Patents by Inventor Thomas Daris
Thomas Daris 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: 8448448Abstract: An air bleed device for cooling components in a turbine engine, including an annular conduit having a substantially rectangular cross-section formed in a housing and having a radially internal wall swept by an airflow is disclosed. The device includes an air inlet orifice, and a flap valve for controlling the airflow entering through the orifice, formed by a plate borne by a maneuvering member mobile in translation parallel to the axis of the orifice between a position in which the plate closes off the orifice and a position in which the plate opens the orifice.Type: GrantFiled: June 24, 2009Date of Patent: May 28, 2013Assignee: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel
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Patent number: 8408009Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a radially internal portion swept by an airflow (22) and which comprises at least one air inlet orifice (20) formed in an upstream radial wall (38) of the conduit (18), a flap valve (40) for controlling the airflow entering through the orifice (20) and of which the flapper (41) includes a plate (42) applied against the wall (38) and capable of being moved by sliding on said wall (38) by a maneuvering member (50) mobile in translation parallel to the wall (38) between a position in which the plate (42) closes off the orifice (20) and a position in which the plate (42) opens said orifice.Type: GrantFiled: June 23, 2009Date of Patent: April 2, 2013Assignee: SnecmaInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel
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Patent number: 8397513Abstract: Device (10) for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct (18) having a radially internal wall (22) swept by a stream of air (24) and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the flow rate of air entering through the orifice (20), formed of an elastically deformable metal plate (42) of which a downstream end is fixed on an edge of the orifice (20), and of which an upstream end can be displaced by a manoeuvring member (46) mobile in translation parallel to the axis (52) of the orifice between a position where the plate (42) seals this orifice and a position where the plate (42) opens this orifice.Type: GrantFiled: October 22, 2009Date of Patent: March 19, 2013Assignee: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel
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Patent number: 8210498Abstract: A gate valve for a system controlling cooling in a turbomachine is disclosed. The gate valve includes a gate mounted so that it can pivot about an axis between a position in which it shuts off an air passage orifice and a position in which it opens the orifice, and a rotating device for rotating the gate about the axis. The rotating device includes two superposed coaxial rotary members collaborating with one another via cam surfaces designed such that rotating the first rotary member from the shut-off position causes a translational movement of the second rotary member and of the gate along the axis of rotation followed by a rotation of this member and of the gate about this axis.Type: GrantFiled: April 25, 2008Date of Patent: July 3, 2012Assignee: SNECMAInventors: Stéphane Pierre Guillaume Blanchard, Thomas Daris
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Patent number: 7784284Abstract: A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator is disclosed. The exhaust assembly includes a duct which forms a vertical elbow and a nozzle.Type: GrantFiled: April 27, 2007Date of Patent: August 31, 2010Assignee: SNECMAInventors: Edgar Brunet, Thomas Daris, Alain Pierre Page, Jackie Raymond Julien Prouteau
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Publication number: 20100104429Abstract: Device (10) for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct (18) having a radially internal wall (22) swept by a stream of air (24) and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the flow rate of air entering through the orifice (20), formed of an elastically deformable metal plate (42) of which a downstream end is fixed on an edge of the orifice (20), and of which an upstream end can be displaced by a manoeuvring member (46) mobile in translation parallel to the axis (52) of the orifice between a position where the plate (42) seals this orifice and a position where the plate (42) opens this orifice.Type: ApplicationFiled: October 22, 2009Publication date: April 29, 2010Applicant: SNECMAInventors: Stephane Pierre Guillaume Blanchard, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel
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Patent number: 7681400Abstract: A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator is disclosed. The propulsion gas exhaust assembly includes a transition element emerging in two duct elements each communicating with an ejection half-nozzle, wherein each of the two duct elements forms an elbow downstream of the transition element.Type: GrantFiled: April 27, 2007Date of Patent: March 23, 2010Assignee: SNECMAInventors: Thomas Daris, Jackie Raymond Julien Prouteau, Frederic Henri Paul Schenher, Edgar Brunet
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Publication number: 20090320498Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a substantially rectangular cross-section formed in a housing (12) and having a radially internal wall (22) swept by an airflow (24), and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the airflow entering through the orifice (20), formed by a plate (44) borne by a maneuvering member (50) mobile in translation parallel to the axis (21) of the orifice (20) between a position in which the plate (44) closes off said orifice and a position in which the plate (44) opens said orifice.Type: ApplicationFiled: June 24, 2009Publication date: December 31, 2009Applicant: SNECMAInventors: Stephane Pierre Guillaume BLANCHARD, Mathieu DAKOWSKI, Thomas DARIS, Romain Nicolas LUNEL
