# US 11,078,804 B2 · Turbine shroud assembly

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- Number: US 11,078,804 B2
- Document ID: US11078804B2
- Status: Granted
- Kind: B2
- Application number: 16/960,726
- Filed: 2018-12-24
- Published: 2020-11-12
- Granted: 2021-08-03
- Earliest claimed: 2018-01-09
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Nicolas Paul Tableau; Sébastien Serge Francis Congratel; Antoine Claude Michel Etienne Danis; Clément Jean Pierre Duffau; Clément Jarrossay
- Web page: https://patentgrep.com/patent/US11078804B2

## CPC

- 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}
- F05D 2230/642: using maintaining alignment while permitting differential dilatation
- F05D 2240/11: Shroud seal segments
- F05D 2250/75: given by its similarity to a letter, e.g. T-shaped
- F05D 2260/36: by a form fit connection, e.g. by interlocking
- F05D 2260/941: particularly aimed at mechanical or thermal stress reduction
- F05D 2300/50212: dissimilar
- F05D 2300/6033: Ceramic matrix composites [CMC]
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- 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
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each sector having, along a cutting plane defined by an axial direction and a radial direction of the ring, a portion forming an annular base with, in the radial direction, an inner face and an outer face from which a first and a second lug protrude, the structure including a shroud from which protrude a first and a second radial clamp from which the first and second lugs are held. The turbine ring includes an annular flange having a first portion bearing against the first lug, and a second portion removably fixed to the first radial clamp, the first portion including radial slits open on a free end of the annular flange and delimiting first-portion sectors.

## Claims

### Claim 1

A turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure, each ring sector having, along a cutting plane defined by an axial direction and a radial direction of the turbine ring, a portion forming an annular base with, in the radial direction of the turbine ring, a radially inner face defining the inner face of the turbine ring and a radially outer face from which a first and a second attachment lug protrude, the ring support structure including a central shroud from which protrude a first and a second radial clamp from which the first and second attachment lugs of each ring sector are held,
the turbine ring assembly further comprising a first annular flange disposed upstream of the turbine ring and of the first radial clamp relative to the direction of an air stream intended to pass through the turbine ring assembly and having in the radial direction a first free end, a second end opposite to the first end, a first portion extending from the first end, and a second portion extending between the first portion and the second end,
the first portion of the first flange bearing against the first attachment lug, the second portion of the first flange being fixed to the first radial clamp of the central shroud of the ring support structure, and
wherein the first portion of the first annular flange comprising a plurality of radial slits which lead to the first end of the first annular flange and which delimit first-portion sectors of the first annular flange, the radial slits passing through the axial direction,
the first annular flange comprising, for each radial slit, a discharge orifice, and each radial slit leads, on the one hand, to the first end of the first annular flange and, on the other hand, into the discharge orifice.

### Claim 2 (depends on 1)

The assembly according to claim 1, wherein the discharge orifices are circular orifices having a diameter comprised between 0.5 mm and 8 mm.

### Claim 3 (depends on 1)

The assembly according to claim 1, further comprising an inter-sector seal for each radial slit of the first annular flange, each radial slit having a first and a second surface parallel to each other in the radial direction and in the axial direction, the first surface comprising a first groove and the second surface comprising a second groove extending symmetrically to the first groove relative to a plane extending in the axial direction and in the radial direction along the radial slit, a first portion of the inter-sector seal being inserted in the first groove and a second portion of the inter-sector seal being inserted in the second groove.

### Claim 4 (depends on 1)

The assembly according to claim 1, further comprising a second annular flange disposed upstream of the first annular flange relative to the direction of the air stream intended to pass through the turbine ring assembly and having a first free end and a second end opposite to the first end, the first end of the second annular flange being distant from the first end of the first annular flange in the axial direction, the second ends of the first and second annular flanges being removably fixed to the first radial clamp of the central shroud of the ring support structure.

### Claim 5 (depends on 4)

The assembly according to claim 4, wherein the first flange has a thickness in the axial direction smaller than the thickness in the axial direction of the second flange.

### Claim 6 (depends on 4)

The assembly according to claim 4, wherein the second radial clamp of the ring support structure has a first free end and a second end secured to the central shroud of the ring support structure, the first end of the second radial clamp being in contact with the second attachment lug of the turbine ring and having a thickness in the axial direction greater than the thickness of the first end of the first annular flange.

### Claim 7 (depends on 1)

The assembly according to claim 1, wherein the ring sector has a section in πaccording to the cutting plane defined by the axial direction and the radial direction, and the assembly comprises, for each ring sector, at least three pins for radially holding the ring sector in position, the first and second attachment lugs of each ring sector each comprising a first end secured to the outer face of the annular base, a second free end, at least three ears for receiving said at least three pins, at least two ears protruding from the second end of one of the first or second attachment lugs in the radial direction of the turbine ring and at least one ear protruding from the second end of the other attachment lug in the radial direction of the turbine ring, each receiving ear including an orifice for receiving one of the pins.

### Claim 8 (depends on 1)

The assembly according to claim 1, wherein the ring sector has a K-section along the cutting plane defined by the axial direction and the radial direction, the first and second attachment lugs having an S shape.

### Claim 9 (depends on 1)

The assembly according to claim 1, wherein the ring sector has an O-section along the cutting plane defined by the axial direction and the radial direction, the first and second attachment lugs each having a first end secured to the outer face and a second free end, and each ring sector comprising a third and a fourth attachment lug each extending, in the axial direction of the turbine ring, between a second end of the first attachment lug and a second end of the second attachment lug, each ring sector being fixed to the ring support structure by a fixing screw including a screw head bearing against the ring support structure and a thread cooperating with a tapping made in a fixing plate, the fixing plate cooperating with the third and fourth attachment lugs.

### Claim 10 (depends on 1)

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

### Claim 11 (depends on 2)

The assembly according to claim 2, wherein the circular orifices have a diameter comprised between 1 mm and 5 mm.