Contoured blade outer air seal for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016003082-A1
Application number	US-201414771281-A
Country	US
Kind code	A1
Filing date	Feb 4, 2014
Priority date	Feb 28, 2013
Publication date	Jan 7, 2016
Grant date	—

Abstract

A blade outer air seal (BOAS) segment according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face, wherein a radial position of the radially inner face varies at a given axial position.

First claim

1 . A blade outer air seal (BOAS) segment, comprising:
a seal body having a radially inner face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face, wherein a radial position of the radially inner face varies at a given axial position.

2 . The BOAS segment of claim 1 , wherein the given axial position is upstream from a rub track of the radially inner face.

3 . The BOAS segment of claim 2 , wherein the given axial position is a first given axial position, and a radial position of the radially inner face varies at a second given axial position that is downstream from the rub track of the radially inner face.

4 . The BOAS segment of claim 1 , wherein the radial position of the radially inner face smoothly varies at the given axial position.

5 . The BOAS segment of claim 1 , wherein the radial position of the radially inner face undulates at the given axial position between positions that are radially closer to the a central axis and positions that are radially further from the central axis.

6 . The BOAS segment of claim 1 , wherein the radial position of the radially inner face is contoured.

7 . The BOAS segment of claim 1 , wherein the BOAS includes at least a layer of an additive manufacturing material.

8 . A blade outer air seal (BOAS) assembly, comprising:
a BOAS segment including a radial inner face that circumferentially extends between a first mate face and a second mate face and axially extends between a leading edge face and a trailing edge face; and at least one contour extending radially a prescribed distance from another area of the radially inner face.

9 . The BOAS assembly of claim 8 , wherein the at least one contour includes a contour at the leading edge face configured to align with a contour extending radially a prescribed distance from a vane wall of a vane stage that is directly upstream from the BOAS segment.

10 . The BOAS assembly of claim 8 , wherein the at least one contour is entirely upstream from a rub track of the radially inner face.

11 . The BOAS assembly of claim 8 , wherein the at least one contour includes at least one peak, trough, or both.

12 . The BOAS assembly of claim 8 , wherein the at least one contour includes a contour having first axial end and an opposing, second axial end, an circumferential width of the first axial end greater than a circumferential width of the second axial end.

13 . The BOAS assembly of claim 8 , wherein the at least one contour includes a first contour that is upstream from a rub track of the radially inner face and a second contour that is downstream from the rub track.

14 . The BOAS assembly of claim 13 , wherein the second contour extends to the trailing edge face and is configured to align with a contour extending radially a prescribed distance from a vane wall of a vane stage that is directly downstream from the BOAS segment.

15 . The BOAS assembly of claim 8 , including at least one cooling hole having an exit at the at the least one contour.

16 . The BOAS assembly of claim 8 , wherein the BOAS segment is a first BOAS segment, and a second BOAS segment interfaces with the first BOAS segment at the first mate face, the second BOAS segment having a second radially inner face and at least one second contour extending radially a prescribed distance from the second radially inner face, wherein a position of the at least one first contour on the first radially inner face is different than a position of the at least one second contour on the second radially inner face.

17 . A method of providing a Blade Outer Air Seal (BOAS) configured to influence flow within a gas turbine engine, comprising:
providing a feature of a BOAS, the feature configured to influence flow moving across a radially inner face of a BOAS.

18 . The method of claim 17 , wherein the feature is a continuation of a feature of a vane wall that is axially adjacent the BOAS.

19 . The method of claim 17 , using an additive manufacturing process to form at least a portion of the BOAS.

20 . The method of claim 17 , wherein the feature causes a radial position of the radially inner face to vary at a given axial position.

21 . An assembly, comprising:
a vane segment; a blade outer air seal (BOAS) segment adjacent the vane segment; and a radially extending contour; wherein the contour resides on both the vane segment and the BOAS segment.

22 . The assembly of claim 21 , wherein the contour is located on a vane wall of the vane segment.

23 . The assembly of claim 21 , wherein the contour is located on a radially inner face of the BOAS.

24 . The assembly of claim 21 , wherein the contour includes at least one peak, trough, or both.

25 . The assembly of claim 21 , wherein the vane segment is upstream of the BOAS segment.

26 . The assembly of claim 21 , wherein the vane segment is downstream of the BOAS segment.

27 . The assembly of claim 21 , further comprising:
a second vane segment adjacent the BOAS segment, wherein the BOAS segment is located between the vane segment and the second vane segment; and a second contour residing on both the second vane segment and the BOAS segment.

28 . The assembly of claim 21 , including at least one cooling hole having an exit at the contour.

29 . The assembly of claim 27 , further comprising:
a third vane segment adjacent the vane segment or the second vane segment; and a third contour residing on both the third vane segment and the BOAS segment.

30 . The assembly of claim 21 , further comprising:
a second vane segment adjacent the BOAS segment and the second vane segment; and a second contour residing on both the second vane segment and the BOAS segment.

31 . A vane segment locatable adjacent a blade outer air seal (BOAS) segment, the vane segment comprising:
a vane wall; and a contour extending radially from said vane wall; wherein said contour corresponds to a contour on the BOAS segment.

32 . A blade outer air seal (BOAS) segment locatable adjacent a vane segment, the BOAS segment comprising:
a radially inner face; and a contour extending radially from said inner face; wherein said contour corresponds to a contour on the vane segment.

Assignees

• United Technologies Corp

Inventors

• Lutjen Paul M
• Bruskotter Michael J

Classifications

• F05D2240/12

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

• F05D2260/202

  by film cooling · CPC title

• F01D11/12 Primary

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2220/32

  in gas turbines · CPC title