# US 2019/0376451 A1 · Primary nozzle of a turbomachine primary exhaust duct

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- Number: US 2019/0376451 A1
- Document ID: US20190376451A1
- Status: Published application
- Kind: A1
- Application number: 16/419,798
- Filed: 2019-05-22
- Published: 2019-12-12
- Earliest claimed: 2018-06-11
- Applicants: Airbus Operations SAS
- Inventors: Thierry GACHES; Lionel CZAPLA; Bastian SABATHIER
- Web page: https://patentgrep.com/patent/US20190376451A1

## CPC

- F02C 7/24: Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00)
- F02K 1/827: {Sound absorbing structures or liners}
- F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)}
- F05D 2230/30: with deposition of material
- F05D 2250/283: honeycomb
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- 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)
- 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)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A primary nozzle of a turbomachine primary exhaust duct, the primary nozzle comprising a microperforated first wall facing towards the inside and which widens from the front as far as an intermediate zone, a one-piece second wall comprising a microperforated internal part which extends rearward and in the continuity of the first wall from the intermediate zone and narrows from the intermediate zone rearwards, an external part which faces towards the outside around the internal part, and a fold connecting the rear parts of the internal part and of the external part, where the first wall and the internal part are fixed to one another, and a noise attenuating element fixed to the first wall and to the internal part.

## Claims

### Claim 1

A primary nozzle of a turbomachine primary exhaust duct, the primary nozzle comprising:
a microperforated first wall, facing towards an inside of the primary nozzle, and which widens from a front as far as an intermediate zone,
a one-piece second wall, comprising
a microperforated internal part, which extends rearwards from the first wall and in continuity therewith from the intermediate zone, and narrows from the intermediate zone rearwards,
an external part which faces towards an outside of the primary nozzle around the internal part, and
a fold connecting rear parts of the internal part and of the external part, where the first wall and the internal part are fixed to one another, and
a noise attenuating element fixed to the first wall and to the internal part, and arranged between the first wall and the external part and between the internal part and the external part.

### Claim 2 (depends on 1)

The primary nozzle according to claim 1, wherein a front end of the internal part has a discontinuity towards the outside and wherein a depth of the discontinuity is sized to house a rear end of the first wall so that a face of the first wall that faces towards the inside of the primary nozzle lies flush with a face of the internal part that faces towards the inside of the primary nozzle.

### Claim 3 (depends on 1)

The primary nozzle according to claim 1, wherein the external part is made up of a rear external part which extends from the fold forward as far as a junction zone, and a front external part which extends from the junction zone to the front, and wherein a front end of the rear external part and a rear end of the front external part are fixed to one another.

### Claim 4 (depends on 3)

The primary nozzle according to claim 3, wherein the front end of the rear external part has a discontinuity towards the inside and wherein a depth of the discontinuity is able to house the rear end of the front external part so that a face of the rear external part at the discontinuity that faces towards the outside of the primary nozzle lies flush with a face of the front external part that faces towards the inside of the primary nozzle.

### Claim 5 (depends on 1)

A turbomachine comprising a primary exhaust duct delimited on the outside by a primary nozzle according to claim 1 and on the inside by an internal structure.

### Claim 6 (depends on 5)

An aircraft comprising at least one turbomachine according to claim 5.