Patents by Inventor Simon Nicolas MORLIERE
Simon Nicolas MORLIERE 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: 11879341Abstract: A turbine for a turbine engine extending along an axis includes an annular casing and at least one turbine stage having a nozzle and a rotor impeller wheel surrounded by a sealing ring with an abradable element. The impeller wheel and the sealing ring are located downstream of the nozzle, and the sealing ring has an upstream end held on the casing by locking means. The turbine includes elastic sealing means in contact with the locking means as well as with the nozzle or the casing so as to press the locking means against the sealing ring. The locking means includes a radially outer portion with a C-shaped cross-section and a radial portion extending radially inwards from the outer portion. The sealing means include two elastic seals bearing on the radial portion, respectively, on either side of the radial portion.Type: GrantFiled: April 12, 2021Date of Patent: January 23, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Nicolas Jean-Marc Marcel Beauquin, Stéphane Sylvain Bois, Sébastien Philippe Edith Bourgeois
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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: 20230212953Abstract: The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring (66) placed between the upstream casing and the downstream casing and fastening means (68) for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading (48a) of the turbine engine is mounted on a downstream hook (480b) of the upstream casing, without being hooked onto the shroud ring (66), and the downstream casing (58) has an upstream hook with which the sealing element (62) is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element (62) is mounted so as to be fastened to the downstream casing.Type: ApplicationFiled: April 28, 2021Publication date: July 6, 2023Inventors: Simon Nicolas MORLIERE, Nicolas Jean-Marc Marcel BEAUQUIN, Thierry FACHAT, Alain Dominique GENDRAUD
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Publication number: 20230184126Abstract: A turbine for a turbine engine extending along an axis includes an annular casing and at least one turbine stage having a nozzle and a rotor impeller wheel surrounded by a sealing ring with an abradable element. The impeller wheel and the sealing ring are located downstream of the nozzle, and the sealing ring has an upstream end held on the casing by locking means. The turbine includes elastic sealing means in contact with the locking means as well as with the nozzle or the casing so as to press the locking means against the sealing ring. The locking means includes a radially outer portion with a C-shaped cross-section and a radial portion extending radially inwards from the outer portion. The sealing means include two elastic seals bearing on the radial portion, respectively on either side of the radial portion.Type: ApplicationFiled: April 12, 2021Publication date: June 15, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas MORLIERE, Nicolas Jean-Marc Marcel BEAUQUIN, Stéphane Sylvain BOIS, Sébastien Philippe Edith BOURGEOIS
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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: 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: 11286803Abstract: The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the casing (18), at least one cooling tube (23) extending circumferentially, at least one attachment member (25) comprising a radially inner portion (36) at least partially surrounding the tube (23), and a radially outer portion (37) attached to the support (24), the radially outer portion (37) of the attachment member (25) being attached to the support (24) through connecting means (30) formed by L-shaped sheets.Type: GrantFiled: March 28, 2019Date of Patent: March 29, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Julian Nicolas Girardeau, Sébastien Jean Laurent Prestel, Ghislain Hervé Abadie, Benjamin Franklin François Gillot
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Patent number: 11274568Abstract: Cooling device (21) extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support (24) extending axially and designed to be secured to the casing, at least one cooling tube extending circumferentially, at least one securing member (25), comprising a radially inner portion (36) at least partially surrounding the tube, and a radially outer portion (37) secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the support (24) via the intermediary of a connection member (30) comprising a central portion (31) having a circumferential end portion (32) and a second circumferential end portion (32) which are circumferentially opposite, the first end portion (32) and the second end portion (32) each extending in an opposite axial direction, the first and second end portions (32, 32) each being secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the central portion (31) of thType: GrantFiled: March 28, 2019Date of Patent: March 15, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Julian Nicolas Girardeau, Sébastien Jean Laurent Prestel, Ghislain Hervé Abadie, Benjamin Franklin François Gillot
