Keystoned blade track

Patent metadata

Field	Value
Publication number	US-10563535-B2
Application number	US-201615090134-A
Country	US
Kind code	B2
Filing date	Apr 4, 2016
Priority date	Apr 29, 2015
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

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 system for a gas turbine engine, the blade-track system comprising
a plurality of blade track segments positioned circumferentially around a central axis to form a ring providing a blade track, each blade track segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, each blade track segment including opposing circumferential end faces and a radially outer surface, and
a track biaser positioned to surround the blade track,
wherein the end faces of the blade track segments are engaged with one another and the track biaser is configured to bias the blade track segments toward the central axis such that each blade track segment acts as a keystone to maintain the form of the ring,
wherein the end faces of the blade track segments are configured to engage and form a resultant radially-outward force away from the central axis against the track biaser and wherein the track biaser is positioned to engage the radially outer surface of the blade track segments to provide a radially-inward force against the blade track segments,
wherein the track biaser includes at least one unitary ring sized to surround the blade track and engage the outer surfaces of the blade track segments, and
wherein the at least one unitary ring includes a first unitary ring substantially aligned with an axially-forward face of the blade track segments and a second unitary ring substantially aligned with an axially-aft face of the blade track segments.

2. The blade track of claim 1 , wherein each of the blade track segments further includes a first bevel surface extending between the axially-forward face and the outer surface and a second bevel surface extending between the axially-aft face and the outer surface, wherein the first and second bevel surfaces are angled radially inward relative to the outer surface, and wherein the first and second rings are configured to engage the first and second bevel surfaces to provide the radially-inward force, and
further comprising springs positioned to bias the first and second rings toward one another.

3. A blade-track system for a gas turbine engine, the blade-track system comprising
a plurality of blade track segments positioned circumferentially around a central axis to form a ring providing a blade track, each blade track segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, each blade track segment including opposing circumferential end faces and a radially outer surface, and
a track biaser positioned to surround the blade track,
wherein the end faces of the blade track segments are engaged with one another and the track biaser is configured to bias the blade track segments toward the central axis such that each blade track segment acts as a keystone to maintain the form of the ring,
wherein the end faces of the blade track segments are configured to engage and form a resultant radially-outward force away from the central axis against the track biaser and wherein the track biaser is positioned to engage the radially outer surface of the blade track segments to provide a radially-inward force against the blade track segments,
wherein the track biaser includes at least one unitary ring sized to surround the blade track and engage the outer surfaces of the blade track segments, and
wherein the track biaser further includes a plurality of outer fins extending radially outward from and circumferentially along the at least one unitary ring, and wherein the fins are spaced apart from one another to define radially-outwardly opening cooling channels.

4. The blade track of claim 3 , further comprising one of a thermal barrier layer and an insulative material positioned between the at least one unitary ring and the blade track.

5. The blade track of claim 3 , wherein the track biaser further includes a plurality of inner fins extending radially inward from and circumferentially along the at least one unitary ring, and wherein the inner fins are spaced apart from one another to define insulation-receiving channels that contain an insulative material.

6. A blade-track system for a gas turbine engine, the blade-track system comprising
a plurality of blade track segments positioned circumferentially around a central axis to form a ring providing a blade track, each blade track segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, each blade track segment including opposing circumferential end faces and a radially outer surface, and
a track biaser positioned to surround the blade track,
wherein the end faces of the blade track segments are engaged with one another and the track biaser is configured to bias the blade track segments toward the central axis such that each blade track segment acts as a keystone to maintain the form of the ring,
wherein the end faces of the blade track segments are configured to engage and form a resultant radially-outward force away from the central axis against the track biaser and wherein the track biaser is positioned to engage the radially outer surface of the blade track segments to provide a radially-inward force against the blade track segments,
wherein the track biaser includes at least one band having first and second ends and the at least one band is sized to surround the blade track to engage the outer surfaces of the blade track segments and the track biaser includes a pin extending through the first and second ends of the band to couple the first end to the second end.

7. A blade-track system for a gas turbine engine, the blade-track system comprising
a plurality of blade track segments positioned circumferentially around a central axis to form a ring providing a blade track, each blade track segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, each blade track segment including opposing circumferential end faces and a radially outer surface, and
a track biaser positioned to surround the blade track,
wherein the end faces of the blade track segments are engaged with one another and the track biaser is configured to bias the blade track segments toward the central axis such that each blade track segment acts as a keystone to maintain the form of the ring,
wherein the end faces of the blade track segments are configured to engage and form a resultant radially-outward force away from the central axis against the track biaser and wherein the track biaser is positioned to engage the radially outer surface of the blade track segments to provide a radially-inward force against the blade track segments,
wherein each of the blade track segments further includes a runner and a pair of flanges that extend radially outward from the outer surface of the blade track segment,
wherein the track biaser is sized and positioned to contact the flanges, and
wherein the flanges are spaced apart from the end faces on the outer surface of the blade track segments.

8. A blade-track system for a gas turbine engine, the blade-track system comprising
a plurality of blade track segments positioned circumferentially around a central axis to form a ring providing a blade track, each blade track segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, each blade track segment including opposing circumferential end faces and a radially outer surface, and
a track biaser positioned to surround the blade track,
wherein the end faces of the blade track segments are engaged with one another and the track biaser is configured to bias the blade track segments toward the central axis such that each blade track segment acts as a keystone

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

• F05D2230/60

  Assembly methods · CPC title

• F01D11/122 Primary

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• C04B35/83

  Carbon fibres in a carbon matrix · CPC title

• F01D11/12

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

• F05D2240/11

  Shroud seal segments · CPC title