# US 11,306,608 B2 · Self-stiffened casing consisting of a composite material with an organic matrix

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- Number: US 11,306,608 B2
- Document ID: US11306608B2
- Status: Granted
- Kind: B2
- Application number: 15/505,437
- Filed: 2015-08-17
- Published: 2017-09-21
- Granted: 2022-04-19
- Earliest claimed: 2014-08-22
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Sébastien Marin; Quentin Damien Lombart
- Web page: https://patentgrep.com/patent/US11306608B2

## CPC

- F01D 21/045: {special arrangements in stators or in rotors dealing with breaking-off of part of rotor}
- B29C 70/222: {the structure being shaped to form a three dimensional configuration}
- B29C 70/24: oriented in at least three directions forming a three-dimensional [3D] structure
- B29C 70/32: on a rotating mould, former or core
- B29C 70/446: {Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames}
- B29C 70/68: by incorporating or moulding on preformed parts, e.g. inserts or layers {, e.g. foam blocks (mould constructions therefor B29C33/12; joining preformed parts by moulding B29C65/70)}
- D03D 11/00: Double or multi-ply fabrics not otherwise provided for
- D03D 15/267: Glass
- D03D 15/275: Carbon fibres
- D03D 15/283: synthetic polymer-based, e.g. polyamide or polyester fibres (cellulose-based artificial fibres D03D15/225)
- F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045})
- B29B 11/16: comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)}
- B29L 2031/7504: {Turbines}
- D10B 2101/06: Glass
- D10B 2101/08: Ceramic
- D10B 2101/12: Carbon; Pitch
- D10B 2403/0331: with one or more convex or concave portions of limited extension, e.g. domes or pouches
- D10B 2505/02: Reinforcing materials; Prepregs
- D10B 2505/12: Vehicles (D10B2505/08 takes precedence)
- F05D 2240/14: Casings or housings protecting or supporting assemblies within
- F05D 2250/232: conical
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F05D 2300/603: Composites; e.g. fibre-reinforced
- F05D 2300/6033: Ceramic matrix composites [CMC]
- F05D 2300/614: Fibres or filaments
- F05D 2300/615: Filler
- F05D 2300/702: Reinforcement
- 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)
- B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00)
- D03D: WOVEN FABRICS; METHODS OF WEAVING; LOOMS
- B29B: PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- D10B: INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- 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 gas turbine casing made of composite material from fiber reinforcement densified by a matrix. The casing includes at least one stiffener portion extending at a radius greater than the radius of upstream and downstream portions of the casing that are adjacent to the stiffener portion so as to form an annular recess in the inside surface of the casing.

## Claims

### Claim 1

A gas turbine casing made of composite material comprising reinforcement densified by a matrix, said casing being in the form of a body of revolution and wherein said casing comprises a first external flange at its upstream end and a second external flange at its downstream end, a retention zone provided between the first external flange and the second external flange, an air inlet passage, and at least one stiffener portion made of said composite material, the at least one stiffener portion having an annular plateau having an outer radius at a center of an outer surface thereof extending at a radius greater than an outer radius at a center of an outer surface of the retention zone and a radius of upstream and downstream portions of the casing that are adjacent to said at least one stiffener portion so as to form an annular recess in an inside surface of the casing, the casing comprising the retention zone presenting thickness that is greater than a remainder of the casing, said at least one stiffener portion being situated outside of and downstream from the retention zone and adjacent to the downstream end of the casing, the air inlet passage extending between the first external flange and the at least one stiffener portion, wherein the annular plateau has a rectilinear shape that is offset radially towards an outside of the casing relative to the inside surface of the casing, the annular plateau being connected to the upstream and downstream portions via respective annular risers, wherein an angle is formed between each of the annular risers and the upstream and downstream portions, and wherein each angle is greater than 90 degrees and less than 180 degrees, and wherein an entire inside surface of the retention zone that is made of the composite material defines in part the air inlet passage.

### Claim 2 (depends on 1)

The casing according to claim 1, wherein the at least one stiffener portion presents, in axial section, an omega-type shape.

### Claim 3 (depends on 1)

The casing according to claim 1, wherein the annular recess formed by the at least one stiffener portion is filled in with a filler material or structure so as to provide continuity of the inside surface of the casing between the upstream and downstream portions of the casing that are adjacent to the at least one stiffener portion.

### Claim 4 (depends on 1)

The casing according to claim 1, wherein the annular recess formed by the at least one stiffener portion is filled in with an acoustic attenuation material or structure.

### Claim 5 (depends on 1)

The casing according to claim 1, wherein an axial section of the annular plateau and annular risers is rectilinear.

### Claim 6 (depends on 1)

A gas turbine aeroengine having a fan retention casing according to claim 1.

### Claim 7 (depends on 6)

An aircraft including one or more engines according to claim 6.

### Claim 8

A method of fabricating a gas turbine casing out of composite material, the method comprising: weaving a fiber texture in the form of a single-piece strip by three-dimensional or multilayer weaving; shaping said fiber texture by winding it on a support tooling to form a fiber reinforcement; and densifying the fiber reinforcement with a matrix to obtain the casing,
wherein said casing comprises a first external flange at its upstream end and a second external flange at its downstream end, a retention zone provided between the first external flange and the second external flange, an air inlet passage, and at least one stiffener portion made of said composite material, the at least one stiffener portion having an annular plateau having an outer radius at a center of an outer surface thereof extending at a radius greater than an outer radius at a center of an outer surface of the retention zone and a radius of upstream and downstream portions of the casing that are adjacent to said at least one stiffener portion so as to form, an annular recess in an inside surface of the casing the casing comprising the retention zone presenting thickness that is greater than a remainder of the casing, said at least one stiffener portion being situated outside of and downstream from the retention zone and adjacent to the downstream end of the casing, the air inlet passage extending between the first external flange and the at least one stiffener portion, wherein the annular plateau has a rectilinear shape that is offset radially towards an outside of the casing relative to the inside surface of the casing, the annular plateau being connected to the upstream and downstream portions via respective annular risers, wherein an angle is formed between each of the annular risers and the upstream and downstream portions, and wherein each angle is greater than 90 degrees and less than 180 degrees, and wherein an entire inside surface of the retention zone that is made of the composite material defines in part the air inlet passage.

### Claim 9 (depends on 8)

The method according to claim 8, wherein the at least one stiffener portion presents, in axial section, an omega-type shape.

### Claim 10 (depends on 8)

The method according to claim 8, wherein the annular recess formed by the at least one stiffener portion is filled in with a filler material or structure so as to provide continuity of the inside surface of the casing between the upstream and downstream portions of the casing that are adjacent to the at least one stiffener portion.

### Claim 11 (depends on 8)

The method according to claim 8, wherein the annular recess formed by the at least one stiffener portion is filled in with an acoustic attenuation material or structure.