STATIONARY TURBINE COMPONENT WITH LAMINATED SKIN

• US 20100054933A1
• Filed: 09/04/2008
• Published: 03/04/2010
• Est. Priority Date: 09/04/2008
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: James, Allister W.
• Granted Patent: US 8,241,001 B2
• Time in Patent Office: Days
• US Class Current: 415/200
• CPC Class Codes: F01D 5/147 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 Class Codes: F01D 5/34 Rotor-blade aggregates of unitary construction , e.g. formed of sheet laminae; discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence

Abstract

A stationary turbine engine component, such as a turbine vane, includes a internal spar and an external skin. The internal spar is made of a plurality of spar laminates, and the external skin is made of a plurality of skin laminates. The plurality of skin laminates interlockingly engage the plurality of spar laminates such that the external skin is located and held in place. This arrangement allows alternative high temperature materials to be used on turbine engine components in areas where their properties are needed without having to make the entire component out of such material. Thus, the manufacturing difficulties associated with making an entire component of such a material and the attendant high costs are avoided. The skin laminates can be made of advanced generation single crystal superalloys, intermetallics and refractory alloys.

Claims

1. A stationary turbine engine component comprising:

an internal spar made of a plurality of spar laminates;

an external skin made of a plurality of skin laminates, each external skin laminate having an outer wall and a retention portion, wherein the retention portion of each skin laminate is disposed between and in interlocking engagement with two neighboring spar laminates, whereby the skin laminates are held in place by their interlocking engagement with the spar laminates.

2. The stationary turbine engine component of claim 1 wherein each of the external skin laminates is made of one of advanced generation single crystal superalloys, intermetallics, nickel-based intermetallics, refractory alloys and oxide dispersion strengthened alloys.

3. The stationary turbine engine component of claim 1 wherein each of the external skin laminates is made of a material that can withstand at least about 1300 to about 1400 Celsius.

4. The stationary turbine engine component of claim 1 wherein at least a portion of the skin laminates is coated with an environmental barrier coating.

5. The stationary turbine engine component of claim 1 wherein each spar laminate includes a body portion having at least one planar surface, wherein the planar surface of one spar laminate abuts the planar surface of the body portion of a neighboring spar laminate.

6. The stationary turbine engine component of claim 1 wherein each spar laminate has an outer peripheral surface, wherein the outer wall of each skin laminate is spaced from the outer peripheral surface of each spar laminate that it is in interlocking engagement with such that a cavity is defined therebetween.

7. The stationary turbine engine component of claim 6 wherein the retention portion of each skin laminate includes a bridge portion that extends inward from the outer wall, whereby the outer wall is spaced from the outer peripheral surface of each laminate, wherein the bridge portion includes at least one passage extending therethrough.

8. The stationary turbine engine component of claim 1 wherein the outer wall of each skin laminate includes an upper end surface and a lower end surface, wherein at least one of the upper end surface and the lower end surface abuts an opposite one of the upper end surface and the lower end surface of a neighboring skin laminate.

9. The stationary turbine engine component of claim 8 wherein an interface is formed between the abutting surfaces of the outer wall of neighboring skin laminates, wherein the interface is angled relative to horizontal.

10. The stationary turbine engine component of claim 1 wherein the retention portion of each skin laminate includes a bridge portion that extends inward from the outer wall, wherein the bridge portion transitions into a transverse engaging portion.

11. The stationary turbine engine component of claim 10 wherein the bridge portion and the engaging portion are generally T-shaped in cross-section.

12. The stationary turbine engine component of claim 1 wherein the skin laminates are held in place solely by their interlocking engagement with the spar laminates, whereby no other structure is used to hold the skin laminates in place.

13. A stationary turbine engine component comprising:

a first and a second internal spar laminate, each spar laminate including a body portion having a substantially planar upper surface and a substantially planar lower surface,

the first and a second internal spar laminates further including a retention portion extending at least partially about the body portion, each retention portion including a bridge portion extending outward from the body portion, the bridge portion transitioning into a transverse engaging portion that defines an outer peripheral surface of each spar laminate, and

an external skin laminate having an outer wall and a retention portion, the retention portion including a bridge portion extending inward from the outer wall, the bridge portion transitioning to a transverse engaging portion,

the laminates being arranged so that the retention portion of the skin laminate is disposed between and in interlocking engagement with the retention portion of first and second spar laminates, and so that the upper planar surface of the first spar laminate is substantially adjacent to the lower planar surface of the second spar laminate, and so that the outer wall of the skin laminate is spaced from the outer peripheral surface of the first and second spar laminates.

14. The stationary turbine engine component of claim 13 wherein the retention portion of the first and second spar laminates is generally T-shaped in cross-section, and wherein the retention portion of the skin laminate is generally T-shaped in cross-section.

15. The stationary turbine engine component of claim 13 wherein the skin laminate is made of one of advanced generation single crystal superalloys, intermetallics, nickel-based intermetallics, refractory alloys and oxide dispersion strengthened alloys.

16. A stationary turbine engine component of claim 13 wherein the outer wall of the skin laminate includes an upper end surface and a lower end surface, wherein the upper end surface and the lower end surface are angled relative to horizontal.

17. The stationary turbine engine component of claim 13 wherein the skin laminate is held in place solely by its interlocking engagement with the first and second spar laminates.

18. A turbine vane assembly comprising:

an inner shroud;

an outer shroud; and

an airfoil extending between and operatively engaging the inner shroud and the outer shroud;

the airfoil including;

an internal spar made of a plurality of generally airfoil shaped spar laminates, each spar laminate including a body portion and a retention portion extending at least partially about the body portion;

an external skin made of a plurality of generally airfoil shaped skin laminates, each external skin laminate having an outer wall and a retention portion, wherein the retention portion of each skin laminate is disposed between and in interlocking engagement with the retention portion of two neighboring spar laminates, wherein each skin laminate is held in place by interlocking engagement with the spar laminates, wherein at least one end of the outer wall of each skin laminate abuts an end of the outer wall of a neighboring skin laminate,

wherein each skin laminate is made of one of advanced generation single crystal superalloys, intermetallics, nickel-based intermetallics, refractory alloys and oxide dispersion strengthened alloys.

19. The turbine vane assembly of claim 18 wherein each spar laminate has an outer peripheral surface, wherein the retention portion of each skin laminate includes a bridge portion that extends inward from the outer wall, the bridge portion transitioning into a transverse engaging portion, wherein the outer wall of each skin laminate is spaced from the outer peripheral surface of each spar laminate that it is in interlocking engagement with, wherein a plurality of cavities are formed between the outer wall of the skin laminates, the outer peripheral surface of the spar laminates and the bridge portion of each skin laminate.

20. The stationary turbine engine component of claim 19 wherein one of the cavities is in fluid communication with a neighboring cavity by way of passages extending through the bridge portion of the skin laminate separating the two cavities.