# US 12,110,840 B2 · Turbine engine separate flow mixer with lobes

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- Number: US 12,110,840 B2
- Document ID: US12110840B2
- Status: Granted
- Kind: B2
- Application number: 17/608,292
- Filed: 2020-04-03
- Published: 2022-07-07
- Granted: 2024-10-08
- Earliest claimed: 2019-05-03
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Cyrille Telman; Pierre Vincent; Olivier Arnaud Fabien Lambert; Simon José Pierre Amoedo
- Web page: https://patentgrep.com/patent/US12110840B2

## CPC

- F02K 1/386: {mixing devices in the jet pipe, e.g. for mixing primary and secondary flow}
- F02K 1/48: Corrugated nozzles
- F05D 2250/184: sinusoidal
- F05D 2250/611: undulated
- F05D 2300/50212: dissimilar
- 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

## Abstract

The invention relates to a turbine engine separate flow mixer centered on a longitudinal axis, comprising an exhaust housing, a shroud directly connected to the exhaust housing and intended to mix the flows originating in the turbine engine, said shroud comprising a metal sheet formed by a succession of first and second longitudinal strips distributed circumferentially around the longitudinal axis of the mixer by circumferentially placing the second strips on either side of the first strips, the first and second strips being configured to form the shroud when at rest and grooves in the shroud when operating, the grooves being defined by an alternation of internal lobes and of external lobes.

## Claims

### Claim 1

A turbine engine separate flow mixer centered on a longitudinal axis, comprising an exhaust housing, a shroud directly connected to the exhaust housing and intended to mix flows originating in a turbine engine, wherein said shroud comprises a metal sheet formed by a succession of first longitudinal strips and second longitudinal strips distributed circumferentially around the longitudinal axis of the turbine engine separate flow mixer, the shroud having a first shape when at rest or in a cold configuration and a second shape different from the first shape when operating or in a hot configuration, and the first longitudinal strips and second longitudinal strips being configured to form the shroud when at rest and grooves in the shroud when operating, the grooves being defined by an alternation of internal lobes and of external lobes the first longitudinal strips and the second longitudinal strips having different thermal dilations when the shroud is operating and, wherein the exhaust housing comprises clevises protruding radially outward from the exhaust housing to fasten the exhaust housing to a pylon, an annular hub centered on the longitudinal axis, and coaxial with an external shroud of the exhaust housing, and wherein a plurality of arms connect the annular hub to the external shroud of the exhaust housing, wherein the annular hub is fully enclosed by the exhaust housing and is upstream of the shroud.

### Claim 2 (depends on 1)

The turbine engine separate flow mixer according to claim 1, wherein the first longitudinal strips and the second longitudinal strips of the shroud are made of different materials.

### Claim 3 (depends on 1)

The turbine engine separate flow mixer according to claim 1, wherein the shroud is connected to the external shroud of the exhaust housing by brazing.

### Claim 4 (depends on 1)

The turbine engine separate flow mixer according to claim 1, wherein the shroud is connected to the external shroud of the exhaust housing by welding.

### Claim 5 (depends on 1)

The turbine engine separate flow mixer according to claim 1, wherein the turbine engine separate flow mixer is configured to obtain, when the turbine engine separate flow mixer is operating, a temperature difference of more than 100° C. between the first longitudinal and the second longitudinal strips.

### Claim 6 (depends on 1)

The turbine engine separate flow mixer according to claim 1, wherein the turbine engine separate flow mixer is configured to obtain, when the turbine engine separate flow mixer is operating, a temperature difference of more than 200° C. between the first longitudinal strips and the second longitudinal strips.

### Claim 7 (depends on 1)

The turbine engine separate flow mixer according to claim 1, wherein the first longitudinal strips and second longitudinal strips of the shroud are made of an aluminum-based material.

### Claim 8 (depends on 1)

The turbine engine separate flow mixer according to claim 1, wherein each arm of the exhaust housing having a leading edge and a trailing edge, the trailing edge being axially aligned with a junction between the first longitudinal strips and the second longitudinal strips of the shroud.

### Claim 9 (depends on 1)

A turbine engine comprising a separate flow nozzle which is equipped with the turbine engine separate flow mixer according to claim 1.

### Claim 10 (depends on 5)

The turbine engine separate flow mixer according to claim 5, wherein the plurality of arms of the exhaust housing are configured to obtain, when the turbine engine separate flow mixer is operating, the temperature difference of more than 100° C. between the first longitudinal strips and the second longitudinal strips.

### Claim 11 (depends on 6)

The turbine engine separate flow mixer according to claim 6, wherein the plurality of arms of the exhaust housing are configured to obtain, when the turbine engine separate flow mixer is operating, the temperature difference of more than 200° C. between the first longitudinal strips and the second longitudinal strips.