# US 11,898,517 B2 · Turbofan engine comprising an outlet cone cooled by its secondary flow

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- Number: US 11,898,517 B2
- Document ID: US11898517B2
- Status: Granted
- Kind: B2
- Application number: 17/297,079
- Filed: 2019-11-21
- Published: 2022-01-27
- Granted: 2024-02-13
- Earliest claimed: 2018-11-27
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Guillaume Claude Robert Belmon; Cédric Zaccardi
- Web page: https://patentgrep.com/patent/US11898517B2

## CPC

- F02K 1/822: {Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors}
- F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)}
- F01D 25/125: {of bearings}
- F01D 25/30: Exhaust heads, chambers, or the like
- F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M)
- F02K 1/04: Mounting of an exhaust cone in the jet pipe
- F01D 25/14: Casings modified therefor (double casings F01D25/26)
- F01D 25/26: Double casings; Measures against temperature strain in casings
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2250/232: conical
- F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- 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)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- 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

A turbofan engine including an exhaust casing traversed by a primary flow and surrounded by a secondary flow and an outlet cone carried by this exhaust casing, the exhaust casing and the outlet cone together defining an internal space. The exhaust casing includes a hollow radial arm traversing the primary flow in order to convey part of the secondary flow so as to form a cooling flow for supplying the internal space, and the outlet cone is terminated by an opening for discharging the cooling flow.

## Claims

### Claim 1

A turbofan engine including
an exhaust casing through which passes a primary flow and which is surrounded by a secondary flow, both the primary flow and the secondary flow circulating from upstream to downstream along a central longitudinal axis of the turbofan engine during operation, and
an outlet cone having an upstream end carried by this exhaust casing, the outlet cone delimiting an inner space,
wherein the exhaust casing includes a hollow radial arm crossing the primary flow which conveys part of the secondary flow in order to form a cooling flow to cool down one or several component(s) located in the inner space,
wherein the outlet cone terminates in an outlet for discharging the cooling flow,
wherein the outlet cone is formed by a main wall and includes an inner lining wall which runs along the main wall while being spaced therefrom so as to delimit, together with this main wall along most of an inner face of the main wall, an inter-wall space, and
wherein a portion of the cooling flow passes through the inter-wall space before being discharged by the outlet, and
wherein the inner lining wall comprises an extension into the hollow radial arm to collect the portion of the cooling flow that passes through the inter-wall space.

### Claim 2 (depends on 1)

The turbofan engine according to claim 1, wherein the hollow radial arm terminates in a scoop soaking in the secondary flow to promote sampling of the cooling flow from the secondary flow.

### Claim 3 (depends on 1)

The turbofan engine according to claim 1, wherein the outlet is formed by a cylindrical extension of the outlet cone.

### Claim 4 (depends on 1)

The turbofan engine according to claim 1, wherein the outlet is formed by a cylindrical extension of the main wall and by a cylindrical extension of the inner lining wall which extends inside the cylindrical extension of the main wall.

### Claim 5 (depends on 1)

The turbofan engine according to claim 1, comprising a low-pressure turbine driving a central shaft via an epicyclic reduction gear, and wherein this the one or several component(s) located in the inner space comprises this epicyclic reduction gear.

### Claim 6 (depends on 1)

The turbofan engine according to claim 1, comprising a central shaft and a bearing for holding this central shaft, wherein the one or several component(s) located in the inner space comprises said bearing.

### Claim 7 (depends on 1)

The turbofan engine according to claim 1, wherein said outlet is an opening formed at an end of the outlet cone centered on the central longitudinal axis.