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1.发明授权ROTOR D'UN COMPRESSEUR DE TURBOMACHINE A PAROI D'EXTREMITE INTERNE OPTIMISEE 有权具有改进的内端转子TURBOMASCHINEN压缩机
公开(公告)号：EP2483565B1
公开(公告)日：2016-01-06
申请号：EP10768209.8
申请日：2010-10-01
发明人： BOSTON, Eric, Jacques , CHARTOIRE, Alexandre, Franck, Arnaud , ILIOPOULOU, Vasiliki , LEPOT, Ingrid , OBRECHT, Thierry, Jean-Jacques
CPC分类号： F04D29/321 , F01D5/143 , F04D29/329 , F05D2240/80 , F05D2250/711 , F05D2250/712 , Y02T50/673
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2.发明公开ROTOR D'UN COMPRESSEUR DE TURBOMACHINE A PAROI D'EXTREMITE INTERNE OPTIMISEE 有权具有改进的内端转子TURBOMASCHINEN压缩机
公开(公告)号：EP2483565A2
公开(公告)日：2012-08-08
申请号：EP10768209.8
申请日：2010-10-01
发明人： BOSTON, Eric, Jacques , CHARTOIRE, Alexandre, Franck, Arnaud , ILIOPOULOU, Vasiliki , LEPOT, Ingrid , OBRECHT, Thierry, Jean-Jacques
CPC分类号： F04D29/321 , F01D5/143 , F04D29/329 , F05D2240/80 , F05D2250/711 , F05D2250/712 , Y02T50/673
摘要： A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.
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公开(公告)号：EP2859239A2
公开(公告)日：2015-04-15
申请号：EP13742668.0
申请日：2013-04-15
申请人： Snecma
CPC分类号： F04D29/526 , F04D19/00 , F04D29/164 , F04D29/541 , F04D29/542 , F04D29/685 , F05D2220/3216
摘要： The invention relates to a compressor for a turbine engine, comprising: a casing, at least one compressor stage formed by an impeller having stationary blades and an impeller having moving blades (1) positioned downstream of the stationary blade impeller, and cavities (5) in the thickness of the casing that are disposed along a circumference of said casing (4) opposite the moving blades (1). The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border (7) and a downstream border (6) are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades (1) such as to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The casing is characterised in that the downstream border (6) of the cavities (5) is oriented parallel to the chord at the head of the moving blade (1).
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公开(公告)号：EP2859240A2
公开(公告)日：2015-04-15
申请号：EP13742669.8
申请日：2013-04-15
申请人： Snecma
CPC分类号： F04D29/547 , F04D17/10 , F04D19/00 , F04D27/0207 , F04D29/164 , F04D29/4206 , F04D29/526 , F04D29/541 , F04D29/685
摘要： The invention relates to a casing for a turbine engine compressor, comprising: cavities (5) in the thickness of the casing, extending in parallel to one another from the inner face of the casing along a circumference thereof, said cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border (7) and a downstream border (6) are formed at the intersections between same and the inner face of the casing (4). The casing is characterised in that the upstream border (7) of the cavities (5) takes the form of a wavy line comprising at least two alternate undulations over the length thereof between the aforementioned side walls. Figure pour l'abrégé : figure
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