Turbine engine with a flow splitter having a profile with inclined serrations

Patent metadata

Field	Value
Publication number	US-11629664-B2
Application number	US-201916969630-A
Country	US
Kind code	B2
Filing date	Feb 15, 2019
Priority date	Feb 16, 2018
Publication date	Apr 18, 2023
Grant date	Apr 18, 2023

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.

First claim

The invention claimed is:

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 arranged downstream of the front fan and separating the air flow into a primary flow and a secondary flow;
first guide vanes for guiding the primary flow in the turbomachine;
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
wherein at least one of the annular airflow dividing wall, the first guide vanes and the second guide vanes comprise a profiled structure having a serrated leading edge including a succession of teeth and depressions, such that, along the leading edge, from a first location to a second location, the teeth of the serrated leading edge are individually inclined towards the second location,
wherein the individual inclinations of the teeth of the serrated leading edge vary according to an engine speed of the turbomachine, and

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 the front fan 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 serrated 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.

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

3. 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.

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

5. The aircraft comprising at least one turbomachine according to claim 1 .

6. The turbomachine according to claim 1 , wherein the incline at the apex of the tooth is closer to a bottom of one adjacent depression than the other adjacent depression.

7. The turbomachine according to claim 1 , wherein the first guide vanes are inlet guide vanes and the second guide vanes are outlet guide vanes.

Assignees

• Safran Aircraft Engines

Inventors

• Gea Aguilera Fernando
• Fiack Matthieu
• Gruber Mathieu Simon Paul

Classifications

• F02K1/386 Primary

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title

• F15D1/004

  oriented essentially parallel to the direction of flow · CPC title

• F02C7/042

  having variable geometry · CPC title

• F05D2250/183

  zigzag · CPC title

• F02K1/48

  Corrugated nozzles · CPC title