Patents by Inventor Armel Touyeras
Armel Touyeras 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: 9181962Abstract: A compressor including at least one cascade of fixed vanes, the vanes of which are mounted on a wall and between them form air-flow passages, and an air bleed system which bleeds air from the passages between two vanes, through openings made in the wall, the openings being discontinuous and each including a plurality of orifices arranged one behind the other in a direction of the air flow. An upstream orifice of each opening has a larger cross-sectional area than downstream orifices of the opening, and a number and cross section of the downstream orifices are adjusted to suit a predetermined bleed-off flow rate.Type: GrantFiled: April 5, 2011Date of Patent: November 10, 2015Assignee: SNECMAInventor: Armel Touyeras
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Patent number: 9074605Abstract: A turbine engine compressor, including a first housing for supporting injectors, a second housing arranged around the first housing while forming with the first housing an annular space therewith, and a plurality of air injectors each mounted in recesses. Each air injector includes at least one inner air injection channel which leads, on one side, into an outflow jet of the gas stream and, on the other side, into the space formed between the recesses, and, at an upstream end, an upstream rim having an inner surface radially bearing against an upstream rim of the corresponding recess of the first housing and an outer surface radially bearing against an inner surface of the second housing. A mechanism clamping the upstream rim of the air injectors between the housings enables the air injectors to be held in position in the recesses of the first housing.Type: GrantFiled: August 20, 2010Date of Patent: July 7, 2015Assignee: SNECMAInventors: Michel André Bouru, Laurent Jablonski, Armel Touyeras
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Patent number: 8882443Abstract: A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.Type: GrantFiled: May 28, 2009Date of Patent: November 11, 2014Assignee: SNECMAInventors: Xavier Agneray, Alexandre Chartoire, Armel Touyeras, Julien Loucheux
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Patent number: 8845269Abstract: The invention relates to a compressor for a turbine engine including a casing (4), at least one compressor stage consisting of a stationary blade (2) impeller and a mobile blade (1) impeller positioned upstream from said stationary blade (2) impeller, and cavities (5) made in said casing opposite the through-path of the mobile blades (1), said cavities having a length L2 measured axially and being shifted upstream relative to the blades (1) so as to generate an overlap with a length L1, characterized in that the lengths L1 and L2 are respectively between 35% and 50% and between 80% and 90% of the axial chord Cax measured at the outer end of the blades (1), and in that the cavities (5) do not in communication with one another.Type: GrantFiled: December 16, 2009Date of Patent: September 30, 2014Assignee: SNECMAInventors: Xavier Jean Yves Alain Agneray, Jerome Jean Bert, Alexandre Franck Arnaud Chartoire, Armel Touyeras
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Publication number: 20130022452Abstract: A compressor including at least one cascade of fixed vanes, the vanes of which are mounted on a wall and between them form air-flow passages, and an air bleed system which bleeds air from the passages between two vanes, through openings made in the wall, the openings being discontinuous and each including a plurality of orifices arranged one behind the other in a direction of the air flow. An upstream orifice of each opening has a larger cross-sectional area than downstream orifices of the opening, and a number and cross section of the downstream orifices are adjusted to suit a predetermined bleed-off flow rate.Type: ApplicationFiled: April 5, 2011Publication date: January 24, 2013Applicant: SNECMAInventor: Armel Touyeras
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Publication number: 20120201654Abstract: A turbine engine compressor, including a first housing for supporting injectors, a second housing arranged around the first housing while forming with the first housing an annular space therewith, and a plurality of air injectors each mounted in recesses. Each air injector includes at least one inner air injection channel which leads, on one side, into an outflow jet of the gas stream and, on the other side, into the space formed between the recesses, and, at an upstream end, an upstream rim having an inner surface radially bearing against an upstream rim of the corresponding recess of the first housing and an outer surface radially bearing against an inner surface of the second housing. A mechanism clamping the upstream rim of the air injectors between the housings enables the air injectors to be held in position in the recesses of the first housing.Type: ApplicationFiled: August 20, 2010Publication date: August 9, 2012Applicant: SNECMAInventors: Michel André Bouru, Laurent Jablonski, Armel Touyeras
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Publication number: 20120003085Abstract: The invention relates to a compressor for a turbine engine including a casing (4), at least one compressor stage consisting of a stationary blade (2) impeller and a mobile blade (1) impeller positioned upstream from said stationary blade (2) impeller, and cavities (5) made in said casing opposite the through-path of the mobile blades (1), said cavities having a length L2 measured axially and being shifted upstream relative to the blades (1) so as to generate an overlap with a length L1, characterised in that the lengths L1 and L2 are respectively between 35% and 50% and between 80% and 90% of the axial chord Cax measured at the outer end of the blades (1), and in that the cavities (5) do not in communication with one another.Type: ApplicationFiled: December 16, 2009Publication date: January 5, 2012Applicant: SNECMAInventors: Xavier Jean Yves Alain Agneray, Jerome Jean Bert, Alexandre Franck Arnaud Chartoire, Armel Touyeras
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Publication number: 20110076133Abstract: A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.Type: ApplicationFiled: May 28, 2009Publication date: March 31, 2011Applicant: SnecmaInventors: Xavier Agneray, Alexandre Chartoire, Armel Touyeras, Julien Loucheux
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Patent number: 7549838Abstract: A turbomachine compressor comprises at least one plurality of moving blades and spaced apart therefrom in an axial direction relative to a central longitudinal axis of the turbomachine, a plurality of stationary vanes, and a stationary casing surrounding said plurality of moving blades and including a plurality of bleed holes centered in the range 5% to 50% of the blade chord length and having a diameter less than or equal to 30% of the blade chord length, each bleed hole sloping at two angles of inclination relative to the central longitudinal axis. Advantageously, each bleed hole has a first axis of inclination presenting an angle ? relative to the central longitudinal axis lying in the range 30° to 90°, and a second axis of inclination perpendicular to the first and presenting an angle ? relative to the central longitudinal axis lying in the range 30° to 90°.Type: GrantFiled: February 8, 2006Date of Patent: June 23, 2009Assignee: SnecmaInventor: Armel Touyeras
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Publication number: 20060182623Abstract: A turbomachine compressor comprises at least one plurality of moving blades and spaced apart therefrom in an axial direction relative to a central longitudinal axis of the turbomachine, a plurality of stationary vanes, and a stationary casing surrounding said plurality of moving blades and including a plurality of bleed holes centered in the range 5% to 50% of the blade chord length and having a diameter less than or equal to 30% of the blade chord length, each bleed hole sloping at two angles of inclination relative to the central longitudinal axis. Advantageously, each bleed hole has a first axis of inclination presenting an angle ? relative to the central longitudinal axis lying in the range 30° to 90°, and a second axis of inclination perpendicular to the first and presenting an angle ? relative to the central longitudinal axis lying in the range 30° to 90°.Type: ApplicationFiled: February 8, 2006Publication date: August 17, 2006Applicant: SNECMAInventor: Armel Touyeras