in claim 1 , wherein the undulating surface has body peaks and valleys, and the undulating profile has passage peaks and valleys that align with the body peaks and valleys such that a wall defined between the cooling passage and the undulating surface has a constant thickness.

5. The article as recited in claim 1 , wherein the undulating profile corresponds to the undulating surface such that a first wall between the cooling passage and the undulating surface has a substantially constant thickness, and a second wall between the cooling passage and an opposed side of the body has a varying thickness.

6. The article as recited in claim 1 , wherein the undulating surface is three-dimensionally undulating.

7. The article as recited in claim 1 , wherein the body is a platform of an airfoil.

8. The article as recited in claim 1 , wherein the undulating surface has at least one body peak or valley, and the undulating profile has at least one passage peak or valley that corresponds to the at least one body peak or valley.

9. An article for a gas turbine engine, comprising:
a unitary body having forward and trailing ends, first and second mateface sides, and gaspath and non-gaspath sides, the gaspath side having an undulating surface defining body peaks and valleys; and
a cooling passage in the unitary body between the gaspath and non-gaspath sides, the cooling passage conforming to the undulating surface, wherein the undulating profile is defined by a radially outer surface of the cooling passage and a radially inner surface of the cooling passage such that the radially outer surface and the radially inner surface have passage peaks and valleys that align in a one-for-one correspondence with the body peaks and valleys.

10. The article as recited in claim 9 , wherein the cooling passage conforms to the undulating surface such that for a given thermal profile at the undulating surface there is a uniform temperature profile variation through a wall defined between the cooling passage and the undulating surface.

11. The article as recited in claim 9 , wherein the cooling passage conforms to the undulating surface such that a wall defined between the cooling passage and the undulating surface has a constant thickness.

12. The article as recited in claim 9 , wherein the cooling passage conforms to the undulating surface such that a wall defined between the cooling passage and the undulating surface has a substantially constant thickness within +/−0.030 inches (762 micrometers).

13. The article as recited in claim 9 , wherein the undulating surface is three-dimensionally undulating.

14. The article as recited in claim 9 , wherein the body is a platform of an airfoil.

15. A casting core comprising:
a core body for forming a cooling passage in a gas turbine engine article, the core body having an undulating profile that conforms to an undulating surface on a gaspath side of the article wherein the undulating profile is defined by a radially outer surface of the core body and a radially inner surface of the core body such that the radially outer surface and the radially inner surface have core body peaks and valleys that align in a one-for-one correspondence with peaks and valleys of the undulating surface on a gaspath side of the article.

16. The casting core as recited in claim 15 , wherein the undulating profile is three-dimensionally undulating.

17. The article as recited in claim 1 , wherein the non-gaspath side is non-conforming with the gaspath side.

18. The article as recited in claim 1 , wherein the cooling passage has an inlet located towards the leading end and an outlet located toward the trailing end.

19. The article as recited in claim 1 , wherein the cooling passage includes a plurality of internal features that increase surface area in the cooling passage for thermal transfer.

20. The article as recited in claim 9 , wherein the non-gaspath side is non-conforming with the gaspath side.

21. The article as recited in claim 9 , wherein the cooling passage has an inlet located towards the leading end and an outlet located toward the trailing end.

22. The article as recited in claim 9 , wherein the cooling passage includes a plurality of internal features that increase surface area in the cooling passage for thermal transfer.

23. The article as recited in claim 1 , wherein the cooling passage is of constant thickness.

24. The article as recited in claim 9 , wherein the cooling passage is of constant thickness.

Assignees

• United Technologies Corp

Inventors

• Quach San
• Propheter-Hinckley Tracy A
• Gautschi Steven Bruce

Classifications

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F01D5/187

  Convection cooling · CPC title

• F05D2250/184

  sinusoidal · CPC title