Patents by Inventor Hanna Reiss
Hanna Reiss 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: 11333164Abstract: A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection.Type: GrantFiled: May 23, 2013Date of Patent: May 17, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Hanna Reiss, Adrien Biscay, Benoit Fayard, Laurent Jablonski, Damien Merlot
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Patent number: 10844735Abstract: A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.Type: GrantFiled: June 9, 2017Date of Patent: November 24, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pradeep Cojande, Hanna Reiss
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Patent number: 10221692Abstract: An outlet guide vane for a turbine engine, the vane having a plurality of vane sections stacked along a radial axis Z. Over a bottom portion of the vane in the range 0 to 50% of its total height, the leading edge of each section is in front of the leading edge of the corresponding section at the total height, and the maximum thicknesses are located at positions that are offset from the leading edge by at least 50% of the chord.Type: GrantFiled: August 4, 2014Date of Patent: March 5, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pradeep Cojande, Eric Pierre Maurice Lippinois, Hanna Reiss
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Patent number: 9995156Abstract: A turbomachine vane including a plurality of vane sections stacked along a radial axis, each vane section extending along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between an active surface and a passive surface, the vane sections being distributed according to longitudinal and tangential distribution laws defining positioning of respective centers of gravity thereof in relation to the longitudinal and tangential axes according to a height of the vane extending from a foot of the vane to a top thereof. Each of the longitudinal and tangential distribution laws involves a change in direction of the slope at between 90% and 100% of the height of the vane.Type: GrantFiled: June 28, 2013Date of Patent: June 12, 2018Assignee: SNECMAInventors: Laurent Jablonski, Hanna Reiss, Jerome Talbotec, Sandrine Quevreux
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Publication number: 20170276004Abstract: A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.Type: ApplicationFiled: June 9, 2017Publication date: September 28, 2017Applicant: SNECMAInventors: Pradeep COJANDE, Hanna REISS
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Patent number: 9759234Abstract: A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm.Type: GrantFiled: June 17, 2011Date of Patent: September 12, 2017Assignee: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Hanna Reiss, Jean-Francois Rios
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Patent number: 9677404Abstract: A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.Type: GrantFiled: October 8, 2012Date of Patent: June 13, 2017Assignee: SNECMAInventors: Didier Merville, Lucie Galons, Vincent Perrot, Hanna Reiss
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Publication number: 20160194962Abstract: An outlet guide vane for a turbine engine, the vane having a plurality of vane sections stacked along a radial axis Z. Over a bottom portion of the vane in the range 0 to 50% of its total height, the leading edge of each section is in front of the leading edge of the corresponding section at the total height, and the maximum thicknesses are located at positions that are offset from the leading edge by at least 50% of the chord.Type: ApplicationFiled: August 4, 2014Publication date: July 7, 2016Applicant: SNECMAInventors: Pradeep COJANDE, Eric Pierre Maurice LIPPINOIS, Hanna REISS
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Publication number: 20150226074Abstract: A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.Type: ApplicationFiled: June 28, 2013Publication date: August 13, 2015Applicant: SNECMAInventors: Pradeep Cojande, Hanna Reiss
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Publication number: 20150192024Abstract: A turbomachine vane including a plurality of vane sections stacked along a radial axis, each vane section extending along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between an active surface and a passive surface, the vane sections being distributed according to longitudinal and tangential distribution laws defining positioning of respective centers of gravity thereof in relation to the longitudinal and tangential axes according to a height of the vane extending from a foot of the vane to a top thereof. Each of the longitudinal and tangential distribution laws involves a change in direction of the slope at between 90% and 100% of the height of the vane.Type: ApplicationFiled: June 28, 2013Publication date: July 9, 2015Applicant: SNECMAInventors: Laurent Jablonski, Hanna Reiss, Jerome Talbotec, Sandrine Quevreux
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Publication number: 20150152880Abstract: A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection.Type: ApplicationFiled: May 23, 2013Publication date: June 4, 2015Applicant: SNECMAInventors: Hanna Reiss, Adrien Biscay, Benoit Fayard, Laurent Jablonski, Damien Merlot
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Publication number: 20140248155Abstract: A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.Type: ApplicationFiled: October 8, 2012Publication date: September 4, 2014Applicant: SNECMAInventors: Didier Merville, Lucie Galons, Vincent Perrot, Hanna Reiss
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Publication number: 20130058776Abstract: A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm.Type: ApplicationFiled: June 17, 2011Publication date: March 7, 2013Applicant: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Hanna Reiss, Jean-Francois Rios