Patents by Inventor Pierre Guillaume
Pierre Guillaume has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20240167490Abstract: The invention concerns a method for detecting a fatigue undergone on at least one specific location of a hydraulic unit (10), the method being characterized in that the fatigue undergone on the at least on specific location is detected by at least one fatigue indicator (F) said at least one fatigue indicator arranged for being remotely queried via wirings or via a wireless connection.Type: ApplicationFiled: November 29, 2023Publication date: May 23, 2024Inventors: Florian DUPARCHY, Pierre-Yves LOWYS, Renaud Guillaume, Francois ANDRE
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Publication number: 20240101542Abstract: The present disclosure relates to novel compounds of formula (I) which are useful as inhibitors of endoplasmic reticulum aminopeptidases (ERAP), in particular as inhibitors of ERAP2. The disclosure also relates to the therapeutic use of these compounds, in particular the use of these compounds in the treatment or prophylaxis of proliferative disorders, autoinflammatory disorders and autoimmune disorders.Type: ApplicationFiled: December 17, 2021Publication date: March 28, 2024Inventors: Rebecca DEPREZ POULAIN, Ronan GEALAGEAS, Virgyl CAMBERLEIN, Charlotte TABEY FLEAU, Valentin GUILLAUME, Damien BOSC, Benoit DEPREZ, Pierre SIEROCKI
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Patent number: 11879347Abstract: A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.Type: GrantFiled: April 13, 2021Date of Patent: January 23, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Benoit Guillaume Silet, Stéphane Pierre Guillaume Blanchard, Fabien Stéphane Garnier, Thibaud Louis Zaia
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Patent number: 11753958Abstract: The present invention relates to a device for cooling, using air jets, an external casing of a turbomachine, comprising a housing for supplying air to cooling tubes of said casing, the housing being provided with an attachment device on the external casing. According to the invention, said attachment device comprises two upstream ball joint retention devices which each connect the housing to the external casing.Type: GrantFiled: August 6, 2020Date of Patent: September 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Stéphane Pierre Guillaume Blanchard, Nicolas Jean-Marc Marcel Beauquin
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Publication number: 20230127638Abstract: A database system, method, and computer program product of handling purchases of products is presented, in which the database system comprises a relational database storing relational data for a plurality of products, a key-value database storing a plurality of first files and a plurality of second files, an interface module connecting the relational database with the key-value database, and a shopping engine to communicate with the key-value database. The interface module converts relational data stored in the relational database into first files and second files. The shopping engine queries the key-value database to retrieve available products in response to an availability request.Type: ApplicationFiled: October 26, 2021Publication date: April 27, 2023Inventors: Yoann POULAIN, Charles Michel Pierre Guillaume CULTIEN, Grégory VALIGIANI, Luigi DI NOIA, Philippe SARCEY
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Patent number: 11555405Abstract: A device for holding (101) at least one cooling tube (120) of a turbomachine casing (10) cooling system (100), the holding device including a fixing frame (104), a holding member (160) being configured to hold two cooling tubes (120), and a connection assembly (140) between the holding member (160) and a fixing frame (104), extending on either side of the frame, the connection assembly (160) comprising a connection part (150) extending through an opening (108) of the fixing frame from an outer portion (141) to the inner portion (142) of the connection assembly, the inner portion (142) being disposed between two cooling tubes (120) and secured to the holding member (160) while the outer portion (141) comprises a resilient return member (170) urged in compression towards the fixing frame by the connection part (150).Type: GrantFiled: December 5, 2019Date of Patent: January 17, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Nicolas Jean-Marc Marcel Beauquin, Stéphane Pierre Guillaume Blanchard, Gaëlle Inès Méganne Moreaux
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Publication number: 20220389874Abstract: The invention relates to an assembly for a turbine engine, comprising a radially inner shaft (3) and a radially outer shaft (7), said shafts (7, 8) being coaxial and extending along an axis (X), means (11, 15) for coupling said inner and outer shafts (7, 8) in rotation, means (22) for axially holding the inner shaft (8) relative to the outer shaft (7), means for centring the inner shaft (8) relative to the outer shaft (7), characterised in that the centring means comprise a shim (14) for radial centring and for axial positioning, this shim being frustoconical and interposed between a frustoconical centring surface (13) of the inner shaft (8) and a corresponding frustoconical centring surface (10) of the outer shaft (7).Type: ApplicationFiled: September 21, 2020Publication date: December 8, 2022Inventors: Patrick Jean Laurent SULTANA, Stéphane Pierre Guillaume BLANCHARD, Antoine Hervé DOS SANTOS
