Safran Aircraft Engines

Jean-Louis Romero

Jérémy Guivarc'h

Thibault Ruf

Alain Jacques Michel Bassot

Angélique Melody Marine Alexia Mainczyk

Frédéric Jean-Bernard Pouzadoux

Jean-Pierre Coulette

Geoffrey Martin

Jean-François Frerot

Gérald Diogo

A leading-edge shield for a turbomachine blade includes a pressure-side wing and a suction-side wing. Both the pressure-side wing and suction-side wing extend heightwise from a bottom edge to a top edge and lengthwise from the leading edge to a respective rear edge. They are connected together via the leading edge. The rear edge of the suction-side wing presents at least one shaped segment that is shaped in such a manner that the length of the suction-side wing within this segment is shorter than the length of the suction-side wing at each end of this segment.

Leading edge shield

The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield () for a turbomachine blade (), said leading-edge shield () having a pressure-side wing () and a suction-side wing (), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing () presenting a greater length than the suction-side wing () over a first segment (S) of the leading-edge shield (), and an equal or smaller length than the suction-side wing () over a second segment (S) of the leading-edge shield ().

A leading-edge shield () for a turbomachine blade () includes a pressure-side wing () and a suction-side wing (). Each of the wings () extends along a height (H) from a bottom edge () to a top edge () and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing () and the pressure-side wing () presents a segment (S), adjacent to the top edge () and extending over at least 10% of the height (H), wherein the rear edge () slopes towards the top edge ().

Blade, associated fan and turbojet engine

A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, the method comprising the following steps: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the value aof the parameter a of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of said part and obtaining the value aof the parameter a of the CIELAB colorimetric space; c) calculating &#x394;a=a&#x2212;a; and d) establishing a risk of heating said determined zone to be tested if &#x394;ais higher than a threshold value A1.

Method for the non-destructive testing of a casing by colorimetry

A method for the non-destructive testing of the heating of a part made from polymer material, the method comprising the following steps: a) carrying out a measurement by infrared spectroscopy on a part to be tested and extracting therefrom at least one of absorbance values and transmittance values according to a spatial frequency; and b) from the measurement of at least one of absorbance and transmittance, determining the period of time during which said region of the part to be tested has been subjected to a given heating temperature and determining said heating temperature, using a reference database comprising at least one of absorbance measurements and transmittance measurements, the measurements established over a plurality of reference samples made from polymer material that have been subjected to a given temperature during a given period of time.

Method for the non-destructive testing of a casing

A turbine engine blade comprising an aerodynamic surface that extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a root and a tip of the blade, and a leading-edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterised in that the fin has a radially outer edge arranged in the vicinity of the tip of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point fitting flush with the tip of the blade at the leading edge and a so-called downstream point separated from the tip of the blade.

Reinforcement for the leading edge of a turbine engine blade

A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, comprising: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the values a, band Lof the parameters a, b and L of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of the part and obtaining the values a, band Lof the parameters a, b and L of the CIELAB colorimetric space; c) calculating the colour difference &#x394;Ebetween the colorimetric measurements obtained in steps a) and b); and d) from the value &#x394;E, determining the time period during which said zone to be tested of the part has been subjected to a determined heating temperature, by using a reference database.

Growing community of inventors

Moissy-Cramayel, France

Jean-Louis Romero