Safran Aircraft Engines

Snecma

Michael Franck Antoine Schvallinger

Vianney Christophe Marie Maniere

Philippe Jacques Pierre Fessou

Henri-Marie Damevin

Laurent Soulat

Damien Bernard Emeric Guegan

Antoine Claude Baudouin Raoul Marie Secondat De Montesquieu

Sebastien Nicolas Jiugne

Raul Martinez Luque

Aircraft turbine engine including two coaxial annular walls defining between them a main annular duct for the flow of a primary airflow; —a rotor blading extending radially through the first duct; —an annular separator arranged downstream of the rotor blading and configured to divide the primary airflow into two to form the secondary air flows; —first variable guide vanes which are distributed around the shaft and each comprise a leading edge which is located upstream of the separator and trailing edges which are located in the secondary airflows; —and fixed guide vanes which are distributed around the shaft in the external airflow and downstream of the first variable vanes.

Aircraft turbomachine

A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point &#xb1;1 degree.

Turbine engine air guide assembly with improved aerodynamic performance

The proposed invention is an airflow straightening assembly for a turbine engine comprising: &#x2014;a cylindrical platform () centered on an axis (X-X), &#x2014;at least one straightener blade () extending from the platform, &#x2014;a structural unit () extending radially relative to the axis, and &#x2014;a mechanical member () protruding from the platform (), said mechanical member () being one of the group comprising: &#x2014;a radial shaft, &#x2014;an angle transmission box of a radial shaft, &#x2014;an electric, hydraulic or pneumatic connection element, &#x2014;an intermediate gear driving a radial shaft, the straightening assembly further comprising a fairing () or the protruding mechanical member, the fairing having a three-dimensional surface defined by: &#x2014;at least one upstream end point (Ai, A) located axially upstream from the mechanical member () relative to the direction of air flow in the turbine engine, and &#x2014;at least one downstream end point (Ci, C) located axially downstream from the mechanical member, the three-dimensional surface being tangential to the platform at the upstream and downstream end points (Ai, A, Ci, C), and having a larger cross-section measured along an axis (Y-Y) orthogonal to the first, and in which the three-dimensional surface is further defined by two lateral end point (B, B) corresponding to the ends of said larger cross-section respectively on the pressure side and suction side of the structural arm (), the axial positions or said points being separated by at most 0.1 C&#x2014;in which Cis the chord of the straightener blade ().

Airflow straightening assembly having improved aerodynamic performances

The invention relates to a turbine engine air flow guide assembly including: a structural arm (); and a guide vane () on the lower surface of the structural arm, comprising a leading edge (), a trailing edge (), and a camber line (), said vane and arm extending radially about an axis (X-X) of the turbine engine and defining therebetween an air flow channel. The structural arm () comprises: an upstream end () having a guide vane profile () and comprising a leading edge () aligned with that of the vane; and a shoulder () located on the lower surface of the arm, defining a neck in the channel. The assembly is characterized in that the area (A) of the section of the channel at the neck is between 0.7 and 0.9 times the area (A) of the section of the channel at the leading edges.

Growing community of inventors

Moissy-Cramayel, France

Michael Franck Antoine Schvallinger