公开(公告)号：US20240151151A1

公开(公告)日：2024-05-09

申请号：US18278803

申请日：2022-02-23

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN HELICOPTER ENGINES

Inventor： Bertrand Guillaume, Robin PELLATON ,  Thibaud Louis ZAIA

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D25/24 ,  F05D2270/3062

Abstract: A turbine for a turbomachine of longitudinal axis including an alternating arrangement of annular rows of movable blades and of fixed blades and a radially inner annular cavity formed radially inside the movable and fixed blades, and a supply circuit for supplying cooling air to the inner annular cavity, the downstream end of the supply circuit comprising an inner annular row of orifices and an outer annular row of orifices opening into the radially inner annular cavity. The turbine may also include means for controlling the flow rate of supply air to the orifices of the inner and outer annular rows of orifices.

公开(公告)号：US20230160319A1

公开(公告)日：2023-05-25

申请号：US17919184

申请日：2021-04-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Benoit Guillaume SILET ,  Stéphane Pierre Fuillaume BLANCHARD ,  Fabien Stéphane GARNIER ,  Thibaud Louis ZAIA

IPC: F01D25/14 ,  F01D25/12

CPC classification number: F01D25/14 ,  F01D25/12 ,  F05D2260/60

Abstract: A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.