Combined featherseal slot and lightening pocket

Patent metadata

Field	Value
Publication number	US-9441497-B2
Application number	US-71132710-A
Country	US
Kind code	B2
Filing date	Feb 24, 2010
Priority date	Feb 24, 2010
Publication date	Sep 13, 2016
Grant date	Sep 13, 2016

Abstract

A segmented engine component has multiple segments which are connected to each other via a featherseal arrangement. Each of the components has a combined featherseal slot and lightening pocket.

First claim

What is claimed is:

1. A method for creating a segmented engine component comprising the steps of;
casting a plurality of segments for said segmented component, wherein each of said segments comprises a body having internal coolant passages and at least a first joint end capable of connecting to a first joint end of an adjacent segment, said first joint end comprises a coolant inlet connected to said internal coolant passages, and at least a portion of said body has a foil shaped profile; and
simultaneously milling at least a featherseal slot and a lightening pocket into at least one circumferential edge of said joint end of each of said plurality of segments.

2. The method of claim 1 , wherein said step of simultaneously milling at least a featherseal slot and a lightening pocket into each of said plurality of segments further comprises using an Electrical Discharge Machining (EDM) process to perform said milling.

3. The method of claim 2 , wherein said step of simultaneously milling at least a featherseal slot and a lightening pocket into each of said plurality of segments further comprises removing flashing resulting from said step of casting a plurality of segments.

4. The method of claim 2 , wherein said EDM process utilizes an EDM tool having a generally T-shaped cross section with a cross bar portion for milling a featherseal slot, and a post portion for milling a lightening pocket.

5. The method of claim 4 , wherein said cross bar portion has a component which is convex relative to said post portion.

6. The method of claim 4 , wherein said cross bar portion comprises a component perpendicular to said post portion in a cross-sectional plane.

7. The method of claim 4 , wherein said cross bar portion and said post portion are a single piece of material.

8. The method of claim 4 , wherein said post portion is at least substantially rectangular and comprises a component perpendicular to said cross bar in a cross sectional plane.

9. The method of claim 1 , wherein said segmented engine component is a gas turbine engine vane assembly.

10. The method of claim 1 , further comprising the additional step of assembling said segmented component such that each of said joint ends is connected to at least one adjacent joint end and said connection is sealed using a featherseal arrangement.

11. The method of claim 1 , wherein said step of simultaneously milling at least a featherseal slot and a lightening pocket into at least one circumferential edge of said joint end of each of said plurality of segments comprises milling said featherseal slot and said lightning pocket to a uniform depth into said segment.

12. A gas turbine engine component comprising;
a plurality of segments, wherein each of said segments comprises a body having coolant passages, and at least a first joint end having a cooling inlet, and at least one featherseal slot and lightening pocket in a circumferential edge of said first joint end, and wherein said featherseal slot and said lightening pocket comprise a single gap in said component, wherein said single gap has a uniform depth into said segment; and
each of said segments being connected to at least one adjacent segment such that a sealed cooling passage connects each of said segment's cooling inlets.

13. The gas turbine engine component of claim 12 , wherein said single gap has a generally T-shaped cross section.

14. The gas turbine engine component of claim 13 , wherein said generally T-shaped cross section comprises a cross bar portion and a post portion, and wherein said post portion of said cross section extends from said cross bar portion away from said segment body.

15. The gas turbine engine component of claim 12 , wherein each of said segments is connected to at least one adjacent segment via a featherseal arrangement.

16. The gas turbine engine component of claim 15 , wherein said featherseal arrangement comprises a sheet of material partially inserted in a featherseal slot on a first of said plurality of segments, and partially inserted in a featherseal slot on a second of said plurality of segments, and wherein said first and second of said plurality of segments are immediately adjacent to each other.

17. The gas turbine engine component of claim 12 , wherein the assembled gas turbine engine component is a turbine vane assembly.

18. The gas turbine engine component of claim 17 , wherein each of said plurality of segment's bodies comprises a foil shaped profile.

19. The gas turbine engine component of claim 12 , wherein said single gap in said component is filled in while said component is cast, and is removed via an Electrical Discharge Machining process.

20. The gas turbine engine component of claim 12 , wherein said single gap in said component comprises substantially no flashing.

Assignees

• Bergman Russell J
• Kovach Scott A
• United Technologies Corp

Inventors

• Bergman Russell J
• Kovach Scott A

Classifications

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2240/12

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