Snecma

Safran Aircraft Engines

Eric Roger Schwartz

Jean-Michel Guimbard

Renaud Gabriel Constant Royan

Philippe Jean-Pierre Pabion

Jean-Luc Soupizon

Ludovic Pintat

Guillaume Jochen Scholl

Vincent Nicolas Leonardon

Renaud James Martet

Patrick Joseph Marie Girard

Philippe Pabion

Alexandre Nicolas Dervaux

Olivier Kueny

Wilfried Lionel Schweblen

Pascal Pierre Nicolas Routier

Antoine Jean Jausovec

Stephanie Dominique Roger

Aurélien René-Pierre Massot

Philippe Gérard Marie Hazevis

Philippe Hazevis

Laurent Dubois

Damien Redon

Fabien Garnier

Helene Condat

Jean-Michel Bernard Guimbard

Renaud Martet

Stéphanie Dominique Roger

A vane for a turbine engine turbine includes a blade and at least one platform that radially extends the blade, and a system for reducing vortices including at least one circuit including a duct extending from at least one air intake orifice formed in the platform upstream of the leading edge as far as at least one air exhaust slot formed on the trailing edge.

Turbine vane comprising a passive system for reducing vortex phenomena in an air flow flowing over said vane

When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane Psituated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of a turbine

A device that measures turbomachine aerodynamic flow parameters is presented. The device includes the information collection elements relating to the flow parameters, and a body that includes the information collection elements. The body features a portion that is elongated in the longitudinal direction and configured to form the leading edge of a turbomachine vane, and a first side portion that laterally extends portion in an axial direction, wherein the information collection elements protrude from the leading edge of the portion and the portion includes internal channels that route the information and individually communicate with at least one information collection elements, wherein the first side portion features a first surface configured to fit, at least partially, onto a second surface of an intrados or extrados wall of a turbomachine vane.

Measuring device for measuring aerodynamic flow parameters of a turbomachine vane, vane and part of turbomachine equipped with said measuring device

A turbine of a gas turbine engine comprising a stator sealing ring element arranged so as to form a labyrinth sealing joint in combination with at least one wiper, rotatable about the axis of the sealing ring. The element includes an abradable material layer with a surface portion engageable with said movable wiper. The abradable material layer on the surface portion axially includes a first area having a first wiper penetration resistance, said first area corresponding to the axial position of the wiper during nominal operation of the turbine, and a second area adjacent to the first area and having lower wiper penetration resistance than the first area. The second area is located downstream from the first area and corresponds to the axial position that the wiper takes when a flame goes out in the combustion chamber of the engine.

Turbine of gas turbine engine, comprising a labyrinth seal element

A device for connecting a fixed turbine engine portion and a distributor foot of a turbine engine turbine is provided. The device includes a ring-shaped body adapted so as to be connected and secured to the fixed turbine engine portion, and two ring-shaped upstream and downstream brackets secured to the body, both brackets being adapted so as to clamp the foot of the distributor. At least one bracket is interrupted by forming an expansion or retraction slot, the slot allowing an expansion of the bracket tending to close the slot or retraction of the bracket tending to further open the slot, under the effect of a difference in internal temperatures of the device.

Device for connecting a fixed portion of a turbine engine and a distributor foot of a turbine engine turbine

A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, wherein, for all of the stator or rotor rows, it consists in simultaneously modifying the shapes of the airfoils of said rows to straighten out the wakes from the trailing edges of said airfoils, then in angularly positioning the rows in such a manner that the wakes from the airfoils of the stator (or rotor) airfoils impact against the leading edges of the stator (or rotor, respectively) airfoils of the rows situated downstream, in order to achieve multistage aerodynamic coupling simultaneously over the turbine as a whole.

Method of designing a multistage turbine for a turbomachine

A transition channel between a first turbine section and a second turbine section for a gas turbine engine is disclosed. The channel includes a first radially external annular wall including ring sector elements housed inside an annular ring and orifices for injecting a fluid into the channel in order to re-energize the boundary layer thereof, a second radially internal annular wall, and a fluid supply device arranged between the space outside the ring and the injection orifices.

Transition channel between two turbine stages

A device for cooling a turbine casing in a turbomachine including a turbine is disclosed. The turbine includes several stages, at least one of the stages includes a nozzle assembly formed of an annular row of fixed vanes and an impeller mounted to rotate in a cylindrical shroud formed of ring sectors fixed to the casing, a cooling circuit including ducts carrying cooling air into cavities formed in the vanes of the nozzle assembly, and an air-carrying arrangement which carries air to casing upstream hooks for suspending the ring sectors.

Device for cooling a turbomachine turbine casing

A turbomachine stator vane having a leading edge, a trailing edge, and pressure side and suction side faces, a first and a second series of a plurality of holes, calibrated emission holes, and a perforated open liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air opening for feeding cooling air to the inside of the liner, and an air exhaust opening for exhausting cooling air from the vane, the liner being secured to the vane at one end and being free at another end to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane. The holes through the liner in the second series of holes are disposed to avoid any impact of the cooling air against the bridges of the vane.

Stator turbine vane with improved cooling

Growing community of inventors

Seine Port, France

Eric Roger Schwartz