Full hoop blade track with flanged segments

Patent metadata

Field	Value
Publication number	US-10550709-B2
Application number	US-201615088884-A
Country	US
Kind code	B2
Filing date	Apr 1, 2016
Priority date	Apr 30, 2015
Publication date	Feb 4, 2020
Grant date	Feb 4, 2020

Abstract

A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.

First claim

What is claimed is:

1. A blade track assembly for a gas turbine engine, the blade track assembly comprising
a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis, each of the plurality of blade track segments including an arcuate runner extending in a circumferential direction around a portion of the central axis and a pair of flanges extending outwardly in a radial direction away from circumferential ends of the arcuate runner,
wherein each one of the pair of flanges of each of the plurality of blade track segments is coupled to a corresponding flange of a circumferentially adjacent blade track segment to resist movement of the plurality of blade track segments relative to each other,
wherein each flange of the pair of flanges is formed to include a channel extending circumferentially through and radially into each flange of the pair of flanges, and the channels of the circumferentially adjacent blade track segments are aligned.

2. The blade track assembly of claim 1 , wherein the pair of flanges of each of the plurality of blade track segments are generally planar.

3. The blade track assembly of claim 1 , further comprising a plurality of locating keys, each one of the plurality of locating keys received in the channels of the circumferentially adjacent blade track segments to locate the circumferentially adjacent blade track segments relative to one another in an axial direction parallel to the central axis.

4. The blade track assembly of claim 1 , wherein the plurality of locating keys are made of ceramic matrix composite materials.

5. An assembly adapted for use in a gas turbine engine, the assembly comprising
a plurality of ceramic matrix composite material segments arranged circumferentially adjacent to one another around a central axis, each of the plurality of ceramic matrix composite material segments including an arcuate surface extending in a circumferential direction around a portion of the central axis and a plurality of flanges extending outwardly in a radial direction away from the arcuate surface, and
a plurality of ceramic matrix composite material connectors received by flanges of circumferentially adjacent ceramic matrix composite material segments to secure circumferentially adjacent ceramic matrix composite material segments to one another,
wherein each of the plurality of flanges is formed to include a channel extending circumferentially through and radially into each of the plurality of flanges, and each of the plurality of ceramic matrix composite material connectors is received in the channels of circumferentially adjacent ceramic matrix composite material segments.

6. The assembly of claim 5 , wherein when one of the plurality of ceramic matrix composite material connectors is received in the channels of circumferentially adjacent ceramic matrix composite material segments, an interference fit is formed between the one of the ceramic matrix composite material connectors and the circumferentially adjacent ceramic matrix composite material segments.

7. An assembly comprising
a first component consisting essentially of ceramic matrix composite material, the first component having an external face and an internal face opposite the external face of the first component,
a second component consisting essentially of ceramic matrix composite material, the second component having an external face and an internal face opposite the external face of the second component arranged in confronting relation with the internal face of the first component, and
a fastener consisting essentially of ceramic matrix composite material that extends through the first component and the second component to couple the first component and the second component, the fastener including a first flared head that extends into the first component from the external face of the first component toward the internal face of the first component, a second flared head that extends into the second component from the external face of the second component toward the internal face of the second component, and a body that extends through the internal faces of the first and second components and interconnects the first flared head and the second flared head,
wherein each of the first component and the second component are formed to include a channel extending circumferentially through and radially into each of the first component and the second component, and wherein the fastener is received in the channels of the first component and second component.

8. The assembly of claim 7 , wherein (i) the body interconnects the first flared head at a first neck of the fastener, (ii) the body interconnects the second flared head at a second neck of the fastener, and (iii) the first and second flared heads extend outwardly in an axial direction from the respective first and second necks toward the respective external faces of the first and second components.

9. The assembly of claim 7 , wherein the fastener comprises a plurality of strands including ceramic-containing reinforcement fibers that extend through the first and second components from the external face of the first component to the external face of the second component.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp
• Rolls Royce Plc
• Rolls Royce High Temperature Composites Inc

Inventors

• Vetters Daniel K
• Sippel Aaron D
• Thomas David J
• Eifert Andrew J
• Davis Paul A
• Jones Simon L
• Hillier Steven M
• Broadhead Peter
• Doyle Joseph
• Jacquinto Michael
• Thibault Wesley
• Shi Jun
• Townes Roderick

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title