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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: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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