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Patent number: 11499436Abstract: A turbine blade including a root carrying an impeller terminated by a tip in the form of a squealer tip. This impeller also includes a serpentine median circuit, including a first radial pipe collecting air at the root and that is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe, a cavity under the squealer tip running along the pressure side wall, extending from a central region of the tip to the trailing edge, and a radial central pipe collecting air at the root extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.Type: GrantFiled: November 29, 2019Date of Patent: November 15, 2022Assignees: SAFRAN, SAFRAN AIRCRAFT ENGINESInventors: Léandre Ostino, Pierre Guillaume Auzillon, Romain Pierre Cariou, Thomas Olivier Michel Pierre De Rocquigny, Patrice Eneau, Adrien Bernard Vincent Rollinger, Vianney Simon, Michel Slusarz, Ba-Phuc Tang
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Publication number: 20220290579Abstract: The invention relates to an assembly (25) for a turbomachine turbine comprising a casing (18) including an annular wall (26) extending about an axis, and means of cooling the casing (18), the said means of cooling comprising a collector housing (22) and at least one tube (23) extending circumferentially around the annular wall (26) of the casing (18) and connected to the housing (22), with the tube (23) comprising cooling-air ejection orifices.Type: ApplicationFiled: August 4, 2020Publication date: September 15, 2022Inventors: Simon Nicolas MORLIERE, Stéphane Pierre Guillaume BLANCHARD, Nicolas Jean-Marc Marcel BEAUQUIN, Alain Dominique GENDRAUD, Olivier RENON
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Publication number: 20220228504Abstract: The present invention relates to a device for cooling, using air jets, an external casing of a turbomachine, comprising a housing for supplying air to cooling tubes of said casing, the housing being provided with an attachment device on the external casing. According to the invention, said attachment device comprises two upstream ball joint retention devices which each connect the housing to the external casing.Type: ApplicationFiled: August 6, 2020Publication date: July 21, 2022Applicant: Safran Aircraft EnginesInventors: Simon Nicolas MORLIERE, Stéphane Pierre Guillaume BLANCHARD, Nicolas Jean-Marc Marcel BEAUQUIN
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Patent number: 11378014Abstract: A turbomachine includes a low-pressure shaft that drives a fan shaft in rotation by a coupling assembly including a first shaft on which are formed plural first axial grooves, a second shaft on which are formed plural second axial grooves, and a coupling device including rolling elements and an annular cage positioned between the first shaft and the second shaft. The rolling elements are positioned between one of the first axial grooves and one of the second axial grooves to couple in rotation the first and the second shaft. Each first and second groove has a first and a second substantially planar surface inclined with respect to one another and extending along the axis.Type: GrantFiled: May 15, 2019Date of Patent: July 5, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Stéphane Pierre Guillaume Blanchard, Helene Myriam Condat, Nicolas Xavier Trappier, Laurent Paul François Perrot
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Publication number: 20220205365Abstract: A turbine vane includes a root carrying a blade terminated by a squealer tip, the blade having intrados and extrados walls, a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall. The blade also includes: a serpentine median circuit, including a first radial pipe that collects air at the root and is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe; a cavity under the squealer tip running along the extrados wall and extending from a central region of the squealer tip to the trailing edge; and a central radial pipe collecting air at the root and extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.Type: ApplicationFiled: April 24, 2020Publication date: June 30, 2022Inventors: Léandre OSTINO, Pierre Guillaume AUZILLON, Michel SLUSARZ, Patrice ENEAU, Thomas Olivier Michel Pierre DE ROCQUIGNY, Romain Pierre CARIOU, Ba-Phuc TANG, Adrien Bernard Vincent ROLLINGER, Vianney SIMON
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Publication number: 20220170371Abstract: An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4?) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.Type: ApplicationFiled: March 11, 2020Publication date: June 2, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Michel SLUSARZ, Pierre Guillaume AUZILLON, Patrice ENEAU, Léandre OSTINO
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Patent number: 11299989Abstract: The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring (28) relative to the rotor disks (20a, 20b), said system comprising: a rotor disk securing flange (222) having a plurality of teeth (224) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), and a mobile ring securing flange (282) having a plurality of lugs (284) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), the engagement of the rotor disk securing flange (222) with the mobile ring securing flange (282) ensuring, by means of the teeth (224) and the lugs (284), that the mobile ring (28) does not rotate relative to the rotor disks (20a, 20b).Type: GrantFiled: January 29, 2019Date of Patent: April 12, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Stéphane Pierre Guillaume Blanchard, Nicolas Xavier Trappier, Quentin De Richaud
