Patents by Inventor Dan Ranjiv Joory
Dan Ranjiv Joory 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: 11971174Abstract: A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.Type: GrantFiled: May 14, 2020Date of Patent: April 30, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Dan-Ranjiv Joory, Jacques Marcel Arthur Bunel, Benjamin Frantz Karl Villenave
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Patent number: 11802512Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).Type: GrantFiled: April 13, 2021Date of Patent: October 31, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan-Ranjiv Joory, Benjamin Frantz Karl Villenave
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Patent number: 11725822Abstract: The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).Type: GrantFiled: May 28, 2019Date of Patent: August 15, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Nicolas Lunel, Damien Bonnefoi, Christophe Pieussergues, Luc Namer, Dominique Raulin, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Publication number: 20230151770Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).Type: ApplicationFiled: April 13, 2021Publication date: May 18, 2023Inventors: Jacques Marcel Arthur BUNEL, William Louis Rodolphe DOUSSE, Dan-Ranjiv JOORY, Benjamin Frantz Karl VILLENAVE
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Patent number: 11614234Abstract: A combustion chamber for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine. The combustion chamber includes a radially outer annular shroud, a radially inner annular shroud coaxial with the radially outer shroud, and an end wall connecting the radially outer shroud and the radially inner shroud. The combustion chamber further includes a first annular sealing member coaxial with said radially inner and outer shrouds. The first annular sealing member is radially interposed between the end wall and the radially outer shroud.Type: GrantFiled: January 4, 2018Date of Patent: March 28, 2023Assignee: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, Dan-Ranjiv Joory, Patrice André Commaret, Romain Nicolas Lunel
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Publication number: 20220196243Abstract: A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection. The swivel connection is established between the pin and a part of the outer housing. The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.Type: ApplicationFiled: May 14, 2020Publication date: June 23, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Dan-Ranjiv JOORY, Jacques Marcel Arthur BUNEL, Benjamin Frantz Karl VILLENAVE
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Patent number: 11333358Abstract: A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.Type: GrantFiled: July 24, 2019Date of Patent: May 17, 2022Assignee: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Patent number: 11248793Abstract: A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.Type: GrantFiled: February 28, 2019Date of Patent: February 15, 2022Assignee: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, Dan-Ranjiv Joory
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Patent number: 11085640Abstract: A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.Type: GrantFiled: July 24, 2019Date of Patent: August 10, 2021Assignee: Sanfran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Publication number: 20210140639Abstract: A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.Type: ApplicationFiled: February 28, 2019Publication date: May 13, 2021Applicant: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, Dan-Ranjiv Joory
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Publication number: 20200103111Abstract: A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.Type: ApplicationFiled: July 24, 2019Publication date: April 2, 2020Applicant: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Publication number: 20200033004Abstract: A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.Type: ApplicationFiled: July 24, 2019Publication date: January 30, 2020Applicant: Safran Aircraft EnginesInventors: Jacques Marcel Arthur Bunel, William Louis Rodolphe Dousse, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Publication number: 20190383489Abstract: The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).Type: ApplicationFiled: May 28, 2019Publication date: December 19, 2019Inventors: Romain Nicolas LUNEL, Damien BONNEFOI, Christophe PIEUSSERGUES, Luc NAMER, Dominique RAULIN, Dan Ranjiv JOORY, Benjamin Frantz Karl VILLENAVE
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Publication number: 20190360698Abstract: A combustion chamber for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine. The combustion chamber includes a radially outer annular shroud, a radially inner annular shroud coaxial with the radially outer shroud, and an end wall connecting the radially outer shroud and the radially inner shroud. The combustion chamber further includes a first annular sealing member coaxial with said radially inner and outer shrouds. The first annular sealing member is radially interposed between the end wall and the radially outer shroud.Type: ApplicationFiled: January 4, 2018Publication date: November 28, 2019Inventors: Jacques Marcel Arthur Bunel, Dan Ranjiv Joory, Patrice André Commaret, Romain Nicolas