Patents by Inventor David Depaepe
David Depaepe 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: 9739154Abstract: The present application relates to the compressor stator of an axial turbomachine. The stator comprises an annular row of main stator blades and auxiliary blades each of which are associated with a main blade. The auxiliary blades are located at the trailing edges of the main blades and are in the vicinity of the pressure faces of the main blades. The auxiliary blades are aligned to generate a low-pressure area at the trailing edges of the main blades. Thus, a flow bypassing a main blade by its suction face is sucked in by the low-pressure area when it approaches the trailing edge of the main blade. Stalling is thus avoided and the efficiency of the machine is improved.Type: GrantFiled: May 2, 2014Date of Patent: August 22, 2017Assignee: Safran Aero Boosters SAInventors: Alain Derclaye, David Depaepe
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Patent number: 9695701Abstract: The present application relates to a bladed stator of a turbomachine compressor, configured to straighten an annular stream of the turbomachine. The stator includes at least one annular wall configured to define the annular stream, a row of blades extending radially from the annular wall and means of pressurizing in communication with the annular stream. The means of pressurizing are configured to pressurize a chamber which is separated from a lubrication housing by a labyrinth seal. The means of pressurizing comprise at least one passage extending through the thickness of the annular wall and connecting with the annular stream. The means of pressurizing further includes at least one scoop in communication with the passage and the annular stream. The scoop is open upstream so as to capture the dynamic pressure of the annular stream.Type: GrantFiled: May 13, 2014Date of Patent: July 4, 2017Assignee: Safran Aero Boosters SAInventor: David Depaepe
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Patent number: 8967958Abstract: A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate.Type: GrantFiled: December 17, 2010Date of Patent: March 3, 2015Assignee: Techspace Aero S.A.Inventors: Denis Bajusz, David Depaepe, Jacques Charlier, Nicolas Raimarckers
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Patent number: 8899917Abstract: The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.Type: GrantFiled: March 26, 2012Date of Patent: December 2, 2014Assignee: Techspace Aero S.A.Inventors: Denis Bajusz, Nicholas Raimarckers, Antoine Stephany, Georges Broers, Yves Culot, Marc Strengnart, Albert Cornet, David Depaepe
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Publication number: 20140334915Abstract: The present application relates to a bladed stator of a turbomachine compressor, configured to straighten an annular stream of the turbomachine. The stator includes at least one annular wall configured to define the annular stream, a row of blades extending radially from the annular wall and means of pressurizing in communication with the annular stream. The means of pressurizing are configured to pressurize a chamber which is separated from a lubrication housing by a labyrinth seal. The means of pressurizing comprise at least one passage extending through the thickness of the annular wall and connecting with the annular stream. The means of pressurizing further includes at least one scoop in communication with the passage and the annular stream. The scoop is open upstream so as to capture the dynamic pressure of the annular stream.Type: ApplicationFiled: May 13, 2014Publication date: November 13, 2014Applicant: Techspace Aero S.A.Inventor: David Depaepe
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Publication number: 20140328675Abstract: The present application relates to the compressor stator of an axial turbomachine. The stator comprises an annular row of main stator blades and auxiliary blades each of which are associated with a main blade. The auxiliary blades are located at the trailing edges of the main blades and are in the vicinity of the pressure faces of the main blades. The auxiliary blades are aligned to generate a low-pressure area at the trailing edges of the main blades. Thus, a flow bypassing a main blade by its suction face is sucked in by the low-pressure area when it approaches the trailing edge of the main blade. Stalling is thus avoided and the efficiency of the machine is improved.Type: ApplicationFiled: May 2, 2014Publication date: November 6, 2014Applicant: Techspace Aero S.A.Inventors: Alain Derclaye, David Depaepe
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Patent number: 8601791Abstract: Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.Type: GrantFiled: December 23, 2010Date of Patent: December 10, 2013Assignee: Techspace Aero S.A.Inventors: Denis Bajusz, David Depaepe, Alain Derclaye, Régis Dupuy
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Publication number: 20120251373Abstract: The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.Type: ApplicationFiled: March 26, 2012Publication date: October 4, 2012Applicant: TECHSPACE AERO S.A.Inventors: Denis Bajusz, Yves Culot, Marc Strengnart, Antoine Stephany, David Depaepe, Albert Cornet, Nicolas Raimarckers, Georges Broers
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Publication number: 20110150634Abstract: A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate.Type: ApplicationFiled: December 17, 2010Publication date: June 23, 2011Inventors: Denis Bajusz, David Depaepe, Jacques Charlier, Nicolas Raimarckers
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Publication number: 20110146229Abstract: Setting in place of one or several coolers in the wall of a secondary flow of a bypass turbomachine. The wall extends from an intermediate casing toward a leading edge of a separator nose between a primary flow and the secondary flow. The wall includes a series of support arms attached to an intermediate casing, distributed over the perimeter of the wall and directed upstream. A series of surface air-oil heat exchangers forming wall segments are arranged end-to-end on the support arms, so as to form an annular wall. A shroud having a leading edge is arranged and fixed in the area of the upstream edges of the heat exchangers, so as to complete the wall. The support arms include hydraulic connectors connected to one another on each arm, adapted to cooperate with corresponding connectors in the area of the heat exchangers and in the area of the intermediate casing.Type: ApplicationFiled: December 23, 2010Publication date: June 23, 2011Inventors: Denis Bajusz, David Depaepe, Alain Derclaye, Régis Dupuy