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：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：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.

公开(公告)号：US20220268160A1

公开(公告)日：2022-08-25

申请号：US17629482

申请日：2020-07-24

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Michel SLUSARZ ,  Patrice ENEAU ,  Charlotte Marie DUJOL

IPC: F01D5/18

Abstract: A blade for a turbomachine, extending longitudinally between a base and an apex, comprising a lower surface wall, an upper surface wall, a leading edge and a trailing edge and comprising a plurality of internal ventilation cavities which form a cooling circuit of the blade, wherein at least one ventilation cavity is a ventilation cavity of a first type comprising at least one ascending portion which extends substantially longitudinally between the base and the apex, engaged with the lower surface wall and spaced from the upper surface wall, and at least one discharge portion which extends substantially transversely and which opens at the trailing edge via at least one port of the trailing edge, and wherein at least one ventilation cavity of the first type further comprises at least one descending portion which extends substantially longitudinally from the apex, engaged with the upper surface wall and spaced from the lower

公开(公告)号：US20240125238A1

公开(公告)日：2024-04-18

申请号：US18264847

申请日：2022-02-03

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Michel SLUSARZ ,  Kevin Michael MUGNIER

IPC: F01D5/18 ,  F01D25/12 ,  F23R3/00

CPC classification number: F01D5/186 ,  F01D25/12 ,  F23R3/002 ,  F05D2260/202

Abstract: A turbomachine component such as a blade, includes a wall provided with at least one cooling hole having a metering portion and a tapered diffusion portion. The diffusion portion includes a central edge forming a bottom of the diffusion portion that is oblique with respect to a flow axis of the cooling hole.

公开(公告)号：US20220316344A1

公开(公告)日：2022-10-06

申请号：US17597549

申请日：2020-07-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Patrice ENEAU ,  Michel SLUSARZ

IPC: F01D5/18 ,  F01D5/30

Abstract: The invention relates to a movable turbomachine blade comprising at least one cooling circuit comprising at least one cavity extending radially between the root and the tip, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots arranged to open out along the trailing edge between the root and the tip, and a plurality of second discharge slots separate from the first discharge slots and arranged along the trailing edge between the root and the tip, the second discharge slots being offset axially upstream relative to the first discharge slots and each of the first discharge slots being radially offset relative to each of the second discharge slots, with no overlap between the first and second discharge slots.

公开(公告)号：US20200300098A1

公开(公告)日：2020-09-24

申请号：US16819420

申请日：2020-03-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Michel SLUSARZ ,  Patrice Eneau

IPC: F01D5/18

Abstract: A turbine vane including at least one inner cavity including a plurality of deflectors which are carried by an inner face of the lower surface wall and by an inner face of the upper surface wall, wherein each deflector extends mainly in a transverse direction from the inner face of the lower surface wall or from the inner face of the upper surface wall, in the direction of the other one of the lower surface wall or the upper surface wall, and wherein the length of each deflector in the transverse direction is greater than half the transverse distance between the inner face of the lower surface wall and the inner face of the upper surface wall, on either side of the deflector.