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Publication number: 20090320497Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a radially internal portion swept by an airflow (22) and which comprises at least one air inlet orifice (20) formed in an upstream radial wall (38) of the conduit (18), a flap valve (40) for controlling the airflow entering through the orifice (20) and of which the flapper (41) includes a plate (42) applied against the wall (38) and capable of being moved by sliding on said wall (38) by a maneuvering member (50) mobile in translation parallel to the wall (38) between a position in which the plate (42) closes off the orifice (20) and a position in which the plate (42) opens said orifice.Type: ApplicationFiled: June 23, 2009Publication date: December 31, 2009Applicant: SNECMAInventors: Stephane Pierre Guillaume BLANCHARD, Mathieu Dakowski, Thomas Daris, Romain Nicolas Lunel
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Patent number: 7631486Abstract: The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.Type: GrantFiled: June 29, 2006Date of Patent: December 15, 2009Assignee: SNECMAInventors: Alain Page, Jackie Prouteau, Thomas Daris, Marc Doussinault, Frederic Schenher
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Patent number: 7581400Abstract: A propulsion gas exhaust assembly is presented for use in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator. The assembly may include a first cylindrical duct, two second ducts, two third ducts, and two axial gas-ejection nozzles. The first cylindrical duct element receives the gases downstream of the gas generator. The gasses flow downstream from the first cylindrical duct element to two second duct elements. These two second duct elements are divergent in a first geometric plane. Each of the two second duct elements may guide the flow to their own respective third duct and nozzle. The third ducts may include elbows to assist in stealth. The nozzles may include the means to steer the aircraft.Type: GrantFiled: April 27, 2007Date of Patent: September 1, 2009Assignee: SNECMAInventors: Edgar Brunet, Thomas Daris, Alain Pierre Page, Jackie Raymond Julien Prouteau
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Publication number: 20080265197Abstract: Gate valve (10) for a system controlling cooling in a turbomachine, comprising a gate (20) mounted so that it can pivot about an axis (16) between a position in which it shuts off an air passage orifice (72) and a position in which it opens the orifice (72), and means (12, 14, 18) for rotating the gate (20) about the axis (16), these means comprising two superposed coaxial rotary members (14, 18) collaborating with one another via cam surfaces (40, 46) designed such that rotating the first rotary member (14) from the shut-off position causes a translational movement of the second rotary member (18) and of the gate (20) along the axis of rotation (16) followed by a rotation of this member (18) and of the gate (20) about this axis. Application of the invention to the cooling of turbojet jet pipe nozzle flaps.Type: ApplicationFiled: April 25, 2008Publication date: October 30, 2008Applicant: SNECMAInventors: Stephane Pierre Guillaume BLANCHARD, Thomas DARIS
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Publication number: 20070284005Abstract: The present invention relates to a propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a duct and a nozzle, wherein said duct comprises a first cylindrical duct element (21) receiving the gases and communicating downstream with two second duct elements (22, 23), the directions of which are divergent in a first plane, each of the two duct elements communicating downstream with a third duct element (25, 27) which emerges in an axial gas-ejection half-nozzle (24, 26).Type: ApplicationFiled: April 27, 2007Publication date: December 13, 2007Applicant: SNECMAInventors: Edgar BRUNET, Thomas Daris, Alain Page, Jackie Prouteau
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Publication number: 20070266712Abstract: The present invention relates to a propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a duct (21) and a nozzle (24). It is noteworthy by the fact that said duct forms a vertical elbow.Type: ApplicationFiled: April 27, 2007Publication date: November 22, 2007Applicant: SNECMAInventors: Edgar Brunet, Thomas Daris, Alain Page, Jackie Prouteau
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Publication number: 20070251211Abstract: The present invention relates to a propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a transition element (21) emerging in two duct elements (22, 23) each communicating with an ejection half-nozzle (24, 26), wherein each of the two duct elements (22, 23) forms an elbow downstream of the transition element.Type: ApplicationFiled: April 27, 2007Publication date: November 1, 2007Applicant: SNECMAInventors: Thomas Daris, Jackie Raymond Julien Prouteau, Frederic Henri Paul Schenher, Edgar Brunet
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Publication number: 20070000233Abstract: The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.Type: ApplicationFiled: June 29, 2006Publication date: January 4, 2007Applicant: SNECMAInventors: Alain Page, Jackie Prouteau, Thomas Daris, Marc Doussinault, Frederic Schenher