Seal ring for turbine shroud in gas turbine engine with arch-style support

Patent metadata

Field	Value
Publication number	US-11015485-B2
Application number	US-201916386809-A
Country	US
Kind code	B2
Filing date	Apr 17, 2019
Priority date	Apr 17, 2019
Publication date	May 25, 2021
Grant date	May 25, 2021

Abstract

A blade track assembly for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form a blade track. Each of the plurality of blade track segments includes a first circumferential end face, a second circumferential end face opposite the first circumferential end face, a radially-outer surface, and a radially inner surface opposite the radially-outer surface.

First claim

What is claimed is:

1. A blade track assembly for a gas turbine engine, the blade track assembly comprising
a plurality of blade track segments that comprise only isotropic ceramic materials, each of the plurality of blade track segments being wedge shaped, and the plurality of blade track segments positioned circumferentially around an axis to form a ring,
an annular band comprising anisotropic ceramic-matrix composite materials, the annular band being disposed circumferentially around each of the plurality of blade track segments to provide a radially inward force that acts against each of the plurality of blade track segments such that each of the plurality of blade track segments act as a voussoir to maintain a form of the ring, and
a ceramic cloth ring that extends circumferentially around the plurality of blade track segments and located radially between the plurality of blade track segments and the annular band.

2. The blade track assembly of claim 1 , wherein each of the plurality of blade track segments include a first end face, a second end face spaced apart circumferentially from the first end face, and a radially-outer surface that extends between the first end face and the second end face.

3. The blade track assembly of claim 2 , wherein each end face of the blade track segments are arranged entirely along a plane that extends radially through the axis.

4. The blade track assembly of claim 2 , wherein the radially outer surface of each of the blade track segments is continuous and formed without holes or protrusions.

5. The blade track assembly of claim 4 , wherein each of the blade track segments includes a radially inner surface that is continuous and formed without holes or protrusions.

6. The blade track assembly of claim 5 , wherein the radially-outer surface is spaced apart from the axis a first radial distance and the radially-inner surface is spaced apart from the axis a second radial distance that is less than the first radial distance and each blade track segment has a constant thickness defined by the difference between the first distance and the second distance.

7. The blade track assembly of claim 2 , wherein the first end face and the second end face interconnect directly the radial-outer and radially-inner surfaces without any protrusions or cutouts formed therein.

8. The blade track assembly of claim 7 , wherein the plurality of blade track segments include a plurality of first blade track segments and a plurality of second blade track segments with an axially-facing surface that is offset axially from the plurality of first blade track segments.

9. The blade track assembly of claim 8 , further comprising a carrier arranged circumferentially around the annular band to support the plurality of blade tracks relative to the axis, and the carrier engages a circumferential end face of the second blade track segment to block rotation of the plurality of blade track segments about the axis.

10. The blade track assembly of claim 9 , wherein the carrier is multi-piece in the circumferential direction and engages the leading end and the trailing end each of the first blade track segments to limit axial movement of the plurality of blade track segments relative to the axis.

11. The blade track assembly of claim 1 , wherein the ceramic cloth ring has a first axial length and the annular band has a second axial length that is less than the first axial length.

12. A blade track assembly for a gas turbine engine, the blade track assembly comprising
a plurality of blade track segments that comprise only isotropic ceramic materials, each of the plurality of blade track segments being wedge shaped, and the plurality of blade track segments positioned circumferentially around an axis to form a ring,
an annular band comprising anisotropic ceramic-matrix composite materials, the annular band being disposed circumferentially around each of the plurality of blade track segments to provide a radially inward force that acts against each of the plurality of blade track segments such that each of the plurality of blade track segments act as a voussoir to maintain a form of the ring,
wherein a first blade track segment included in the plurality blade track segments has a first axial length and a second blade track segment included in the plurality of blade track segments has a second axial length that is greater than the first axial length to provide an anti-rotation feature.

13. The blade track assembly of claim 12 , wherein the first blade track segment has a first circumferential length, the second blade track segment has a second circumferential length, and the first circumferential length is greater than the second circumferential length.

14. A method comprising
positioning a plurality of blade track segments circumferentially around a central axis, each blade track segment shaped to extend part-way around the central axis,
locating the plurality of blade track segments around the central axis to form a ring of the plurality of blade track segments,
heating an annular ceramic-matrix composite band,
positioning the annular ceramic-matrix composite band circumferentially around the plurality of blade track segments after heating the annular ceramic-matrix composite band, and
applying a compressive force against the each of the plurality of blade track segments with the annular ceramic-matrix composite band to maintain a form of the ring, wherein each of the blade track segments act as a voussoir to maintain a form of the ring, and
further comprising positioning a ceramic cloth ring circumferentially around the plurality of blade track segments before positioning the annular ceramic-matrix composite band around the plurality of blade track segments.

15. The method of claim 14 , wherein the plurality of blade track segments includes a first blade track segment having a first axial width and a first circumferential length and a second blade track segment having a second axial width and a second circumferential length, the second axial width is greater than the first axial length, and the first circumferential length is greater than the second circumferential length.

16. The method of claim 14 , wherein the positioning a plurality of blade track segments includes positioning a plurality of first blade track segments partway around the central reference axis, each of the plurality of first blade track segments having a first axial width, and positioning at least one second blade track segment partway around the central axis between two of the first blade track segments to form the ring, the at least one second blade track segment having a second axial width that is greater than the first axial width.

17. The method of claim 16 , further comprising arranging a carrier circumferentially around the plurality of blade track segments to cause the carrier to engage the second blade track segment to limit rotation of the plurality of blade track segments relative to the axis.

18. The method of claim 14 , further comprising providing a carrier and engaging the ceramic cloth ring with the carrier to form a seal between the carrier and the plurality of blade track segments to block fluid flow between the carrier and the blade track segments in an axial direction.

Assignees

• Rolls Royce Corp

Inventors

• Moga Corina
• Starr Shaling

Classifications

• F01D9/04

  forming ring or sector · CPC title

• F05C2253/04

  Composite, e.g. fibre-reinforced · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title