公开(公告)号：US20180087389A1

公开(公告)日：2018-03-29

申请号：US15554936

申请日：2016-03-01

申请人： Safran Aircraft Engines

发明人： Philippe Gérard Edmond Joly ,  François Jean Comin ,  Laurent Jablonski ,  Damien Merlot ,  Jean-Marc Claude Perrollaz

IPC分类号： F01D5/34

CPC分类号： F01D5/34 ,  F05D2220/36

摘要： A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.

公开(公告)号：US20170276145A1

公开(公告)日：2017-09-28

申请号：US15507116

申请日：2015-09-03

申请人： Safran Aircraft Engines

发明人： Philippe Gérard Edmond Joly ,  Damien Merlot ,  Jean-Marc Claude Perrollaz

IPC分类号： F04D29/32 ,  F01D5/14 ,  F01D21/04 ,  F01D11/00

CPC分类号： F04D29/324 ,  F01D5/141 ,  F01D5/143 ,  F01D5/3007 ,  F01D11/006 ,  F01D21/045 ,  F05D2220/36 ,  F05D2240/80 ,  F05D2250/73 ,  F05D2260/94 ,  Y02T50/673

摘要： The invention relates to a blade, the platform (14) of which has at least one bumper (40) which rises, on the inner face, from a connection to an intermediate area of the blade located along a longitudinal axis of the blade, between the blade root and the outer face (143), towards a free side edge (145) of the platform. The platform bumper (40) locally has a thinned portion at a distance from said free side edge of the platform.The invention is applicable to turboshaft engine fans.

公开(公告)号：US11333164B2

公开(公告)日：2022-05-17

申请号：US14403003

申请日：2013-05-23

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Hanna Reiss ,  Adrien Biscay ,  Benoit Fayard ,  Laurent Jablonski ,  Damien Merlot

IPC分类号： F04D29/38 ,  F04D29/32 ,  F04D29/66 ,  F01D5/14 ,  F04D19/00

摘要： A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection.

公开(公告)号：US10458257B2

公开(公告)日：2019-10-29

申请号：US15872782

申请日：2018-01-16

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Marco Nucci ,  Damien Merlot ,  Jacky Rodriguez

IPC分类号： F01D5/30 ,  F01D5/14 ,  F01D5/16

摘要： The shank of a blade includes a first side and a second side provided with a depression. By concentrating this depression on a single side, a shank that is more rigid and resistant with an equal lightening is obtained, with the stress concentrations depending on the depth of the depression but being absent from first flat side. The vibrations and bending deformations are also reduced.

公开(公告)号：US11209012B2

公开(公告)日：2021-12-28

申请号：US16393577

申请日：2019-04-24

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Laurent Jablonski ,  Philippe Gérard Edmond Joly ,  Christophe Perdrigeon ,  Damien Merlot ,  Hervé Pohier

IPC分类号： F04D29/32 ,  F01D5/34 ,  F01D5/14 ,  F01D5/30 ,  F01D5/32 ,  F04D19/00 ,  F04D29/02 ,  F04D29/053 ,  F04D29/38

摘要： The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

公开(公告)号：US20190249683A1

公开(公告)日：2019-08-15

申请号：US16393577

申请日：2019-04-24

申请人： Safran Aircraft Engines

发明人： Laurent Jablonski ,  Philippe Gérard Edmond Joly ,  Christophe Perdrigeon ,  Damien Merlot ,  Hervé Pohier

IPC分类号： F04D29/32 ,  F04D29/38 ,  F01D5/34 ,  F04D29/02 ,  F04D19/00 ,  F04D29/053 ,  F01D5/32 ,  F01D5/30 ,  F01D5/14

CPC分类号： F04D29/329 ,  F01D5/14 ,  F01D5/30 ,  F01D5/303 ,  F01D5/3053 ,  F01D5/3069 ,  F01D5/32 ,  F01D5/323 ,  F01D5/34 ,  F04D19/002 ,  F04D29/023 ,  F04D29/053 ,  F04D29/322 ,  F04D29/38 ,  F05D2220/36 ,  Y02T50/671

摘要： The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.