公开(公告)号：US20220025771A1

公开(公告)日：2022-01-27

申请号：US17312244

申请日：2019-11-29

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Léandre OSTINO ,  Pierre Guillaume AUZILLON ,  Romain Pierre CARIOU ,  Thomas Olivier Michel Pierre DE ROCQUIGNY ,  Patrice ENEAU ,  Adrien Bernard Vincent ROLLINGER ,  Vianney SIMON ,  Michel SLUSARZ ,  Ba-Phuc TANG

IPC: F01D5/18

Abstract: A turbine blade including a root carrying an impeller terminated by a tip in the form of a squealer tip. This impeller also includes a serpentine median circuit, including a first radial pipe collecting air at the root and that is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe, a cavity under the squealer tip running along the pressure side wall, extending from a central region of the tip to the trailing edge, and a radial central pipe collecting air at the root extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.

公开(公告)号：US20220170377A1

公开(公告)日：2022-06-02

申请号：US17594071

申请日：2020-03-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Matthieu SIMON ,  Jean-Luc BACHA ,  Paul DANRE ,  Léandre OSTINO

IPC: F01D5/18 ,  F01D9/06

Abstract: A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.

公开(公告)号：US20230098861A1

公开(公告)日：2023-03-30

申请号：US17906300

申请日：2021-03-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Léandre OSTINO ,  Erwan Daniel BOTREL

IPC: F01D5/18

Abstract: A turbomachine turbine blade, includes a platform, a vane, a cooling cavity supplying a plurality of cooling outlets provided along the trailing edge, two radially adjacent cooling outlets defining therebetween a rib. At least one cooling hole is formed in the thickness of at least one rib and/or in the thickness of a portion of the trailing edge fillet located in the axial extension of at least one rib, so as to ensure fluid communication for a cooling flow between the inside and the outside of the blade for cooling the at least one rib.

公开(公告)号：US20220205365A1

公开(公告)日：2022-06-30

申请号：US17595008

申请日：2020-04-24

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Léandre OSTINO ,  Pierre Guillaume AUZILLON ,  Michel SLUSARZ ,  Patrice ENEAU ,  Thomas Olivier Michel Pierre DE ROCQUIGNY ,  Romain Pierre CARIOU ,  Ba-Phuc TANG ,  Adrien Bernard Vincent ROLLINGER ,  Vianney SIMON

IPC: F01D5/18 ,  B22C9/10

Abstract: A turbine vane includes a root carrying a blade terminated by a squealer tip, the blade having intrados and extrados walls, a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall. The blade also includes: a serpentine median circuit, including a first radial pipe that collects air at the root and is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe; a cavity under the squealer tip running along the extrados wall and extending from a central region of the squealer tip to the trailing edge; and a central radial pipe collecting air at the root and extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.

公开(公告)号：US20220170371A1

公开(公告)日：2022-06-02

申请号：US17440853

申请日：2020-03-11

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Michel SLUSARZ ,  Pierre Guillaume AUZILLON ,  Patrice ENEAU ,  Léandre OSTINO

IPC: F01D5/14

Abstract: An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4′) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.