# US 2020/0400069 A1 · Turbine engine with a flow splitter having a profile with inclined serrations

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 2020/0400069 A1
- Document ID: US20200400069A1
- Status: Published application
- Kind: A1
- Application number: 16/969,630
- Filed: 2019-02-15
- Published: 2020-12-24
- Earliest claimed: 2018-02-16
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Fernando Gea Aguilera; Matthieu Fiack; Mathieu Simon Paul Gruber
- Web page: https://patentgrep.com/patent/US20200400069A1

## CPC

- F02K 1/386: {mixing devices in the jet pipe, e.g. for mixing primary and secondary flow}
- B64C 3/16: Frontal aspect
- F02C 7/042: having variable geometry
- F02C 7/045: having provisions for noise suppression
- F02K 1/48: Corrugated nozzles
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- F05D 2250/183: zigzag
- F05D 2250/184: sinusoidal
- F05D 2250/61: corrugated
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F15D 1/0035: {in the form of riblets}
- F15D 1/004: {oriented essentially parallel to the direction of flow}
- 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)
- B64C: AEROPLANES; HELICOPTERS
- 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
- F15D: FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS

## Abstract

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

## Claims

### Claim 1

A turbomachine for an aircraft, the turbomachine comprising:
a general axis about which rotating parts of the turbomachine rotate, the rotating parts including blades of a front fan;
an annular airflow dividing wall for an air flow, the annular airflow dividing wall having a leading edge and arranged downstream of the front fan, the annular airflow dividing wall separating the air flow into a primary flow and a secondary flow;
first guide vanes for guiding the primary flow in the turbomachine, each first guide vane having a leading edge;
second guide vanes for guiding the secondary flow in the turbomachine, each second guide vane having a leading edge, the first guide vanes for guiding the primary flow and the second guide vanes guiding the secondary flow being connected to the annular airflow dividing wall; and
a serrated leading edge profile including a succession of teeth and depressions, and such that, along the leading edge, from a first location to a second location, the teeth of the serrated leading edge profile are individually inclined towards the second location, wherein:
a) the teeth are, circumferentially around said general axis and downstream of the front fan, individually inclined towards a generally oblique orientation of the air flow with respect to said general axis, to face it generally, or
b) on the annular airflow dividing wall where they are present, the teeth are oriented in the direction of a camber line of the first guide vanes at the leading edge thereof, or
c) about said general axis, at least some of said depressions of the serrated leading edge profile are angularly offset with respect to the angular position of the first guide vanes, so that said at least some of the depressions are angularly interposed between two circumferentially successive first guide vanes.

### Claim 2 (depends on 1)

The turbomachine of claim 1, wherein the teeth and depressions of the serrated leading edge profile are individually wavy in shape, with rounded or more sharp tops.

### Claim 3 (depends on 1)

The turbomachine of claim 1, wherein the teeth and depressions of the serrated leading edge profile individually have a shape with locally rectilinear side walls.

### Claim 4 (depends on 2)

The turbomachine of claim 2, wherein the wavy shape is periodic and has, in at least some of the periods, teeth which are different from one another and/or depressions which are different from one another.

### Claim 5 (depends on 1)

The turbomachine of claim 1, wherein the individual inclinations of the teeth of the serrated leading edge profile vary according to an engine speed of the turbomachine.

### Claim 6 (depends on 1)

An aircraft comprising
at least one turbomachine according to claim 1.