Patents by Inventor Alain Jacques
Alain Jacques 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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Patent number: 11131196Abstract: 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.Type: GrantFiled: December 21, 2016Date of Patent: September 28, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Jean-Bernard Pouzadoux, Alain Jacques Michel Bassot, Jérémy Guivarc'h, Jean-Louis Romero, Thibault Ruf
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Patent number: 11015460Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).Type: GrantFiled: August 2, 2016Date of Patent: May 25, 2021Assignee: Safran Aircraft EnginesInventors: Matthieu Arnaud Gimat, Alain Jacques Michel Bassot, Jérémy Guivarc'h, Jean-Noël Mahieu, Thibault Ruf
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Patent number: 10934851Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).Type: GrantFiled: December 21, 2016Date of Patent: March 2, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Guivarc'h, Alain Jacques Michel Bassot, Gérald Diogo, Jean-Louis Romero, Thibault Ruf
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Patent number: 10844725Abstract: A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.Type: GrantFiled: December 21, 2016Date of Patent: November 24, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Jean-Bernard Pouzadoux, Alain Jacques Michel Bassot, Jérémy Guivarc'h, Gilles Pierre-Marie Notarianni, Thibault Ruf
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Publication number: 20200270997Abstract: A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.Type: ApplicationFiled: December 21, 2016Publication date: August 27, 2020Inventors: Frédéric Jean-Bernard POUZADOUX, ALAIN JACQUES MICHEL BASSOT, Jérémy GUIVARC'H, GILLES PIERRE-MARIE NOTARIANNI, THIBAULT RUF
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Patent number: 10619486Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) 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 (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).Type: GrantFiled: December 21, 2016Date of Patent: April 14, 2020Assignee: Safran Aircraft EnginesInventors: Frédéric Jean-Bernard Pouzadoux, Alain Jacques Michel Bassot, Jérémy Guivarc'h, Jean-Louis Romero, Thibault Ruf
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Publication number: 20190024512Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).Type: ApplicationFiled: December 21, 2016Publication date: January 24, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jérémy GUIVARC'H, Alain Jacques Michel BASSOT, Gérald DIOGO, Jean-Louis ROMERO, Thibault RUF
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Publication number: 20190010807Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) 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 (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).Type: ApplicationFiled: December 21, 2016Publication date: January 10, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Jean-Bernard POUZADOUX, Alain Jacques Michel BASSOT, Jérémy GUIVARC'H, Jean-Louis ROMERO, Thibault RUF
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Publication number: 20190003312Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) including a pressure-side wing (34) and a suction-side wing (36). Each pressure-side wing (34) and suction-side wing (36) extends heightwise from a bottom edge (50) to a top edge (51) and lengthwise from the leading edge (18) to a rear edge (40, 42), and they are connected together via the leading edge (18), and wherein the rear edge (42) of the suction-side wing (36) presents at least one shaped segment (S1, S2) that is shaped in such a manner that the length of the suction-side wing (36) within this segment is shorter than the length (l2, l3, l21, l22, l31, l32) of the suction-side wing (36) at each end of this segment (S1, S2).Type: ApplicationFiled: December 21, 2016Publication date: January 3, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Jean-Bernard POUZADOUX, Alain Jacques Michel BASSOT, Jérémy GUIVARC'H, Jean-Louis ROMERO, Thibault RUF
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Publication number: 20180230825Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).Type: ApplicationFiled: August 2, 2016Publication date: August 16, 2018Applicant: Safran Aircraft EnginesInventors: Matthieu Arnaud Gimat, Alain Jacques Michel BASSOT, Jérémy GUIVARC'H, Jean-Noël MAHIEU, Thibault RUF
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Patent number: 9433995Abstract: A method of manufacturing a liner for use in a pressure vessel includes a cold drawing process that shapes a transition zone (20b) part of an aluminum alloy liner shell (10). The transition zone (20b) links a thinner walled drum part (18) and a thicker walled end region (20a), which is at an open top of the shell. The transition zone (20b) may be shaped by the cold drawing process such that it reduces susceptibility of the shell to fracture during removal from a cold drawing press and also redistributes shell material in preparation for a subsequent process in which a threaded neck is formed from the end region (20a). This process is particularly suited to processing harder aluminum alloy materials such as AA7060 or AA7032.Type: GrantFiled: March 14, 2014Date of Patent: September 6, 2016Assignee: Luxfer Gas Cylinders LimitedInventors: Bernard Alain Jacques Chalandon, Romary Georges Marcel Daval, Warren Hepples
