# US 12,000,300 B2 · Exhaust cone for a turbomachine

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- Number: US 12,000,300 B2
- Document ID: US12000300B2
- Status: Granted
- Kind: B2
- Application number: 18/034,659
- Filed: 2021-11-03
- Published: 2023-12-07
- Granted: 2024-06-04
- Earliest claimed: 2020-11-05
- Assignees: Safran Nacelles
- Applicants: Safran Nacelles
- Inventors: Jean-Philippe Joret; Vincent Devanlay; Marine Ollivier; Guillaume Levieux
- Web page: https://patentgrep.com/patent/US12000300B2

## CPC

- 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})
- F02K 1/04: Mounting of an exhaust cone in the jet pipe
- F02K 1/80: Couplings or connections
- F02K 1/805: {Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps}
- F05D 2260/30: Retaining components in desired mutual position
- 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)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- 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

The invention relates to an assembly for a turbomachine, comprising an exhaust cone (18) and an exhaust case having an annular inner shell, the exhaust cone (18) and the exhaust case extending about an axis (X), the exhaust cone (18) having a radially outer skin (31) extending in the projection of said inner shell and a radially inner skin (30) defining a chamber (32) with the outer skin (31), the upstream end (33) of the cone (18) being fastened to the inner shell (19) via connecting lugs (39), the assembly comprising an annular fairing (29) located radially outside said lugs (39) and extending axially between the inner shell (19) of the exhaust case (17) and the outer skin (31) of the exhaust cone (18), said fairing (29) extending in the projection of said inner shell (19) and of the outer skin (31), the assembly being characterized in that the fairing (29) is segmented and consists of multiple angular segments (42) arranged circumferentially end to end.

## Claims

### Claim 1

An assembly for a turbomachine (1) comprising:
an exhaust cone (18) and an exhaust case (17) including an annular inner shell (19), the exhaust cone (18) and the exhaust case (17) extending about an axis (X),
the exhaust cone (18) including a radially outer skin (31) extending in the projection of said inner shell (19) and a radially inner skin (30) defining a chamber (32) with the outer skin (31), an upstream end (33) of the cone (18) being fastened to the inner shell (19) via connecting lugs (39),
the assembly including an annular fairing (29) located radially outside said lugs (39) and extending axially between the inner shell (19) of the exhaust case (17) and the outer skin (31) of the exhaust cone (18), said fairing (29) extending in the projection of said inner shell (19) and of the outer skin (31),
wherein the fairing (29) is segmented and comprises several angular segments (42) arranged circumferentially end to end.

### Claim 2 (depends on 1)

The assembly according to claim 1, wherein the fairing (29) includes an upstream end fastened to the inner shell (19) of the exhaust case (17) or to a flange (36) fastened to said inner shell (17), and an opposite downstream zone supported by a support member (48), said support member (48) extending radially between said downstream zone of the fairing (29) and the cone (18).

### Claim 3 (depends on 2)

The assembly according to claim 2, wherein the assembly includes an annular seal (53) extending radially between the downstream zone of the fairing (29) and the cone (18).

### Claim 4 (depends on 3)

The assembly according to claim 3, wherein the annular seal (53) includes a fastening portion (54) to the fairing (29) or to the cone (18), and a median portion (56) in sheet form, extending obliquely in relation to a radial direction.

### Claim 5 (depends on 4)

The assembly according to claim 4, wherein said median portion (56) extends from downstream to upstream and radially from the outside inward.

### Claim 6 (depends on 4)

The assembly according to claim 4, wherein said median portion (56) extends from upstream to downstream and radially from the outside inward.

### Claim 7 (depends on 3)

The assembly according to claim 3, wherein the annular seal (53) includes a zone of hollow rounded cross-section (60).

### Claim 8 (depends on 1)

The assembly according to claim 1, wherein circumferential ends of two adjacent fairing angular segments (42) overlap circumferentially (42a).

### Claim 9 (depends on 1)

The assembly according to claim 1, wherein the adjacent angular segments (42) are fastened to one another or to the inner shell (19) of the exhaust case (17) via removable fastening means (46, 47).

### Claim 10 (depends on 1)

A turbomachine (1) including at least one assembly according to claim 1.

### Claim 11 (depends on 3)

The assembly of claim 3, wherein the annular seal (53) is segmented and circumferential ends of two adjacent fairing segments (42) overlap circumferentially (42a).

### Claim 12 (depends on 3)

The assembly according to claim 3, wherein the adjacent angular segments (42) are fastened to one another or to the inner shell (19) of the exhaust case (17) via removable fastening means (46, 47).