Keystoned blade track

Patent metadata

Field	Value
Publication number	US-11274567-B2
Application number	US-201916385725-A
Country	US
Kind code	B2
Filing date	Apr 16, 2019
Priority date	Apr 29, 2015
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

A blade track 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 the blade track.

First claim

What is claimed is:

1. A blade track for a gas turbine engine, the blade track comprising
a plurality of blade track segments, each of the plurality of blade track segments shaped to extend circumferentially part-way around an axis, and the plurality of blade track segments being positioned circumferentially around the axis to form a ring, and
an annular hoop arranged circumferentially around the entire ring whereby the annular hoop applies a radially-inward force toward the axis against each of the plurality of blade track segments such that each of the plurality of blade track segments acts as a keystone to maintain a form of the ring,
wherein each of the plurality of blade track segments includes opposing circumferential end faces and a radially outer surface extending between the end faces and wherein the end faces of neighboring blade track segments are engaged with one another, and
wherein the annular hoop comprises an annular composite-lock structure positioned to engage the radially outer surface of each of the plurality of blade track segments.

2. The blade track of claim 1 , wherein the annular composite-lock structure includes ceramic-matrix materials and at least one reinforcement fiber of ceramic-containing material suspended in the ceramic-matrix materials of the annular composite-lock structure and the annular composite-lock structure extends circumferentially around the entire ring to provide the radially-inward force toward the axis against each of the plurality of blade track segments such that each blade track segment acts as a keystone to maintain the form of the ring.

3. The blade track of claim 1 , wherein each of the plurality of blade track segments includes a runner that defines a radially outer surface and a pair of flanges that extend radially outward from the radially outer surface of the runner to form a radially-outward opening channel with the runner that receives at least a portion of the annular hoop.

4. The blade track of claim 1 , wherein each of the plurality of blade track segments comprises ceramic material.

5. The blade track of claim 4 , further comprising a thermal barrier layer positioned radially between the plurality of blade track segments and the annular hoop.

6. The blade track of claim 4 , wherein each of the plurality of the blade track segments include a runner that defines the radially outer surface and a pair of flanges that extend radially outward from the radially outer surface of the runner to form a radially-outward opening channel with the runner that receives at least a portion of the annular hoop.

7. The blade track of claim 1 , wherein the opposing circumferential end faces included in each of the plurality of blade track segments includes a first circumferential end face and a second circumferential end face spaced apart circumferentially from the first circumferential end face, the first circumferential end face and the second circumferential end face of each of the plurality of blade track segments are planar, and the first circumferential end face and the second circumferential end face of each of the plurality of blade track segments lie in planes defined in part by the axis.

8. The blade track of claim 1 , wherein each of the plurality of blade track segments comprise ceramic matrix composite materials.

9. The blade track of claim 1 , further comprising a thermal barrier layer positioned entirely radially between the plurality of blade track segments and the annular hoop.

10. A blade track for a gas turbine engine, the blade track comprising
a plurality of blade track segments, each of the plurality of blade track segments shaped to extend circumferentially part-way around an axis, and the plurality of blade track segments being positioned circumferentially around the axis to form a ring,
an annular hoop arranged circumferentially around the entire ring whereby the annular hoop applies a radially-inward force toward the axis against each of the plurality of blade track segments such that each of the plurality of blade track segments acts as a keystone to maintain a form of the ring,
wherein each of the plurality of blade track segments comprises ceramic material, and
wherein the annular hoop comprises ceramic materials.

11. The blade track of claim 10 , wherein the annular hoop comprises ceramic matrix composite materials.

12. The blade track of claim 10 , wherein each of the plurality of blade track segments includes opposing circumferential end faces and a radially outer surface extending between the end faces and wherein the end faces of neighboring blade track segments of the plurality of blade track segments are engaged with one another.

13. The blade track of claim 12 , wherein the annular hoop comprises an annular composite-lock structure positioned to engage the radially outer surface of each of the plurality of blade track segments.

14. The blade track of claim 13 , wherein the annular composite-lock structure includes ceramic-matrix materials and at least one reinforcement fiber of ceramic-containing material suspended in the ceramic-matrix materials of the annular composite-lock structure and the annular composite-lock structure extends circumferentially around the entire ring.

15. The blade track of claim 10 , further comprising a thermal barrier layer positioned radially between the plurality of blade track segments and the annular hoop.

16. A method of forming a blade track for use in a gas turbine engine, the method comprising
forming a plurality of blade track segments,
arranging the plurality of blade track segments around an axis to form a ring,
forming an annular hoop, and
positioning the annular hoop circumferentially around the ring to provide a radially inward force against the plurality of blade track segments such that each of the plurality of blade track segments acts as a keystone to maintain a form of the ring,
wherein each of the plurality of blade track segments comprise ceramic-matrix composite materials, and
wherein forming the annular hoop includes wrapping a single continuous fiber along radially outer surfaces of the plurality of blade track segments.

17. The method of claim 16 , further comprising heating the annular hoop before positioning the annular hoop circumferentially around the ring.

18. The method of claim 17 , wherein the annular hoop comprises metallic material and the entire annular hoop is located radially outward of the ring.

19. The method of claim 16 , wherein each of the plurality of blade track segments comprise ceramic materials.

20. The method of claim 16 , wherein positioning the annular hoop circumferentially around the ring includes press-fitting the annular hoop onto the ring.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp
• Rolls Royce Plc

Inventors

• Vetters Daniel K
• Sippel Aaron D
• Thomas David J
• Eifert Andrew J
• Davis Paul A
• Jones Simon L
• Broadhead Peter
• Varney Bruce E
• Walston Jeffrey A
• Hillier Steven

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2260/52

  involving springs · CPC title

• Y02T50/60

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

• F05D2240/55

  Seals · CPC title

• C04B2235/5252

  having a specific pre-form · CPC title