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Publication number: 20160023265Abstract: A method of manufacturing a liner for use in a pressure vessel includes a cold drawing process that shapes a transition zone (20b) part of an aluminium alloy liner shell (10). The transition zone (20b) links a thinner walled drum part (18) and a thicker walled end region (20a), which is at an open top of the shell. The transition zone (20b) may be shaped by the cold drawing process such that it reduces susceptibility of the shell to fracture during removal from a cold drawing press and also redistributes shell material in preparation for a subsequent process in which a threaded neck is formed from the end region (20a). This process is particularly suited to processing harder aluminium alloy materials such as AA7060 or AA7032.Type: ApplicationFiled: March 14, 2014Publication date: January 28, 2016Applicant: LUXFER GAS CYLINDERS LIMITEDInventors: Bernard Alain Jacques Chalandon, Romary Georges Marcel Daval, Warren Hepples
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Patent number: 8987184Abstract: The present invention is directed, in certain embodiments, to compositions useful for the removal of grease, lime scale, soap scum, feces, rust or other soils from surfaces such as those found in bathrooms, toilets and kitchens. Methods of removing soils and preventing soil adhesion are also contemplated.Type: GrantFiled: February 27, 2013Date of Patent: March 24, 2015Assignee: Colgate-Palmolive CompanyInventors: Michele Davister, Nathalie Dastbaz, Alain Jacques, Germaine Zocchi
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Patent number: 8864472Abstract: A method of repairing or of reworking a turbomachine disk including, on its rim, at least one external radial tab with an axial bore to accept an axial pin including a head and a shank with a threaded portion, the pin being slipped into the bore such that the head comes to press against one face of the tab through tightening of a nut on to the shank with the threaded portion against the opposite face of the tab, the pin forming a retaining mechanism to keep a tab secured to a component attached to the rim. A spot face is machined in the tab around the bore corresponding to a wearing zone, and a replacement pin including a flange pressing against the surface of the spot face, of a diameter greater than that of the head, is fitted.Type: GrantFiled: July 16, 2009Date of Patent: October 21, 2014Assignee: SNECMAInventors: Herve Gignoux, Eric Gvozdenovic, Gael Loro, Alain Jacques Michel Bassot
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Publication number: 20140165812Abstract: A saw-blade comprises a disc and a plurality of tooth holders. The saw blade disc has a plurality of receiving stations with at least one recess with an indentation extending tangentially from a radially inner leading edge portion thereof. Each one of the tooth holders has a protrusion extending tangentially from a radially inner leading edge portion thereof. The tooth holders are engageable in the receiving stations of the saw blade disc with the protrusions of the tooth holders being inserted in the indentation of the receiving stations.Type: ApplicationFiled: July 27, 2012Publication date: June 19, 2014Applicant: 9293-3720 QUÉBEC INC.Inventor: Alain Jacques
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Publication number: 20130247936Abstract: The present invention is directed, in certain embodiments, to compositions useful for the removal of grease, lime scale, soap scum, feces, rust or other soils from surfaces such as those found in bathrooms, toilets and kitchens. Methods of removing soils and preventing soil adhesion are also contemplated.Type: ApplicationFiled: February 27, 2013Publication date: September 26, 2013Applicant: Colgate-Palmolive CompanyInventors: Michele Davister, Nathalie Dastbaz, Alain Jacques, Germaine Zocchi
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Patent number: 8470762Abstract: Fabric softening compositions comprising polymeric materials capable of retaining volatile perfume ingredients are disclosed, as well as methods of softening fabrics.Type: GrantFiled: May 31, 2007Date of Patent: June 25, 2013Assignee: Colgate-Palmolive CompanyInventors: Guy Broze, Alain Jacques, Alexandrine Tuzi, Georges Yianakopoulos
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Patent number: 8410038Abstract: The present invention is directed, in certain embodiments, to compositions useful for the removal of grease, lime scale, soap scum, feces, rust or other soils from surfaces such as those found in bathrooms, toilets and kitchens. Methods of removing soils and preventing soil adhesion are also contemplated.Type: GrantFiled: December 28, 2007Date of Patent: April 2, 2013Assignee: Colgate-Palmolive CompanyInventors: Michele Davister, Nathalie Dastbaz, Alain Jacques, Germaine Zocchi
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Publication number: 20130000052Abstract: The present invention is directed to methods of reducing fabric malodor, comprising applying a water-soluble soil release polymer (SRP), as well as compositions comprising such polymers.Type: ApplicationFiled: November 17, 2006Publication date: January 3, 2013Applicant: Colgate-Palmolive CompanyInventors: Myriam Peeters, Alain Jacques, Doris Moré
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Publication number: 20120246838Abstract: There is provided a fabric conditioner that reduces wrinkle formation in laundered garments. There is further provided a method for reducing the occurrence of wrinkles in laundered garments.Type: ApplicationFiled: July 8, 2010Publication date: October 4, 2012Applicant: Colgate-Palmolive CompanyInventors: Raul Garduno, Javier Tovar, Alain Jacques, Regis Cesar, Ana Acosta, Amit Sachdev