阅读说明：本技术 具有锯齿轮廓的分流缝翼的涡轮发动机 (Turbine engine with splitter slats having a sawtooth profile ) 是由 费尔南多·盖亚·阿奎莱拉 马修·菲亚克 马修·西蒙·保罗·格鲁伯 于 2019-02-15 设计创作，主要内容包括：本发明涉及一种带前置风扇的涡轮发动机,其包括一种设置有用于在主流和次级流之间分流进气流的前端(16)的环形分流壁(160),所述前端具有前缘；用于引导主流的导叶IGV,以及用于引导次级流的导叶OGV。前端(16)的前缘具有一种显示连续的齿和槽的锯齿轮廓(28)。(The invention relates to a turbine engine with a front fan, comprising an annular flow dividing wall (160) provided with a front end (16) for dividing an intake air flow between a main flow and a secondary flow, the front end having a leading edge; guide vanes IGV for guiding the main flow, and guide vanes OGV for guiding the secondary flow. The leading edge of the leading end (16) has a saw-tooth profile (28) showing continuous teeth and troughs.)

1. Turbine engine with a front fan (14) wherein the air flow can circulate from upstream to downstream, said turbine engine having a general axis (X) about which the front fan can rotate, said front fan generating a wake downstream when rotating, said turbine engine comprising:

-an annular splitter wall (160) having a slat (16) for splitting the airflow downstream of the fan (14) into a primary flow and a secondary flow, the slat (16) having a leading edge,

a first guide vane (IGV 24) for guiding the main flow (Fp),

-a second guide vane (OGV 26) for guiding the secondary flow (Fs),

characterized in that the leading edge of the slat (16) of the annular splitter wall (160) has a sawtooth profile (28), the sawtooth profile (28) having continuous teeth (30) and undulating recesses (32):

-said serrations defining:

along the direction of elongation (L) of the leading edge, a repeating elementary geometry, two equal undulations of two successive elementary geometries (34, 36) along said direction (L), with a distance (λ) between them along said direction, and

-a maximum amplitude h perpendicular to said direction (L) along which said leading edge has a length, and

-the serrations satisfy at least one of the following criteria a), b), c):

a) in the following formula:

determining the size of the maximum amplitude (h) to within 40% according to the following relationship:

wherein:

-u' i, which is the speed of the air flow (38) between the forward fan (14) and the first guide vane (24, IGV) in the direction i,

-r, which is the distance in the k direction between two points in the wake of the front fan (14),

--in the direction of the chord (40) of the profile or parallel to the turbine engineMain axis (X), integral scale of airflow (38) generated by the front fan (14):

b) the distance (λ) complies with the following relation:

e < λ ≦ d-e where d/λ ≠ 1,2,3, …, having:

--e-the width of the air flow (28) generated by the front fan in the wake of one of the blades (140) of the front fan (14), calculated at the point where half of the maximum turbulence kinetic energy K _ max generated in the wake is found; according to the guidelinesEvaluating e to within 40%, and

--da spacing between two circumferentially consecutive blades (140) of the front fan (14),

c) the number of teeth (30), recesses (32), or repeating period of the elementary geometry along the length of the leading edge is equal to the number of first vanes (24, IGV) within 40%.

2. The turbine engine of claim 1, wherein:

-the first guide vane (24, IGV) has an angular position (β) with respect to the general axis (X), and

-surrounding the total axis (X), at least some of the recesses (32) of the sawtooth profile (28) being angularly offset with respect to the angular position (β) of the first guide vane (24, IGV), so that said at least some recesses (32) are angularly interposed between two circumferentially consecutive first guide vanes (24, IGV)).

3. A turbine engine according to any preceding claim, wherein:

-said front fan (14) is adapted to rotate in a predetermined direction (Y) around said main axis (X) so that the air flow (38) downstream of said fan is generally oriented obliquely at an angle (a) with respect to said main axis (X), and

-said teeth (30) are circumferentially inclined around said general axis (X) towards a general direction of inclination (a) of the air flow downstream of said front fan (14), so as to face said air flow in general.

4. A turbine engine according to any preceding claim, wherein:

-the first guide vanes (24, IGV) have a camber line (240) and a leading edge (25), respectively, and

-said teeth (30) circumferentially surround said general axis (X) and are respectively oriented generally in the direction of a tangent (42) to an arc (240) of said first vane (24, IGV) passing through the leading edge (25), said tangent forming a non-zero angle (β) with respect to the general axis (X) direction of the turbine engine.

5. A turbine engine according to any preceding claim, wherein:

-the recess (320) of the sawtooth profile (28) has a bottom, and

-along the direction of the general axis (X), at least some of the bottoms of the recesses (320) belong to a first surface (Y1, Y2), the first surface (Y1, Y2) being positioned more upstream (AM) or downstream (AV) than a second surface (Y '1, Y'2) transversal to the general axis (X), at least some leading edges (25) of the first vanes (24, IGV) belonging to the second surface (Y '1, Y' 2).

6. Turbine engine according to any of the preceding claims, wherein the teeth (30) and the recesses (32) of the sawtooth profile each have a wave shape with rounded or sharp crests (31).

7. The turbine engine according to any one of the preceding claims, characterized in that it is adapted to propel an aircraft (100).