Patents by Inventor Alain Pierre Garassino
Alain Pierre Garassino 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: 10494084Abstract: A control system for controlling the pitch of a propeller, the system including a propeller shaft, a blade swivel device having a rotary control element suitable for placing the blades in an angular position corresponding to a desired propeller pitch, and a transmission presenting an outlet member coupled in rotation with the rotary control element of the blade swivel device. The transmission includes a variable speed drive having drive, control, and outlet rotors that are coupled in rotation respectively with the propeller shaft, with a control member, and with the outlet member of the transmission. With the variable speed drive, the speed of rotation of the outlet member of the transmission is a predetermined function of the speeds of rotation not only of the propeller shaft, but also of the control member.Type: GrantFiled: March 28, 2017Date of Patent: December 3, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventor: Alain Pierre Garassino
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Patent number: 10352190Abstract: A turbomachine or a turbojet engine or a turboprop engine of an aircraft, including at least one oil circuit and a cooling mechanism including a refrigerant circuit including a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, a second heat exchanger configured to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander mounted downstream from the first exchanger and upstream from the second exchanger, in a direction in which the refrigerant circulates, and a compressor mounted downstream from the second exchanger and upstream from the first exchanger.Type: GrantFiled: July 12, 2013Date of Patent: July 16, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alain Pierre Garassino, Olivier Robert Michel Delepierre-Massue, Marc Missout, Mathieu Jean Pierre Trohel
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Patent number: 10072581Abstract: A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body, a high-pressure rotating body, and a starter designed to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body, for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter.Type: GrantFiled: May 7, 2015Date of Patent: September 11, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Bellal Waissi, Sébastien Chalaud, Alain Pierre Garassino
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Patent number: 9803556Abstract: A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.Type: GrantFiled: September 3, 2013Date of Patent: October 31, 2017Assignees: SNECMA, HISPANO SUIZAInventors: Jordane Peltier, Frantz Armange, Lambert Olivier Marie Demoulin, Alain Pierre Garassino, Nuria Llamas Castro, Stephane Prunera-Usach, Bellal Waissi
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Publication number: 20170283036Abstract: A control system (10) for controlling the pitch of a propeller (50), the system comprising a propeller shaft (60), a blade swivel device (20) having a rotary control element (22) suitable for placing the blades (52) in an angular position corresponding to a desired propeller pitch, and a transmission (12) presenting an outlet member coupled in rotation with the rotary control element (22) of the blade swivel device (20). The transmission (12) includes a variable speed drive (70) having drive, control, and outlet rotors that are coupled in rotation respectively with the propeller shaft (60), with a control member, and with the outlet member of the transmission. By means of the variable speed drive (70), the speed of rotation of the outlet member of the transmission is a predetermined function of the speeds of rotation not only of the propeller shaft, but also of the control member.Type: ApplicationFiled: March 28, 2017Publication date: October 5, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventor: Alain Pierre GARASSINO
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Publication number: 20170074169Abstract: A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body , a high-pressure rotating body, and a starter to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body , for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter.Type: ApplicationFiled: May 7, 2015Publication date: March 16, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Bellal Waissi, Sébastien Chalaud, Alain Pierre Garassino
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Publication number: 20150204246Abstract: This A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.Type: ApplicationFiled: September 3, 2013Publication date: July 23, 2015Applicants: SNECMA, HISPANO SUIZAInventors: Jordane Peltier, Frantz Armange, Lambert Olivier, Marie Demoulin, Alain Pierre Garassino, Nuria Llamas Castro, Stephane Prunera-Usach, Bellal Waissi
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Publication number: 20150192033Abstract: A turbomachine or a turbojet engine or a turboprop engine of an aircraft, including at least one oil circuit and a cooling mechanism including a refrigerant circuit including a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, a second heat exchanger configured to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander mounted downstream from the first exchanger and upstream from the second exchanger, in a direction in which the refrigerant circulates, and a compressor mounted downstream from the second exchanger and upstream from the first exchanger.Type: ApplicationFiled: July 12, 2013Publication date: July 9, 2015Applicant: SNECMAInventors: Alain Pierre Garassino, Olivier Robert, Michel Delepierre-Massue, Marc Missout, Mathieu Jean, Pierre Trohel
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Patent number: 6393353Abstract: A hydraulic fuel control unit (100) for an aircraft engine comprises means (14, 2, 16) for controlling cutoff on stop and cutoff on overspeed of a fuel flow transferred by an output (1) to the engine injectors. A logic module (140) controls the position of a state switch (121, 143) into a test position or a normal position. The state module is managed such that the operation of the overspeed module can be tested each time the system is started on the ground. The architecture of the hydraulic unit (100) is such that operation of the cutoff on stop can be tested during each landing. Correct operation in the overspeed test and in the cutoff on stop test is observed by detecting a difference between a control value (153) of an allowable fuel flow that depends mainly on the engine speed, and a real flow value detected by sensors (22).Type: GrantFiled: March 17, 2000Date of Patent: May 21, 2002Assignee: SNECMA MoteursInventors: Jean-Marie Brocard, Alain Pierre Garassino, Christian Denis Le Boeuf, Alain Patrick Paya, Alain Michel Varizat