Patents by Inventor Pradeep Cojande
Pradeep Cojande 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: 11492968Abstract: A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.Type: GrantFiled: October 2, 2018Date of Patent: November 8, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Benjamin Bulot, Pradeep Cojande, Eva Julie Lebeault
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Patent number: 11047300Abstract: A disclosed propulsion unit includes a pylon having a blade presenting a chord Cx and a downstream arm having a structural arm. The pylon has a first distance D between a trailing edge of a fan blade and a leading edge of the fan blade, a second distance d between said trailing edge of the blade and a leading edge of the structural arm, and a third distance L between the trailing edge of the blade and a mark located at a maximum thickness of the downstream arm. The pylon is dimensioned according to: a first quotient between D and Cx between 2.2 and 2.6, a second quotient between d and Cx between 1 and 1.2, and a third quotient between L and Cx between 4 and 7.Type: GrantFiled: November 21, 2018Date of Patent: June 29, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Hélène Madeleine Nicole Deparis, Pierre Grégoire Anton, Pradeep Cojande, Ghislain Maxime Romuald Madiot
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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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Publication number: 20200232393Abstract: A discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprises an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one discharge inlet opening to at least one secondary outlet opening, and comprising an ejection grill (32) arranged at the outlet end (42), the ejection grill (32) comprising a plurality of fins (43), characterised in that the fins (43) comprise flow channels (44) for a fluid to be cooled, so as to form a heat exchange system.Type: ApplicationFiled: October 2, 2018Publication date: July 23, 2020Inventors: Benjamin BULOT, Pradeep COJANDE, Eva Julie LEBEAULT
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Publication number: 20190153940Abstract: A disclosed propulsion unit includes a pylon having a blade presenting a chord Cx and a downstream arm having a structural arm. The pylon has a first distance D between a trailing edge of a fan blade and a leading edge of the fan blade, a second distance d between said trailing edge of the blade and a leading edge of the structural arm, and a third distance L between the trailing edge of the blade and a mark located at a maximum thickness of the downstream arm. The pylon is dimensioned according to: a first quotient between D and Cx between 2.2 and 2.6, a second quotient between d and Cx between 1 and 1.2, and a third quotient between L and Cx between 4 and 7.Type: ApplicationFiled: November 21, 2018Publication date: May 23, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Hélène Madeleine Nicole Deparis, Pierre Grégoire Anton, Pradeep Cojande, Ghislain Maxime Romuald Madiot
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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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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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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