专利检索 cpc:"F05D2250/31420130101" 第 1 页

1.

发明授权
INTEGRALLY BLADED ROTOR, GAS TURBINE ENGINE AND METHOD FOR MANUFACTURING AN INTEGRALLY BLADED ROTOR 有权转让

公开(公告)号：EP3882437B1

公开(公告)日：2024-06-19

申请号：EP21164108.9

申请日：2021-03-22

IPC分类号： F01D5/20 , F01D11/12 , F01D5/34

CPC分类号： F01D5/20 , F01D11/122 , F05D2250/18320130101 , F05D2250/19220130101 , F05D2250/29420130101 , F05D2250/31420130101

2.

发明授权
ROTOR BLADE AND CORRESPONDING GAS TURBINE 有权转让

公开(公告)号：EP3088674B1

公开(公告)日：2024-05-29

申请号：EP16166812.4

申请日：2016-04-25

IPC分类号： F01D5/20

CPC分类号： F01D5/20 , F05D2250/31420130101 , F05D2250/71320130101 , F05D2250/32420130101

3.

发明公开
GAS TURBINE COMBUSTION SECTION HAVING AN INTEGRATED FUEL CELL ASSEMBLY 审中-公开

公开(公告)号：EP4368891A1

公开(公告)日：2024-05-15

申请号：EP23194123.8

申请日：2023-08-29

申请人： General Electric Company

发明人： HONG, Seung-Hyuck , HART, Richard , WANG, Honggang , DUGGAL, Anil Raj , BENJAMIN, Michael Anthony , WICKERSHAM, Andrew , HSIEH, Shih-Yang

IPC分类号： F23R3/34 , F01D15/10 , F02C6/00 , H01M8/10

CPC分类号： F23R3/343 , F01D15/10 , H01M8/10 , F05D2240/3520130101 , F05D2220/7620130101 , F05D2250/31420130101 , B22F5/009 , B33Y80/00 , F05D2230/3020130101 , F05D2230/23420130101 , F05D2230/2220130101 , F02K3/06 , F02K5/00

摘要： A combustion section (114) defines an axial direction, a radial direction, and a circumferential direction. The combustion section (114) includes a casing (400) that defines a diffusion chamber (406). A combustion liner (402) is disposed within the diffusion chamber (406) and defines a combustion chamber (404). The combustion liner (402) is spaced apart from the casing (400) such that a passageway (408) is defined between the combustion liner (402) and the casing (400). A fuel cell assembly (410) is disposed in the passageway (408). The fuel cell assembly (410) includes a fuel cell stack (415) having a plurality of fuel cells (416) each extending between an inlet end (418) and an outlet end (420). Each fuel cell of the plurality of fuel cells (416) includes an air channel (496) and a fuel channel (498) each fluidly coupled to the combustion chamber (404).

4.

发明公开
HEAT EXCHANGER(S) FOR RECOVERING WATER AND/OR HEAT ENERGY FROM TURBINE ENGINE COMBUSTION PRODUCTS 审中-公开

公开(公告)号：EP4428348A1

公开(公告)日：2024-09-11

申请号：EP24150778.9

申请日：2024-01-08

申请人： RTX Corporation

发明人： SOBANSKI, Jon E. , CHANDLER, Jesse M.

IPC分类号： F02C3/30 , F02C7/12 , F02K3/06

CPC分类号： F05D2260/21320130101 , F02C3/305 , F05D2250/31420130101 , F02C7/12 , F05D2220/6020130101 , F02K3/06 , F05D2260/232220130101

摘要： A turbine engine (20) includes a fan section (30), a turbine engine core (28) and a recovery system (116). The turbine engine core (28) is configured to power the fan section (30). The turbine engine core (28) includes a core compressor section (31), a core combustor section (32) and a core turbine section (33). A centerline axis of the turbine engine core (28) is offset from a centerline axis of the turbine engine (20). The recovery system (116) includes an evaporator module (120) and a condenser module (121). A core flowpath (64) extends sequentially through the core compressor section (31), the core combustor section (32), the core turbine section (33), the evaporator module (120) and the condenser module (121) from an inlet (66) into the core flowpath (64) to an exhaust (68) from the core flowpath (64).

5.

发明公开
APPARATUS COMPRISING A VANE ARRAY STRUCTURE 审中-公开

公开(公告)号：EP4417792A1

公开(公告)日：2024-08-21

申请号：EP24158678.3

申请日：2024-02-20

申请人： Pratt & Whitney Canada Corp.

发明人： DUONG, Hien , KANDASAMY, Vijay

IPC分类号： F01D9/04 , F01D5/14

CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F01D5/141 , F05D2240/12220130101 , F05D2240/8020130101 , F05D2250/1120130101 , F05D2250/1320130101 , F05D2250/31420130101 , F05D2250/14120130101 , F05D2250/1420130101 , F05D2250/3820130101 , F05D2250/7120130101 , F05D2250/71120130101 , F05D2250/71220130101 , F01D5/146

摘要： A vane array structure (20) for a gas turbine engine (94) includes a first platform (22), a second platform (24), a plurality of vanes (26A, 26B) and a flowpath (28). Each of the vanes (26A, 26B) extends across the flowpath (28) between the first platform (22) and the second platform (24). The vanes (26A, 26B) include a first vane (26A) and a second vane (26B) disposed longitudinally next to the first vane (26A) along the flowpath (28). The first vane (26A) includes a first airfoil (58A) and a first recess (60A). The first airfoil (58A) extends spanwise between a first end (64A) at the first platform (22) and a second end (66A) at the second platform (24). The first airfoil (58A) extends chordwise between a leading edge (52A) and a trailing edge (50A). The first airfoil (58A) extends laterally between a first side (72A) and a second side (74A). The first recess (60A) projects spanwise into the first airfoil (58A) from the first end (64A). The first recess (60A) projects chordwise into the first airfoil (58A) from the trailing edge (50A).

6.

发明公开
DUCT STRUCTURE FOR AIRCRAFT PROPULSION SYSTEM 审中-实审

公开(公告)号：EP4382739A3

公开(公告)日：2024-07-24

申请号：EP23214230.7

申请日：2023-12-05

申请人： Rohr, Inc.

发明人： DAVIS, Jennifer

IPC分类号： F02K3/02

CPC分类号： F02K3/02 , F05D2300/60320130101 , F05D2300/4320130101 , F05D2230/5320130101 , F05D2250/31420130101 , F02C9/18 , F02C7/04

摘要： An apparatus is provided for an aircraft propulsion system (20). This apparatus includes a duct structure (60), and the duct structure (60) includes a transition duct (65), an inlet duct (64) and a bypass duct (66). The duct structure (60) is configured as a monolithic body. The transition duct (65) includes an inlet (74), a first outlet (82) and a second outlet (84). The transition duct (65) extends longitudinally along a longitudinal centerline (70) from the inlet (74) to the second outlet (84). The first outlet (82) is arranged longitudinally along the longitudinal centerline (70) between the inlet (74) and the second outlet (84). A centerline axis (90) of the first outlet (82) is angularly offset from the longitudinal centerline (70). The inlet duct (64) extends longitudinally along the longitudinal centerline (70) to the inlet (74). The bypass duct (66) extends longitudinally along the longitudinal centerline (70) from the second outlet (84).