Patents by Inventor Jean-Michel Guimbard
Jean-Michel Guimbard 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).
-
Publication number: 20220074595Abstract: A turbine engine includes a combustion chamber, comprising two coaxial axisymmetric walls extending one inside the other and delimiting between one another an annular air-circulation, an exterior wall, and at least one injector passing through the walls via ports, wherein the injector comprises a peripheral tube connected to the walls by three connections, at least two connections being of the slideway and/or ball-joint or bellows type.Type: ApplicationFiled: December 17, 2019Publication date: March 10, 2022Inventors: Damien Fauvet, Marc Nguyen, Baptiste Guerin, Jean-Michel Guimbard
-
Patent number: 9518467Abstract: A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface.Type: GrantFiled: January 7, 2015Date of Patent: December 13, 2016Assignee: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
-
Publication number: 20150147179Abstract: A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface.Type: ApplicationFiled: January 7, 2015Publication date: May 28, 2015Applicant: SNECMAInventors: Jean-Michel GUIMBARD, Olivier KUENY, Ludovic PINTAT
-
Patent number: 9022744Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3H to 0.8H, where H is the height of the blade measured from its root to its tip.Type: GrantFiled: June 20, 2012Date of Patent: May 5, 2015Assignee: SNECMAInventors: Renaud Gabriel Constant Royan, Renaud Martet, Jean-Michel Guimbard
-
Patent number: 9004865Abstract: A blade for a turbomachine impeller including an airfoil and at least one platform at one end of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring, the platform surface having a suction surface profile and a pressure surface profile respectively along the suction surface and the pressure surface. In the blade, the pressure surface profile including a pressure surface recessed part is located axially in an upstream half of the airfoil. Due to this configuration, efficiency of the blade is improved.Type: GrantFiled: February 27, 2009Date of Patent: April 14, 2015Assignee: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
-
Patent number: 8757968Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of the profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 28, 2011Date of Patent: June 24, 2014Assignee: SnecmaInventors: Jean Bleuzen, Jean-Michel Guimbard, Ludovic Pintat, Pascal Routier
-
Patent number: 8734096Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 29, 2011Date of Patent: May 27, 2014Assignee: SNECMAInventors: Jean-Michel Guimbard, Pierre Marche, Renaud Martet, Renaud Royan
-
Patent number: 8734115Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 28, 2011Date of Patent: May 27, 2014Assignee: SNECMAInventors: Jean Bleuzen, Jean-Michel Guimbard, Pierre Marche, Renaud Martet
-
Publication number: 20140105750Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3 H to 0.8 H, where H is the height of the blade measured from its root to its tip.Type: ApplicationFiled: June 20, 2012Publication date: April 17, 2014Applicant: SNECMAInventors: Renaud Gabriel Constant ROYAN, Renaud Martet, Jean-Michel Guimbard
-
Patent number: 8647066Abstract: A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved.Type: GrantFiled: February 27, 2009Date of Patent: February 11, 2014Assignee: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
-
Publication number: 20120051895Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: ApplicationFiled: June 29, 2011Publication date: March 1, 2012Applicant: SNECMAInventors: Jean-Michel GUIMBARD, Pierre Marche, Renaud Martet, Renaud Royan
-
Publication number: 20120020799Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: ApplicationFiled: June 28, 2011Publication date: January 26, 2012Applicant: SNECMAInventors: Jean BLEUZEN, Jean-Michel Guimbard, Pierre Marche, Renaud Martet
-
Publication number: 20120020800Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: ApplicationFiled: June 28, 2011Publication date: January 26, 2012Applicant: SNECMAInventors: Jean BLEUZEN, Jean-Michel Guimbard, Ludovic Pintat, Pascal Routier
-
Patent number: 8011879Abstract: A transition channel between a first turbine section and a second turbine section for a gas turbine engine is disclosed. The channel includes a first radially external annular wall including ring sector elements housed inside an annular ring and orifices for injecting a fluid into the channel in order to re-energize the boundary layer thereof, a second radially internal annular wall, and a fluid supply device arranged between the space outside the ring and the injection orifices.Type: GrantFiled: October 5, 2007Date of Patent: September 6, 2011Assignee: SNECMAInventors: Jean-Michel Guimbard, Philippe Jean-Pierre Pabion, Eric Schwartz, Jean-Luc Soupizon
-
Publication number: 20110189023Abstract: A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved.Type: ApplicationFiled: February 27, 2009Publication date: August 4, 2011Applicant: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
-
Publication number: 20110110788Abstract: A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface.Type: ApplicationFiled: February 27, 2009Publication date: May 12, 2011Applicant: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
-
Publication number: 20110014056Abstract: A blade for a turbomachine impeller including an airfoil and at least one platform at one end of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring, the platform surface having a suction surface profile and a pressure surface profile respectively along the suction surface and the pressure surface. In the blade, the pressure surface profile including a pressure surface recessed part is located axially in an upstream half of the airfoil. Due to this configuration, efficiency of the blade is improved.Type: ApplicationFiled: February 27, 2009Publication date: January 20, 2011Applicant: SNECMAInventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
-
Patent number: 7527470Abstract: A turbomachine stator vane having a leading edge, a trailing edge, and pressure side and suction side faces, a first and a second series of a plurality of holes, calibrated emission holes, and a perforated open liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air opening for feeding cooling air to the inside of the liner, and an air exhaust opening for exhausting cooling air from the vane, the liner being secured to the vane at one end and being free at another end to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane. The holes through the liner in the second series of holes are disposed to avoid any impact of the cooling air against the bridges of the vane.Type: GrantFiled: June 29, 2005Date of Patent: May 5, 2009Assignee: SnecmaInventors: Jean-Michel Guimbard, Philippe Pabion, Eric Schwartz
-
Publication number: 20070122281Abstract: The layout for cooling a blade (10), said blade (10) having a cavity (12) surrounded by an internal wall (14) comprising cooling fins (24) which are spaced apart from each other by a pitch (p) and each have a thickness (e), said blade (10) having, inside said cavity (12), a jacket (26) passed through by emission holes (28) each having a diameter (d), is characterised in that, when the jacket (26) is in place in the cavity (12) of the blade (10), and in respect of the critical operating point of the turbine engine, each emission hole (28) of the jacket (26) is opposite a place on the internal wall (14) of the blade (10) which is located between cooling fins (24).Type: ApplicationFiled: November 6, 2006Publication date: May 31, 2007Applicant: SNECMAInventors: Alexandre DERVAUX, Jean-Michel Guimbard, Damien Redon, Pascal Bertrand, Papot
-
Patent number: 7137783Abstract: A cooled gas turbine blade includes a foundry part and a longitudinal sleeve obtained by the forming of metal sheet. The foundry part includes a longitudinal body provided with a longitudinal cavity with first and second apertures at its ends. The sleeve is mounted in the cavity being held therein by soldering or brazing to the wall of the first aperture, and an end portion of which is free to slide in the second slide-forming aperture. The end portion and the slide are in sliding contact relatively to surfaces formed by machining. A sealing insert can be positioned between the end portion of the sleeve and the wall of the second aperture. This insert can be integral with the sleeve.Type: GrantFiled: June 29, 2004Date of Patent: November 21, 2006Assignee: Snecma MoteursInventors: Philippe Pabion, Jean-Luc Soupizon, Jean-Michel Guimbard