Safran Aircraft Engines

Guillaume Pascal Jean-Charles Gondre

Thomas Alain De Gaillard

Stéphane Roger Mahias

Nicolas Pierre Alain Edme De Cacqueray-Valmenier

Sadim Dieudonne

Clément Pierre Postec

Olivier Bazot

Pierre Jean Faivre D'arcier

Charles-Henri Claude Jacky Sullet

Julien Paul Schneider-Die-Gross

Mickaël Cavarec

Nicolas Paul Tableau

Paul Antoine Foresto

Teddy Fixy

Matthieu Pierre Michel Dubosc

Guillaume Claude Robert Belmon

Mickael Cavarec

Morgane Astrid Leger

Romuald Bernard Mauvais

Pierre-Antoine Gérard Joseph Barbier

Carole Onja Rakotoarisoa

A blade () of a fan (), made of composite material, of a turbomachine. On a portion () of the blade () which extends from a lower limit () located at a predetermined distance (d) from the shank () of the blade equal to at least 80% of the predetermined height (h) to the top () of the blade (), a dihedral angle (D) measured at least one predefined point on the chord of the blade (), located on the chord of the blade () at the upstream end () of the nose () of the shield (), is greater than or equal to −3° and less than or equal to 0°.

Fan blade with zero tip dihedral at the head

The invention relates to a fan blade () of a turbomachine () comprising a structure () made of composite material having, within the root () and/or the stilt () of the blade, a first layer () comprising the lower face () and having a first thickness (E) of between 10% and 25% of the total thickness (E), a second layer () comprising the suction face () and having a second thickness (E) of between 10% and 25% of the total thickness (E), and a central layer () extending between the first layer () and the second layer (), the shortening of the warp strands () in the first and second layers () being greater than the shortening of the warp strands () in the central layer ().

Differentiated shortening of strands of the fibrous reinforcement of a fan blade

The invention relates to a blade comprising a shield () attached to the upstream end of the body of the blade, the shield () comprising an upstream end forming a leading edge of the blade, the shield () further comprising a nose () upstream from which the leading edge is located, an pressure-face fin and an suction-face fin laterally attached on the blade, the fins extending from the nose, the blade comprising a defrosting air passage duct () arranged inside the nose and extending radially inside the nose, the duct () having an inner end () emerging opposite the root () and a radially external end emerging from the nose between the leading edge and its junction at the pressure-face fin.

Blade comprising a shield having a defrosting air passage duct

A method for manufacturing a blade from composite material having an added metal leading edge for a gas turbine aeroengine includes producing a blade body from composite material including a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in a longitudinal direction between a lower end present at the shank part of the composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body.

Blade made of composite material with variable-density attached leading edge

A blade comprising a blade body made of fiber-reinforced organic-matrix composite material and a leading edge shield made of a material having a better resistance to point impacts than the composite material of the blade body, the leading edge shield being assembled on the blade body and including a pressure side fin and a suction side fin connected by a thicker central part, the blade including an aerodynamic airfoil height and a chord length, the suction side fin having a first length projected onto the chord between 10 and 18% of the chord length, the first length being disposed between 70 and 80% of the aerodynamic airfoil height, a second length projected onto the chord between 18 and 26% of the chord length, the second length being disposed between 85 and 95% of the aerodynamic airfoil height.

Blade made of composite material comprising a leading edge shield, turbine engine comprising the blade

The present invention relates to a fan blade of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement obtained by three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded, which comprises a first portion forming the suction-side wall and a second portion forming the pressure-side wall, the strands of the fibrous reinforcement comprising first strands comprising carbon or aramid fibres, the Young's modulus of which is greater than 250 GPa, and second strands produced from a viscoelastic material and having a Young's modulus less than 10 GPa, the first portion comprises uniquely first strands whereas the second portion comprises second strands.

Hybridization of the fibers of the fibrous reinforcement of a fan blade with elastic fibers

The invention relates to a fan blade () made of composite material the fibrous reinforcement of which comprises first strands () having a first stiffness, second strands () having a second stiffness and third strands () having a third stiffness lower than the first stiffness and greater than the second stiffness, the blade comprising a first portion () comprising only first strands (), a second portion () comprising only second strands () and a third portion () which is located between the first and second portions () and which comprises both first, second and third strands (); there is a gradual transition of properties at the interface between the different portions ().

Hybridization of the fibers of the fibrous reinforcement of a fan blade

The present invention relates to a turbomachine rotary-fan blade (), comprising a body () made of a composite material, a metal reinforcement part () comprising a metal upstream nose (), characterised in that the metal upstream nose () comprises, at least on the metal part () of the blade tip, a recess () of longitudinally tapering thickness (AX), delimiting on the metal part () over a height (H) at least one metal projection () with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (), the recess () and the metal projection () with prescribed wear extending the first metal fin () and/or the second metal fin () and/or the upstream edge () of the body () made of composite material.

Turbomachine rotary-fan blade, fan and turbomachine provided therewith

The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.

Turbomachine rotary fan blade, fan, and turbomachine provided therewith

The present invention relates to a fan blade () having a structure made from a composite material, comprising a fibrous reinforcement (), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in which the fibrous reinforcement () is embedded, wherein&#x2014;the fibrous reinforcement () comprises a first portion () forming the trailing edge () of the structure made from a composite material and a second portion () forming its leading edge (), and wherein&#x2014;the warp strands of the fibrous reinforcement () comprise first strands () having a predetermined stiffness and second strands () having a greater stiffness than that of the first strands (), the first portion () comprising all or part of the first strands () and being devoid of second strands () while the second portion () comprises all or part of the second strands ().

Fan blade comprising an insert of stiff fibers

A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.

Fibrous texture for manufacturing a fan blade made of composite material

A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.

Turbomachine blade having a sweep law with high flutter margin

A turbomachine rotor blade is formed of plural blade sections stacked along an axis extending from a blade root to a blade tip. Each blade section located at various heights along the blade is designed to have a given ratio between a maximum thickness, which is measured between a suction side and pressure side of the blade, and a chord, which is defined by a line connecting a leading edge and a trailing edge of the blade. Each blade section is further designed to have a ratio of the maximum thickness to the chord at a given height of the blade relative to a ratio of the maximum thickness to the chord of another blade section located at a different height of the blade.

Turbomachine blade having a maximum thickness law with high flutter margin

A fibrous texture to form the fibrous reinforcement of a turbomachine blade made of composite material, the texture being made in one piece and having a three-dimensional weaving, and includes blade root, blade airfoil and blade support portions. The blade support portion includes a first area extending transversely from a first edge of the texture to form a leading edge and a second area extending transversely from the first area up to a second edge of the texture to form a trailing edge, the first area including warp yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than that of the first fibers, the first area having a first volume ratio in yarns or strands made of second fibers strictly greater than a second volume ratio in yarns or strands made of second fibers in the second area.

Fibrous texture for producing a fan blade made of composite material

A turbine engine rotor blade including a plurality of blade cross sections stacked along an axis Z between a blade root and a blade tip defining therebetween the height of the blade, each blade cross section including a leading edge () and a trailing edge () and a chord defined by the length of the segment which extends from the leading edge to the trailing edge and ensuring that:

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Moissy-Cramayel, France

Guillaume Pascal Jean-Charles Gondre