公开(公告)号：EP3734025B1

公开(公告)日：2025-01-01

申请号：EP19171955.8

申请日：2019-04-30

Inventor： KAKAR, Sukesh ,  KUMAR, Gaurav ,  PAUL, Sayantan ,  SHUKLA, Nidhi ,  SINGH, Paramdeep

IPC: F01D25/26

公开(公告)号：EP4435233A1

公开(公告)日：2024-09-25

申请号：EP24163816.2

申请日：2024-03-15

Applicant: Cummins Ltd

Inventor： Gentle, Christopher ,  Eastwood, David Michael ,  Dickson, Jonathan ,  Nirgude, Pravin ,  Gehlot, Sarendra S. ,  Sonar, Kalpeshbapu

IPC: F01D9/02 ,  F01D25/24 ,  F01D25/26

CPC classification number: F01D25/24 ,  F01D9/026 ,  F05D2220/4020130101 ,  F01D25/243 ,  F01D25/26

Abstract: There is disclosed a turbine housing 2 for a turbomachine. The turbine housing 2 comprises a volute 6 which extends around an axis 22 and defines at least part of a flow passage 24 through the turbine housing 2. The flow passage 24 extends from a first inlet opening 12. The turbine housing 2 further comprises a flange 4 that surrounds the first inlet opening 12, and an external surface 26 that defines a rib 28. The rib 28 defines a first portion 30 that adjoins the flange 4, and a second portion 32 that is angled with respect to the first portion 30.

公开(公告)号：EP4410453A3

公开(公告)日：2024-09-25

申请号：EP24183135.3

申请日：2021-10-29

Applicant: RTX Corporation

Inventor： BINEK, Lawrence A. ,  LYDA, Randolph T.

IPC: F01D25/24 ,  F01D25/26 ,  B33Y80/00 ,  B22F5/00

CPC classification number: F01D25/24 ,  F05D2230/5320130101 ,  F01D25/26 ,  B33Y80/00 ,  F05D2240/1420130101 ,  B22F2998/0020130101 ,  B22F10/28 ,  B22F5/009 ,  Y02P10/25

Abstract: An assembly is provided for a gas turbine engine (20). This gas turbine engine (20) assembly includes a split case structure (62). The split case structure (62) includes a first wall (56), a second wall (56), a first case segment (98A) and a second case segment (98B). The first wall (56) extends axially along and circumferentially about an axial centerline (22). The second wall (56) extends axially along and circumferentially about the axial centerline (22). The second wall (56) is radially outboard of and axially overlaps the first wall (56). The first case segment (98A) is configured to form a first portion (158A) of the first wall (56) and a first portion (158A) of the second wall (56). The second case segment (98B) is configured to form a second portion (158B) of the first wall (56) and a second portion (158B) of the second wall (56). The second case segment (98B) is circumferentially adjacent and attached to the first case segment at a joint.

公开(公告)号：EP3929401B1

公开(公告)日：2024-08-07

申请号：EP21178501.9

申请日：2021-06-09

IPC: F01D5/08 ,  F01D25/26

CPC classification number: F01D5/085 ,  F01D25/26 ,  F05D2240/6320130101 ,  F05D2240/6120130101 ,  F05D2220/3220130101 ,  F05D2260/23220130101 ,  F05D2220/7620130101

公开(公告)号：EP3862539B1

公开(公告)日：2024-05-08

申请号：EP21155059.5

申请日：2021-02-03

IPC: F01D9/06 ,  F01D25/12 ,  F01D25/14 ,  F01D25/26 ,  F02C7/18 ,  F02C6/08

CPC classification number: F05D2240/8120130101 ,  F01D25/14 ,  F01D25/12 ,  F01D9/06 ,  F01D25/26 ,  F02C6/08 ,  F05D2260/60620130101 ,  F05D2260/3720130101 ,  F05D2260/20120130101 ,  F05D2260/20520130101 ,  F05D2240/12620130101 ,  Y02T50/60

公开(公告)号：EP3850194B1

公开(公告)日：2023-09-13

申请号：EP19795107.2

申请日：2019-10-15

Inventor： PREIBISCH, Stefan

IPC: F01D25/26 ,  F01K7/22 ,  F01K7/02 ,  F01D25/14

公开(公告)号：EP3222820B1

公开(公告)日：2023-07-26

申请号：EP17162637.7

申请日：2017-03-23

Inventor： MCMAHAN, Kevin Weston ,  LEBEGUE, Jeffrey Scott ,  FLANAGAN, James Scott

IPC: F01D9/02 ,  F01D11/00 ,  F01D25/26

公开(公告)号：EP4095353A1

公开(公告)日：2022-11-30

申请号：EP22173727.3

申请日：2022-05-17

Applicant: General Electric Company

Inventor： HEALY, Michael James ,  DEVARAJAN, Sabarinath ,  CARDOZA, Carlos Alberto

IPC: F01D9/04 ,  F01D25/26 ,  F01D25/24 ,  F04D29/54

Abstract: A compressor section (14) includes a compressor casing (48) that has an upper casing portion (60) coupled to a lower casing portion (62) such that a split-line (64) is defined between the upper casing portion (60) and the lower casing portion (62). A split-line stator vane assembly (70) includes a first split-line stator vane (76) that has a first shank (75) with a first platform portion (84) and a first mounting portion (86) that extends radially outward of the first platform portion (84). A first airfoil (88) extends radially inward of the first platform portion (84). The first platform portion (84) includes a protrusion (80) that extends circumferentially beyond the split-line (64). A second split-line stator vane (78) has a second shank (79) with a second platform portion (94) and a second mounting portion (96) that extends radially outward of the second platform portion (94). A second airfoil (88) extends radially inward of the second platform portion (94). The second platform portion (94) includes a recess (82) that extends circumferentially away from the split-line (64).

公开(公告)号：EP4088010A1

公开(公告)日：2022-11-16

申请号：EP21708155.3

申请日：2021-02-18

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： STUPARIU-COHAN, Sebastian

IPC: F01D21/00 ,  F01D25/00 ,  F01D25/24 ,  F01D25/26

公开(公告)号：EP4086175A1

公开(公告)日：2022-11-09

申请号：EP22165755.4

申请日：2022-03-31

Applicant: Rolls-Royce plc

Inventor： Eryilmaz, Ibrahim ,  Pachidis, Vasileios

IPC: B64D13/00 ,  B64D33/08 ,  B64D27/10 ,  F02C7/12 ,  F01D25/26 ,  B64D13/06 ,  B64D27/02

Abstract: A cabin blower (100) for an aircraft (50), the system comprising: a cabin blower compressor (110); an electric machine (131); and a controller (133) configured to control the cabin blower system (100) so that: in a cabin blower mode of operation, the cabin blower compressor (110) is driven by power extracted from one or more spools (26, 27) of a gas turbine engine (10) of the aircraft (50) and provides a flow of air to a cabin of the aircraft (50). The controller (133) may be further configured to control the system (100) so that: in a rotor bow mitigation mode of operation, the cabin blower compressor (110) is driven by the electric machine (131) using electrical power from an electrical power source (134) and provides a flow of air through a core of the gas turbine engine (10) to remove heat from the core. A method (60) of operating a cabin blower system (100) of an aircraft (50) is also provided.