# US 10,371,009 B2 · Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners

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- Number: US 10,371,009 B2
- Document ID: US10371009B2
- Status: Granted
- Kind: B2
- Application number: 15/113,543
- Filed: 2015-01-20
- Published: 2017-02-02
- Granted: 2019-08-06
- Earliest claimed: 2014-01-23
- Assignees: Safran Aircraft Engines
- Applicants: Snecma
- Inventors: Mario Cesar De Sousa; Benoit Argemiro Matthieu Debray; Paul Moreau; Frederic Noel
- Web page: https://patentgrep.com/patent/US10371009B2

## CPC

- F01D 25/162: {Bearing supports}
- B64D 27/402: {comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant}
- F01D 25/243: {Flange connections; Bolting arrangements (F01D25/265 takes precedence)}
- F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing
- F05D 2220/32: in gas turbines
- F05D 2240/90: Mounting on supporting structures or systems
- F05D 2250/75: given by its similarity to a letter, e.g. T-shaped
- F05D 2260/30: Retaining components in desired mutual position
- F05D 2260/31: Retaining bolts or nuts
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

The invention relates to a turbomachine casing (1) comprising: a hub (2), an outer shroud (3), and yokes (11) projecting from the outer shroud (3), for attaching the housing (1), characterized in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing each other, and comprising a central part (18) and side arms (19) projecting from the central part (18).

## Claims

### Claim 1

A turbine engine casing comprising:
a hub,
an outer shell ring, and
clevises protruding from the outer shell ring, for attaching the casing,
wherein the turbine engine casing further comprises at least one stiffener extending between pairs of clevises facing each other, said at least one stiffener having the general shape of an H, and
comprising a central part and lateral arms protruding from the central part.

### Claim 2 (depends on 1)

The casing according to claim 1, wherein the stiffener comprises ends that are integral with the clevises.

### Claim 3 (depends on 1)

The casing according to claim 1, wherein the stiffener comprises ends that are attached to the clevises via attachment elements.

### Claim 4 (depends on 1)

The casing according to claim 1, wherein the lateral arms have a section wider in their center than at their ends.

### Claim 5 (depends on 1)

The casing according to claim 1, wherein the lateral arms have a section narrower in their center than at their ends.

### Claim 6 (depends on 1)

The casing according to claim 1, wherein the lateral arms have a section of substantially constant width.

### Claim 7 (depends on 1)

The casing according to claim 1, said casing being an exhaust casing of a turbine engine and comprising a plurality of structural arms positioned circumferentially between the hub and the outer shell ring, the clevises being positioned in alignment with the structural arms.

### Claim 8 (depends on 1)

A turbine engine comprising:
a casing according to claim 1,
link rods attached on the one hand to the clevises of the casing via attachment elements,
and on the other hand to a support of the turbine engine,
the stiffener being configured to assume the forces applied by the link rods to the casing.