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公开(公告)号：US20180258779A1
公开(公告)日：2018-09-13
申请号：US15914150
申请日：2018-03-07
发明人： Mohamed-Lamine Boutaleb , Fabien Roger Gaston Caty , Sebastien Vincent Francois Dreano , Thierry Georges Paul Papin , Christophe Marcel Lucien Perdrigeon , Cedric Zaccardi
摘要： The invention relates to a guide vane for a twin-spool aircraft turbomachine, of which the aerodynamic part (32) comprises an internal lubricant cooling passage (50a) extending along a principal lubricant flow direction (52a).According to the invention, the aerodynamic part is made in a single piece and also comprises heat transfer fins (80a, 80b) arranged in the passage (50a) connecting the intrados and extrados walls (70, 72) and extending approximately parallel to the direction (52a), these fins being distributed in successive rows along the principal direction (52a) and made such that for two rows (R1, R2) of staggered directly consecutive fins, the row (R1) comprises fins (80a) forming a positive acute angle A1 with a dummy reference plane (Pf), while the row (R2) comprises fins (80b) forming a negative acute angle A2 with this plane (Pf).
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公开(公告)号：US11828183B2
公开(公告)日：2023-11-28
申请号：US17783629
申请日：2020-12-01
发明人： Paul Ghislain Albert Levisse , Olivier Belmonte , Fabien Roger Gaston Caty , Amelie Argie Antoinette Chassagne
CPC分类号： F01D1/24 , F01D11/005 , F01D25/00 , F05D2260/40311 , F05D2260/98
摘要： Disclosed is a turbomachine (10) with counter-rotating turbine for an aircraft, comprising: —a high-pressure body, —a low-pressure counter-rotating turbine (22), —a planetary-type mechanical epicyclic reduction gear (42), —a guide bearings (56-62) for the turbine shafts (36, 38), characterised in that said reduction gear (42) and certain of the bearings (60, 62) are housed in a lubrication chamber (86) supplied with oil and comprising dynamic seals (86a-86d), and in that the turbomachine comprises circuits (C1, C2) for pressurising these seals.
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公开(公告)号：US20230008678A1
公开(公告)日：2023-01-12
申请号：US17783629
申请日：2020-12-01
发明人： Paul Ghislain Albert Levisse , Olivier Belmonte , Fabien Roger Gaston Caty , Amelie Argie Antoinette Chassagne
摘要： Disclosed is a turbo machine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bearings (56-62) for the turbine shafts (36, 38), characterised in that said reduction gear (42) and certain of the bearings (60, 62) are housed in a lubrication chamber (86) supplied with oil and comprising dynamic seals (86a-86d), and in that the turbo machine comprises circuits (C1, C2) for pressurising these seals.
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公开(公告)号：US11377978B2
公开(公告)日：2022-07-05
申请号：US16778643
申请日：2020-01-31
摘要： A ventilated chamber (19), subject to an irruption of air at a pressure higher than that in a surrounding chamber (20) through labyrinth seals separating them and evacuation of excess air through an evacuation duct (30), comprises a motor-driven compressor (32) in the evacuation duct to facilitate suction and evacuation, even when the engine speed does not allow a large overpressure in the chamber (20).
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公开(公告)号：US11852025B2
公开(公告)日：2023-12-26
申请号：US17760173
申请日：2021-03-15
CPC分类号： F01D25/12 , F01D5/081 , F01D9/065 , F01D17/141 , F01D17/145 , F02C6/08 , F02C9/18 , F02C3/13 , F05D2260/20 , F05D2270/3015 , F05D2300/50212
摘要： A turbo machine including a device for ventilating and pressurising a turbine rotor of a turbomachine having an axis, the device including at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber inside the turbomachine that communicates with a second inner chamber delimited by the turbine rotor, the first and second chambers being at least partially separated by a stationary shroud having the axis, wherein it includes at least one injector passing through the stationary shroud and having a cross-section that varies in response to a pressure difference between the first and second chambers.
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公开(公告)号：US10697312B2
公开(公告)日：2020-06-30
申请号：US15914150
申请日：2018-03-07
发明人： Mohamed-Lamine Boutaleb , Fabien Roger Gaston Caty , Sebastien Vincent Francois Dreano , Thierry Georges Paul Papin , Christophe Marcel Lucien Perdrigeon , Cedric Zaccardi
IPC分类号： F01D9/06 , F01D9/04 , F01D25/12 , F01D25/18 , F02C7/14 , F28D21/00 , F01D5/18 , F28F1/40 , F28D1/02 , F28D1/053
摘要： A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.
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