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

Patent metadata

Field	Value
Publication number	US-11913405-B2
Application number	US-202318183232-A
Country	US
Kind code	B2
Filing date	Mar 14, 2023
Priority date	Feb 16, 2018
Publication date	Feb 27, 2024
Grant date	Feb 27, 2024

Abstract

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. 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;
inlet guide vanes for guiding the primary flow in the turbomachine, each inlet guide vane having an inlet guide vane leading edge;
outlet guide vanes for guiding the secondary flow in the turbomachine, each outlet guide vane having a leading edge, the inlet guide vanes for guiding the primary flow and the outlet 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 inlet guide vanes and the outlet guide vanes comprise a profiled structure having a serrated leading edge including a succession of teeth and depressions, such that, along the serrated 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:
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 generally face the air flow, 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 inlet 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 inlet guide vanes, so that said at least some of the depressions are angularly interposed between two circumferentially successive inlet guide vanes, and wherein the teeth have apexes located upstream the inlet guide vane leading edge.

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

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 turbomachine of claim 1 , wherein the individual inclinations of the teeth of the serrated leading edge are defined according to an engine speed of the turbomachine.

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

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

8. 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 being arranged downstream of the front fan and separating the air flow into a primary flow and a secondary flow;
inlet guide vanes for guiding the primary flow in the turbomachine, each inlet guide vane having an leading edge;
outlet guide vanes for guiding the secondary flow in the turbomachine, each outlet guide vane having a leading edge; and
wherein at least one of the inlet guide vane and the outlet guide vane comprise a profiled structure having a serrated leading edge including a succession of teeth and depressions, such that, along the serrated 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 teeth have apexes located upstream the leading edge of said at least one of the inlet guide vane and the outlet guide vane, 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 generally face the air flow, 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 inlet 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 are angularly offset with respect to the angular position of the inlet guide vanes, so that said at least some of the depressions are angularly interposed between two circumferentially successive inlet guide vanes.

9. The turbomachine of claim 8 , wherein the individual inclinations of the teeth of the serrated leading edge are defined according to an engine speed of the turbomachine.

10. The turbomachine according to claim 8 , wherein the incline at a respective apex of a tooth is closer to a bottom of one adjacent depression than the other adjacent depression.

11. The aircraft comprising at least one turbomachine according to claim 8 .

12. The turbomachine of claim 11 , wherein the individual inclinations of the teeth of the serrated leading edge are defined according to an engine speed of the turbomachine.

13. The turbomachine according to claim 11 , wherein the incline at a respective apex of a tooth is closer to a bottom of one adjacent depression than the other adjacent depression.

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

• F02C7/042

  having variable geometry · CPC title

• F02C7/045

  having provisions for noise suppression · CPC title

• F02K1/48

  Corrugated nozzles · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title