Diffusion bonded and superplastically formed turbomachine blade

• US 8,764,404 B2
• Filed: 12/16/2011
• Issued: 07/01/2014
• Est. Priority Date: 12/23/2010
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Wallis, Michael J., Barlow, Simon M.
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US13/328,579
• Publication Number:
  US 20120163983A1
• Time in Patent Office: 928 Days
• Field of Search: 416/229.R, 416/229.A, 416/232, 416/233
• US Class Current: 416/229.R
• CPC Class Codes: B23P 15/04 turbine or like blades from several pieces
• 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 5/18 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 Class Codes: F05D 2230/236 Diffusion bonding
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A diffusion bonded and superplastically formed turbomachine blade, the turbomachine blade comprising: a first layer (4); a second layer (6); and a membrane (2) disposed between the first and second layers (4, 6); wherein the membrane (2) is diffusion bonded to the first layer (4) along a plurality of first strips (10) and the membrane (2) is diffusion bonded to the second layer (6) along a plurality of second strips (12), wherein the first and second strips (10, 12) are offset from one another so that the membrane (2) is bonded to the first and second layers (4, 6) in an alternating pattern; wherein the membrane (2) has a recess (28) which extends into an area between an adjacent pair of first or second strips (10, 12).

Claims

1. A diffusion bonded and superplastically formed turbomachine blade, the turbomachine blade comprising:

a first layer;

a second layer; and

a membrane disposed between the first and second layers;

wherein;

the membrane is diffusion bonded to the first layer along a plurality of first strips and the membrane is diffusion bonded to the second layer along a plurality of second strips, wherein the first and second strips are offset from one another so that the membrane is bonded to the first and second layers in an alternating pattern; and

the membrane has a recess which extends into an area between an adjacent pair of first or second strips.

2. The turbomachine blade as claimed in claim 1, wherein

the strips are spaced from an edge of the turbomachine blade, and

the membrane is diffusion bonded to the first and/or second layers at a plurality of dots located between the edge of the turbomachine blade and the strips.

3. The turbomachine blade as claimed in claim 1, wherein the first strips are spaced further from an edge of the turbomachine blade than the second strips.

4. The turbomachine blade as claimed in claim 1, wherein

the strips are spaced from an edge of the turbomachine blade,

the membrane is diffusion bonded to the first and/or second layers at a plurality of dots located between the edge of the turbomachine blade and the strips, and

the first strips are spaced further from an edge of the turbomachine blade than the second strips.

5. The turbomachine blade as claimed in claim 1, wherein an end of the recess is located substantially equidistant between the adjacent pair of first or second strips.

6. A The turbomachine blade as claimed in claim 1, wherein

the first strips are spaced further from an edge of the turbomachine blade than the second strips, and

an end of the recess is located substantially equidistant between the adjacent pair of first or second strips.

7. The turbomachine blade as claimed in claim 1, wherein an end of the recess is located closer to one of the pair of first or second strips than the other of the pair of first or second strips.

8. The turbomachine blade as claimed in claim 1, wherein the recess tapers towards its end.

9. The turbomachine blade as claimed in claim 1, wherein

the first strips are spaced further from an edge of the turbomachine blade than the second strips, and

an end of the recess is located substantially equidistant between the adjacent pair of first or second strips, the recess tapering towards its end.

10. The turbomachine blade as claimed in claim 1, wherein the recess is v-shaped.

11. The turbomachine blade as claimed in claim 1, wherein an end of the recess has a radius.

12. A The turbomachine blade as claimed in claim 1, wherein

the first strips are spaced further from an edge of the turbomachine blade than the second strips, and

an end of the recess is located substantially equidistant between the adjacent pair of first or second strips, the recess tapering towards its end, the end of the recess having a radius.

13. The turbomachine blade as claimed in claim 11, wherein the radius is greater than or equal to a radius of an end of the first or second strips.

14. The turbomachine blade as claimed in claim 11, wherein the radius is less than or equal to a distance between adjacent first and second strips.

15. The turbomachine blade as claimed in claim 11, wherein the radius is less than or equal to a radius at a tip end of the recess.

16. The turbomachine blade as claimed in claim 1, wherein the first layer forms a suction surface of the turbomachine blade and the second layer forms a pressure surface of the turbomachine blade.

17. The turbomachine blade as claimed in claim 16, wherein the recess extends into an area between an adjacent pair of second strips.

18. The turbomachine blade as claimed in claim 1, wherein the blade is a compressor fan blade.