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Publication number: 20220025771Abstract: A turbine blade including a root carrying an impeller terminated by a tip in the form of a squealer tip. This impeller also includes a serpentine median circuit, including a first radial pipe collecting air at the root and that is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe, a cavity under the squealer tip running along the pressure side wall, extending from a central region of the tip to the trailing edge, and a radial central pipe collecting air at the root extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.Type: ApplicationFiled: November 29, 2019Publication date: January 27, 2022Applicants: SAFRAN, SAFRAN AIRCRAFT ENGINESInventors: Léandre OSTINO, Pierre Guillaume AUZILLON, Romain Pierre CARIOU, Thomas Olivier Michel Pierre DE ROCQUIGNY, Patrice ENEAU, Adrien Bernard Vincent ROLLINGER, Vianney SIMON, Michel SLUSARZ, Ba-Phuc TANG
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Publication number: 20210189972Abstract: The invention relates to a turbomachine comprising a low-pressure shaft (27) configured to drive a fan shaft (32) in rotation by means of a coupling assembly comprising a first shaft (1) on which are formed a plurality of first axial grooves (7), a second shaft (2) on which are formed a plurality of second axial grooves (12), and a coupling device (4) including a plurality of rolling elements (13) and an annular cage (14) positioned between the first shaft (1) and the second shaft (2), the rolling elements (13) being positioned between one of the first axial grooves (7) and one of the second axial grooves (12) to couple in rotation the first and the second shaft (1, 2), each first and second groove (7, 12) having a first (16) and a second (17) substantially planar surface inclined with respect to one another and extending along the axis.Type: ApplicationFiled: May 15, 2019Publication date: June 24, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Stéphane Pierre Guillaume BLANCHARD, Helene Myriam CONDAT, Nicolas Xavier TRAPPIER, Laurent Paul François PERROT
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Publication number: 20210054743Abstract: The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring (28) relative to the rotor disks (20a, 20b), said system comprising: a rotor disk securing flange (222) having a plurality of teeth (224) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), and a mobile ring securing flange (282) having a plurality of lugs (284) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), the engagement of the rotor disk securing flange (222) with the mobile ring securing flange (282) ensuring, by means of the teeth (224) and the lugs (284), that the mobile ring (28) does not rotate relative to the rotor disks (20a, 20b).Type: ApplicationFiled: January 29, 2019Publication date: February 25, 2021Applicant: Safran Aircraft EnginesInventors: Stéphane Pierre Guillaume BLANCHARD, Nicolas Xavier TRAPPIER, Quentin DE RICHAUD
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Patent number: 10920609Abstract: A turbine assembly for a turbine engine, includes a rotor disk having a plurality of CMC material blades, a stationary nozzle made of CMC material having a plurality of vanes with outer platforms forming a nozzle ring, a turbine ring made as a single piece of CMC material, and a casing of material presenting a coefficient of thermal expansion that is strictly greater than the coefficient of thermal expansion of the ceramic matrix composite material forming the blades of the rotor disk, the nozzle, and the turbine ring, the casing extending around the nozzle ring and the turbine ring, at least the nozzle ring or the turbine ring being connected to the casing via at least one sliding connection having a degree of freedom to move radially.Type: GrantFiled: April 24, 2018Date of Patent: February 16, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Hélène Myriam Condat, Stéphane Pierre Guillaume Blanchard, Sylvain Yves Jean Duval
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Patent number: 10767505Abstract: A tubular shaft (8) of a turbomachine, including at the inner periphery of same, a bath (11), substantially perpendicular to splines (9), the bath (11) includes cavities (17) distributed over a circumference centred on an axis of rotation (LL) of the shaft (8).Type: GrantFiled: August 28, 2015Date of Patent: September 8, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Youki Olivier Ito-Lardeau, Pierrick Raphael Americo Bauduin, Stephane Pierre Guillaume Blanchard, Bertrand Guillaume Robin Pellaton
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Publication number: 20200242520Abstract: A computer-implemented method comprising: receiving a user-generated request comprising functional data; retrieving a list of data items and a set of dependency rules, each data item being assigned an undefined binary validity value; generating a directed graph by organizing the data items in accordance with the retrieved dependency rules; applying a filtration process to solve the directed graph comprising: calculating the validity value; propagating the validity values through the graph; and filtering the directed graph by keeping only nodes having a validity value of one; calculating, for each filtered data item, a price; and generating a list of available data items with their price. The node suppression decreases the number of data items for which a price has to be calculated, thereby saving resources and/or decreasing the time needed to resolve the user request.Type: ApplicationFiled: January 21, 2020Publication date: July 30, 2020Inventors: Marc Andre Jerome TRAINA, Yoann POULAIN, Charles Michel Pierre Guillaume CULTIEN, Valerian Romain Emmanuel ROCHE, Fabien Xavier MOURGUES, Gregory VALIGIANI