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Patent number: 11035244Abstract: Turbine engine turbine sealing module extending about an axis and including a distributor fixed to a casing, and at least one blade connected to an outer platform. The turbine module further includes an impeller mounted rotating inside the casing and surrounded by a sealing ring fastened to this casing. The sealing ring includes an annular row of ring sectors arranged such that the circumferential end edges of two adjacent sectors are facing one another. Each sector includes a body configured to engage with at least one seal lip carried by the impeller and a hook which extends circumferentially which is configured to engage with a fastening rail of the casing. Each ring sector further includes a deflector which extends radially inwards and upstream with respect to the axis, such that the radially inward end thereof extends around a downstream end of the outer platform of the distributor.Type: GrantFiled: July 1, 2019Date of Patent: June 15, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Nicolas Jean-Marc Marcel Beauquin, Renaud James Martet, Vincent Francois Georges Millier
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Patent number: 11035242Abstract: A sealing assembly for a turbine is provided. The turbine includes stages each including a nozzle blade extending between radially inner and outer platforms, the outer platform including a spoiler which delimits a groove. The assembly includes a ring, a tab, and an anti-wear foil. The ring is to be attached to an outer casing of the turbine. A part of the sealing tab is engaged in a first housing of a ring sector of the ring and another part in a second housing of an adjacent ring sector. The anti-wear foil, open upstream, is mounted in the groove. The downstream end of the ring sectors are to be engaged in the anti-wear foil. Each of the first and second housings is formed by a slot. The tab is bent and disposed in the slots so that a downstream end of the tab extends out of the slots.Type: GrantFiled: July 17, 2019Date of Patent: June 15, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas Morliere, Nicolas Jean-Marc Marcel Beauquin, Vincent Francois Georges Millier
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Publication number: 20210164361Abstract: The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the casing (18), at least one cooling tube (23) extending circumferentially, at least one attachment member (25) comprising a radially inner portion (36) at least partially surrounding the tube (23), and a radially outer portion (37) attached to the support (24), the radially outer portion (37) of the attachment member (25) being attached to the support (24) through connecting means (30) formed by L-shaped sheets.Type: ApplicationFiled: March 28, 2019Publication date: June 3, 2021Inventors: Simon Nicolas MORLIERE, Julian Nicolas GIRARDEAU, Sébastien Jean Laurent PRESTEL, Ghislain Hervé ABADIE, Benjamin Franklin François GILLOT
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Publication number: 20210164362Abstract: Cooling device (21) extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support (24) extending axially and designed to be secured to the casing, at least one cooling tube extending circumferentially, at least one securing member (25), comprising a radially inner portion (36) at least partially surrounding the tube, and a radially outer portion (37) secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the support (24) via the intermediary of a connection member (30) comprising a central portion (31) having a circumferential end portion (32) and a second circumferential end portion (32) which are circumferentially opposite, the first end portion (32) and the second end portion (32) each extending in an opposite axial direction, the first and second end portions (32, 32) each being secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the central portion (31) of thType: ApplicationFiled: March 28, 2019Publication date: June 3, 2021Inventors: Simon Nicolas MORLIERE, Julian Nicolas GIRARDEAU, Sébastien Jean Laurent PRESTEL, Ghislain Hervé ABADIE, Benjamin Franklin François GILLOT
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Publication number: 20200182058Abstract: 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: ApplicationFiled: December 5, 2019Publication date: June 11, 2020Applicant: 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: 20200063588Abstract: The invention relates to a sealing assembly for a turbine (1) rotor of a turbomachine, said turbine comprising an outer casing (4) and a plurality of rotor impellers (3) and nozzles (2), the sealing assembly comprising a sealing ring (7), attached to the casing (4), consisting of a plurality of ring sectors (70a, 70b) and surrounding the impeller (3), a sealing tab (8, 8?) being engaged, in a first slot (73a) of a ring sector (70a) and in a second slot (73b) of an adjacent ring sector (70b).Type: ApplicationFiled: July 17, 2019Publication date: February 27, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Simon Nicolas MORLIERE, Nicolas Jean-Marc Marcel BEAUQUIN, Vincent Francois Georges MILLIER
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Publication number: 20200011194Abstract: Turbine engine turbine sealing module extending about an axis and including a distributor fixed to a casing, and at least one blade connected to an outer platform. The turbine module further includes an impeller mounted rotating inside the casing and surrounded by a sealing ring fastened to this casing. The sealing ring includes an annular row of ring sectors arranged such that the circumferential end edges of two adjacent sectors are facing one another. Each sector includes a body configured to engage with at least one seal lip carried by the impeller and a hook which extends circumferentially which is configured to engage with a fastening rail of the casing. Each ring sector further includes a deflector which extends radially inwards and upstream with respect to the axis, such that the radially inward end thereof extends around a downstream end of the outer platform of the distributor.Type: ApplicationFiled: July 1, 2019Publication date: January 9, 2020Inventors: Simon Nicolas MORLIERE, Nicolas Jean-Marc Marcel BEAUQUIN, Renaud James MARTET, Vincent Francois Georges MILLIER