# US 11,441,434 B2 · Turbine ring assembly with curved rectilinear seatings

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- Number: US 11,441,434 B2
- Document ID: US11441434B2
- Status: Granted
- Kind: B2
- Application number: 17/311,892
- Filed: 2019-12-10
- Published: 2022-01-27
- Granted: 2022-09-13
- Earliest claimed: 2018-12-19
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Antoine Claude Michel Etienne Danis; Sébastien Serge Francis Congratel; Clément Jean Pierre Duffau; Lucien Henri Jacques Quennehen; Nicolas Paul Tableau
- Web page: https://patentgrep.com/patent/US11441434B2

## CPC

- F01D 9/04: forming ring or sector
- F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20)
- F01D 25/246: {Fastening of diaphragms or stator-rings}
- F01D 11/005: {Sealing means between non relatively rotating elements}
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2240/11: Shroud seal segments
- F05D 2240/14: Casings or housings protecting or supporting assemblies within
- F05D 2260/30: Retaining components in desired mutual position
- F05D 2260/941: particularly aimed at mechanical or thermal stress reduction
- F05D 2300/6033: Ceramic matrix composites [CMC]
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A turbine ring assembly including ring sectors forming a turbine ring and a ring support structure, each sector having, in a section plane defined by an axial direction and a radial direction of the ring, a first and a second attachment tabs extending in the radial direction, and the structure including a central shell ring from which extend as projections a first and a second radial flanges between which are retained the first and second attachment tabs of each sector. Each sector includes rectilinear seatings mounted on the faces of the first and second attachment tabs in contact, respectively, with the second annular flange and the annular ring-flange and including, along a tangent to the circumferential direction, a variable thickness in the axial direction with a minimum thickness at the first and second ends of the sector and a maximum thickness in a median portion of the rectilinear seating.

## Claims

### Claim 1

A turbine ring assembly comprising:
a plurality of ring sectors forming a turbine ring; and
a ring support structure,
each ring sector having, in a section plane defined by an axial direction and a radial direction of the ring and orthogonal to a circumferential direction of the turbine ring, a part forming an annular base with, in the radial direction of the turbine ring, an internal face defining the internal face of the turbine ring and an external face from which extend as projections a first and a second attachment tabs,
the ring support structure including a central shell ring from which extend as projections a first radial flange and a second radial flange to retain each ring sector, and an annular ring-flange having a free first end seated against the first attachment tab and a second end opposite to the first end and cooperating with the first radial flange,
each ring sector extending between a first circumferential end and a second circumferential end each intended to face another adjacent ring sector in the circumferential direction, and comprising a first rectilinear seating surface positioned on an upstream face of the first attachment tab in contact with the annular ring-flange and a second rectilinear seating surface positioned on a downstream face of the second attachment tab in contact with the second radial flange, each of the first and second rectilinear seating surfaces extending along a tangent to the circumferential direction between the first and second circumferential ends of the ring sector,
wherein a downstream face of the annular-ring flange is only in axial contact with the first rectilinear seating surface, and an upstream face of the second radial flange is only in axial contact with the second rectilinear seating surface, and
wherein the rectilinear seating surfaces of each ring sector have, along said tangent to the circumferential direction, a variable thickness in the axial direction with a minimum thickness at the first and second circumferential ends of the ring sector and a maximum thickness in a median portion of the rectilinear seating surface.

### Claim 2 (depends on 1)

The assembly according to claim 1, wherein the rectilinear seating surfaces are electrical discharge machined surfaces.

### Claim 3 (depends on 1)

The assembly according to claim 1, wherein a gap between said maximum thickness and said minimum thickness of the rectilinear seating surface is comprised between 0.1 and 0.5 mm.

### Claim 4 (depends on 1)

The assembly according to claim 1, wherein the minimum thickness of the rectilinear seating surfaces is less than 0.1 mm.

### Claim 5 (depends on 1)

The assembly according to claim 1, wherein the rectilinear seating surfaces form a strip extending along said tangent to the circumferential direction and along the radial direction, the rectilinear seating surfaces having a height extending along the radial direction comprised between 0.5 and 5 mm.

### Claim 6 (depends on 5)

The assembly according to claim 5, wherein the rectilinear seating surfaces of each ring sector comprise, in the radial direction, a first radial end and a second radial end, and have, along the radial direction, a variable thickness in the axial direction with a minimum thickness at the radial ends of the ring sector and a maximum thickness in a radially median portion of the rectilinear seating.

### Claim 7 (depends on 6)

The assembly according to claim 6, wherein the rectilinear seating surfaces have a first axis of symmetry parallel to the radial direction and a second axis of symmetry parallel to the tangent to the circumferential direction.

### Claim 8 (depends on 1)

The assembly according to claim 1, wherein the ring sector has a pi cross section in the section plane defined by the axial direction and the radial direction, and the assembly comprises, for each ring sector, at least three pins to radially retain the ring sector in position, the first and second attachment tabs of each ring sector each comprising a first end integral with the external face of the annular base, a free second end, at least three lugs for receiving said at least three pins, at least two lugs extending as projections from the second end of one of the first or second attachment tabs in the radial direction of the turbine ring and at least one lug extending as a projection from the second end of the other attachment tab in the radial direction of the turbine ring, each reception lug including an opening for receiving one of the pins.

### Claim 9 (depends on 1)

The assembly according to claim 1, wherein the ring sector has an O cross section in the section plane defined by the axial direction and the radial direction, the first and second attachment tabs each having a first end integral with the external face and a free second end, and each ring sector comprising a third and a fourth attachment tabs each extending, in the axial direction from the turbine ring, between the free second end of the first attachment tab and the free second end of the second attachment tab, each ring sector being fastened to the ring support structure by a fastening screw including a screw head seated against the ring support structure and a thread cooperating with a tapped opening formed in a fastening plate, the fastening plate cooperating with the third and fourth attachment tabs.

### Claim 10 (depends on 1)

A turbomachine comprising a turbine ring assembly according to claim 1.