公开(公告)号：US20200063588A1

公开(公告)日：2020-02-27

申请号：US16514027

申请日：2019-07-17

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Vincent Francois Georges MILLIER

IPC: F01D11/00 ,  F01D5/20 ,  F02C7/28

Abstract: The invention relates to a sealing assembly for a turbine (1) rotor of a turbomachine, said turbine comprising an outer casing (4) and a plurality of rotor impellers (3) and nozzles (2), the sealing assembly comprising a sealing ring (7), attached to the casing (4), consisting of a plurality of ring sectors (70a, 70b) and surrounding the impeller (3), a sealing tab (8, 8′) being engaged, in a first slot (73a) of a ring sector (70a) and in a second slot (73b) of an adjacent ring sector (70b).The assembly is remarkable in that an anti-wear foil (5) is mounted in a groove (223) of the nozzle (2), in that the downstream end of the ring sectors (70a, 70b) is engaged in said anti-wear foil (5), in that each of the first and second slots (73a, 73b) comprises a radially outer wall (731a, 731b) and a radially inner wall (732a, 732b) which extend axially and in that the sealing tab (8, 8′) is bent at its downstream end and is disposed in the slots, so that its downstream end extends out of the slots facing the anti-wear foil (5).

公开(公告)号：US20200182058A1

公开(公告)日：2020-06-11

申请号：US16704031

申请日：2019-12-05

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Stéphane Pierre Guillaume BLANCHARD ,  Gaëlle Inès Méganne MOREAUX

IPC: F01D3/02 ,  F01D9/06 ,  F01D5/08

Abstract: A device for holding (101) at least one cooling tube (120) of a turbomachine casing (10) cooling system (100), the holding device including a fixing frame (104), a holding member (160) being configured to hold two cooling tubes (120), and a connection assembly (140) between the holding member (160) and a fixing frame (104), extending on either side of the frame, the connection assembly (160) comprising a connection part (150) extending through an opening (108) of the fixing frame from an outer portion (141) to the inner portion (142) of the connection assembly, the inner portion (142) being disposed between two cooling tubes (120) and secured to the holding member (160) while the outer portion (141) comprises a resilient return member (170) urged in compression towards the fixing frame by the connection part (150).

公开(公告)号：US20200011194A1

公开(公告)日：2020-01-09

申请号：US16459406

申请日：2019-07-01

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Renaud James MARTET ,  Vincent Francois Georges MILLIER

IPC: F01D11/12

Abstract: Turbine engine turbine sealing module extending about an axis and including a distributor fixed to a casing, and at least one blade connected to an outer platform. The turbine module further includes an impeller mounted rotating inside the casing and surrounded by a sealing ring fastened to this casing. The sealing ring includes an annular row of ring sectors arranged such that the circumferential end edges of two adjacent sectors are facing one another. Each sector includes a body configured to engage with at least one seal lip carried by the impeller and a hook which extends circumferentially which is configured to engage with a fastening rail of the casing. Each ring sector further includes a deflector which extends radially inwards and upstream with respect to the axis, such that the radially inward end thereof extends around a downstream end of the outer platform of the distributor.

公开(公告)号：US20230212953A1

公开(公告)日：2023-07-06

申请号：US17922288

申请日：2021-04-28

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Thierry FACHAT ,  Alain Dominique GENDRAUD

IPC: F01D11/00 ,  F01D9/04 ,  F01D11/12 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D9/042 ,  F01D11/122 ,  F01D25/243 ,  F05D2240/11

Abstract: The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring (66) placed between the upstream casing and the downstream casing and fastening means (68) for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading (48a) of the turbine engine is mounted on a downstream hook (480b) of the upstream casing, without being hooked onto the shroud ring (66), and the downstream casing (58) has an upstream hook with which the sealing element (62) is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element (62) is mounted so as to be fastened to the downstream casing.

公开(公告)号：US20220228504A1

公开(公告)日：2022-07-21

申请号：US17633834

申请日：2020-08-06

Applicant: Safran Aircraft Engines

Inventor： Simon Nicolas MORLIERE ,  Stéphane Pierre Guillaume BLANCHARD ,  Nicolas Jean-Marc Marcel BEAUQUIN

IPC: F01D11/24 ,  F01D25/12

Abstract: The present invention relates to a device for cooling, using air jets, an external casing of a turbomachine, comprising a housing for supplying air to cooling tubes of said casing, the housing being provided with an attachment device on the external casing. According to the invention, said attachment device comprises two upstream ball joint retention devices which each connect the housing to the external casing.

公开(公告)号：US20230184126A1

公开(公告)日：2023-06-15

申请号：US17996038

申请日：2021-04-12

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Stéphane Sylvain BOIS ,  Sébastien Philippe Edith BOURGEOIS

IPC: F01D11/12 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D11/122 ,  F01D9/04 ,  F01D25/24 ,  F05D2220/323 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2240/55

Abstract: A turbine for a turbine engine extending along an axis includes an annular casing and at least one turbine stage having a nozzle and a rotor impeller wheel surrounded by a sealing ring with an abradable element. The impeller wheel and the sealing ring are located downstream of the nozzle, and the sealing ring has an upstream end held on the casing by locking means. The turbine includes elastic sealing means in contact with the locking means as well as with the nozzle or the casing so as to press the locking means against the sealing ring. The locking means includes a radially outer portion with a C-shaped cross-section and a radial portion extending radially inwards from the outer portion. The sealing means include two elastic seals bearing on the radial portion, respectively on either side of the radial portion.

公开(公告)号：US20220290579A1

公开(公告)日：2022-09-15

申请号：US17634159

申请日：2020-08-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Simon Nicolas MORLIERE ,  Stéphane Pierre Guillaume BLANCHARD ,  Nicolas Jean-Marc Marcel BEAUQUIN ,  Alain Dominique GENDRAUD ,  Olivier RENON

IPC: F01D25/14 ,  F01D25/12

Abstract: The invention relates to an assembly (25) for a turbomachine turbine comprising a casing (18) including an annular wall (26) extending about an axis, and means of cooling the casing (18), the said means of cooling comprising a collector housing (22) and at least one tube (23) extending circumferentially around the annular wall (26) of the casing (18) and connected to the housing (22), with the tube (23) comprising cooling-air ejection orifices.

公开(公告)号：US20190226357A1

公开(公告)日：2019-07-25

申请号：US16253842

申请日：2019-01-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Jean-Marc Marcel BEAUQUIN

IPC: F01D25/14 ,  F01D9/06

Abstract: The invention concerns a cooling device (21) extending circumferentially around a turbo machine housing, such as a turbine housing, having at least one cooling module (30a, 30b, 30c) comprising a tube holder (31, 32) having at least one plate, preferably a radially inner plate (31) and a radially outer plate (32) fixed to each other, the tube holder (31, 32) defining at least two axially spaced housings (34a), each housing (34a) receiving a tube (23) and a sleeve (38) mounted around each tube (23), each tube (23) extending circumferentially around the housing, each cooling module (30a, 30b, 30c) having first fastening means capable of firmly holding its tube holder (31, 32) with respect to the housing, the fixing means comprising at least one spacer (41) having a radially inner end intended to bear against the housing and a radially outer end bearing on the single or on one of the sheets of the tube support (31, 32).