Safran Aircraft Engines

Snecma

Safran Aircarft Engines

Damien Joseph Cellier

Vincent Paul Gabriel Perrot

Laurent Christophe Francis Villaines

Alicia Lise Julia Dufresne

Philippe Pierre Marcel Marie Pelletrau

Jean-Francois Rios

Jean-Francois Antoine Christian Rios

Daniel Georges Plona

Antoine Robert Alain Brunet

Matthieu Jean Luc Vollebregt

Pierre-Alain Francis Claude Sebrecht

Jean Bertucchi

Vincent Perrot

Ghislain Maxime Romuald Madiot

Irwin Pierre Robert Kernemp

Cédric Michel Claude Chretien

Aurélien Mazzella

Mickael Dias Gomes

Nicolas Jean Fernand Pignier

A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3&#xb0; and 15&#xb0;.

Dimensioning of the skeleton angle of the trailing edge of the arms crossing the by-pass flow of a turbofan

A stage of variable-pitch vanes for a turbine engine includes a plurality of vanes. Each vane has a blade with a first radially internal frusto-conical surface. The cone angle of the first frusto-conical surface is radially flared inwards and is configured to interact with an internal frusto-conical surface of a first frusto-conical bushing. The vane further includes a second radially external frusto-conical surface with cone angle that is radially flared outwards and is configured to interact with an internal frusto-conical surface of a second substantially frusto-conical bushing.

Stage of variable-pitch blades for a turbine engine, turbine engine and associated installation method

A turbomachine part including at least first and second blades, and a platform from which the blades extend, wherein the platform has a non-axisymmetric surface limited by first and second end planes, and defined by at least three construction curves of class CI each representing the value of a radius of the surface on the basis of a position between the lower surface of the first blade and the upper surface of the second blade according to a plane substantially parallel to the end planes, including a first curve that increases in the vicinity of the second blade; a second curve that decreases in the vicinity of the second blade; a third curve having a minimum at the second blade.

Turbomachine part with a non-axisymmetric surface

The main object of the invention is an angular stator sector () for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal () forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).

Angular stator sector for a turbomachine compressor comprising a brush seal

A turbomachine compressor blade of main radial orientation with respect to a main axis of the turbomachine. The blade includes a radially internal root portion, a radially external tip portion, a radially intermediate portion, a curved portion tangentially in a direction, and at least one straight portion on the root portion and/or on the tip portion.

Turbomachine centre blade comprising a curved portion

A turbine engine rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle &#x3bb; and its dihedral angle &#x3bd;, wherein the sweep angle &#x3bb; varies as a function of height H in such a manner that the sweep angle &#x3bb; reaches a maximum at a height H&#x3bb;M, the value H&#x3bb;M lying in the range 5% to 40%, and the sweep angle &#x3bb; increases from 0% to H&#x3bb;M, and wherein the dihedral angle &#x3bd; varies as a function of H, the dihedral angle &#x3bd; being a decreasing function of height H for heights H lying in the range 0% to H&#x3bd;, H&#x3bd;lying in the range 10% to 40%.

Turbine engine rotor blade

A method for modeling at least part of a non-axisymmetric surface () of one portion () of a part (). The portion () is bounded by first and second extremal planes (PS, PR). The method includes processing data from a device (), by: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up the surface, each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S); (b) constructing at least one connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) to keep to the connection curve (CR) near a discontinuity; and (d) restoring, at least part of the obtained surface ().

Method for modeling a non-axisymmetric surface

The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.

Blade and blade dihedral angle

The present invention relates to a method for modelling a part (), the method being characterized in that it comprises implementing, using data processing means () of a piece of equipment (), steps of: (a) parameterizing a curve of class C1 representing the value of a physical quantity characterizing said part () as a function of a position along at least one portion of the part (), the curve being defined by: a. two end points (PCU, PCU) defining the extent of said portion of the part (); b. at least one intermediate point PCU, i&#x2208;[[1,K&#x2212;1]]) located between the two end points (PCU, PCU); c. at least two Bezier curves connected to said intermediate point; the parameterization being carried out using one or more parameters defining said intermediate point; (b) determining optimized values for said parameters of said curve; and (c) returning the determined values to an interface () of said piece of equipment ().

Method for modelling a part, in particular a blading

A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.

Turbine engine blade, in particular for a one-piece bladed disk

An assembly including an airfoil for a bladed wheel together with a platform, the airfoils in association with such platforms forming a bladed wheel. The platform surface presents a circumferential depression between a leading edge of an airfoil at 60% of the airfoil going downstream. A skeleton curve designates a curve plotting variations in a skeleton angle of the airfoil as a function of position along the axis of the wheel; and a linearized skeleton curve designates a curve that provides a straight line connection between points representing the skeleton angle respectively at 10% and at 90% of an axial extent of the airfoil from its leading edge, and, in a vicinity of the platform, a lowered portion of the skeleton curve lying under the linearized skeleton curve extends axially over at least half of an axial extent of the depression.

Airfoil and platform assembly for subsonic flow

An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.

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Paris, France

Damien Joseph Cellier