公开(公告)号：EP3772568B1

公开(公告)日：2024-09-25

申请号：EP20189698.2

申请日：2020-08-05

IPC: F01D9/04 ,  F01D5/08 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D5/082 ,  F01D25/24 ,  Y02T50/60

公开(公告)号：EP4431716A1

公开(公告)日：2024-09-18

申请号：EP24163618.2

申请日：2024-03-14

Applicant: RTX Corporation

Inventor： KRAMER, Stephen K. ,  SMITH, Lance L. ,  DAI, Zhongtao

IPC: F02C3/22 ,  F01D9/04 ,  F01D9/06 ,  F02C3/30 ,  F04D29/54

CPC classification number: F01D9/065 ,  F01D9/041 ,  F02C3/30 ,  F02C3/305 ,  F02C3/22 ,  F05D2250/32420130101 ,  F05D2240/12220130101 ,  F05D2240/12320130101 ,  F05D2240/12420130101 ,  F04D29/542 ,  F01D25/30 ,  F05D2220/321920130101 ,  F04D29/705

Abstract: An aircraft propulsion system is provided that include a propulsor rotor (38), a turbine engine core (37) and a steam system (122). The turbine engine core (37) is configured to power the propulsor rotor (38). The turbine engine core (37) includes a core flowpath (52), a compressor section (29), a combustor section (30) and a turbine section (31). The core flowpath (52) extends through the compressor section (29), the combustor section (30) and the turbine section (31) from a flowpath inlet (56) to a flowpath exhaust (58). The combustor section (30) includes a diffuser plenum (68) and a combustor (62) disposed within the diffuser plenum (68). The steam system (122) is configured to introduce steam into the core flowpath (52) upstream of the diffuser plenum (68).

公开(公告)号：EP4431703A2

公开(公告)日：2024-09-18

申请号：EP24192714.4

申请日：2022-03-03

Applicant: RTX Corporation

Inventor： WHITE III, Robert A. ,  SIMPSON, Benjamin B.

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/284 ,  F01D5/188 ,  F05D2300/603320130101 ,  F05D2240/5520130101 ,  F01D11/005 ,  F01D11/003

Abstract: A vane arc segment (60) includes an airfoil fairing (62) that has an airfoil wall (63) that defines a fairing platform (66) and a hollow airfoil section (64). A spar (72) has a spar platform (72a) adjacent the fairing platform (66) and a spar leg (72b) that extends from the spar platform (72a) and through the hollow airfoil section (64). The spar leg (72b) is spaced from the airfoil wall (63) in the hollow airfoil section (64) such that there is a first gap (73a). The spar platform (72a) is spaced from the fairing platform (66) such that there is a second gap (72b). A support platform (78) is secured to the spar leg (72b) such that the airfoil fairing (62) is trapped between the spar platform (72a) and the support platform (78). There is a spring seal (82) between the spar platform (72a) and the fairing platform (66). The spring seal (82) biases the airfoil fairing (62) toward the support platform (78) and seals the first gap (73a) from the second gap (73b).

公开(公告)号：EP4124722B1

公开(公告)日：2024-08-28

申请号：EP22187073.6

申请日：2022-07-26

IPC: F01D9/04 ,  F01D5/28 ,  F01D11/00

CPC classification number: F01D9/041 ,  F05D2300/603320130101 ,  F01D5/284 ,  F01D11/005 ,  Y02T50/60

公开(公告)号：EP3604770B1

公开(公告)日：2024-08-28

申请号：EP18776659.7

申请日：2018-03-20

IPC: F02C7/16 ,  B01D53/94 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F02C3/22 ,  F02C3/30 ,  F02C3/34 ,  F02C7/22 ,  F01D9/04 ,  F02C3/24

CPC classification number: F02C7/16 ,  F01D9/041 ,  F01D5/185 ,  F01D5/186 ,  F02C3/24 ,  F05D2260/20520130101 ,  F05D2260/23220130101 ,  F02C3/34 ,  B01D53/8631 ,  B01D53/90 ,  B01D2251/1120130101 ,  B01D2251/206220130101 ,  B01D2258/028320130101

公开(公告)号：EP4388178A1

公开(公告)日：2024-06-26

申请号：EP22765936.4

申请日：2022-08-11

Applicant: SAFRAN

Inventor： MONDIN, Gabriel Jacques Victor ,  RIERA, William Henri Joseph

IPC: F01D5/14 ,  F01D9/04

CPC classification number: F01D5/146 ,  F01D9/041 ,  F05D2240/1220130101

公开(公告)号：EP4379190A1

公开(公告)日：2024-06-05

申请号：EP23213138.3

申请日：2023-11-29

Applicant: RTX Corporation

Inventor： WHITE III, Robert A. ,  SURACE, Raymond ,  LILES, Howard J. ,  DUBE, Bryan P.

IPC: F01D5/28 ,  F01D9/04

CPC classification number: F01D9/042 ,  F01D9/041 ,  F01D5/282 ,  F05D2240/8020130101 ,  F05D2300/60320130101 ,  F01D5/284 ,  F01D5/288 ,  F05D2230/1820130101 ,  F05D2230/6120130101 ,  F05D2230/1420130101 ,  F05D2300/21120130101 ,  F05D2300/211220130101 ,  F05D2300/603320130101

Abstract: A plurality of static stator vanes (106A,106B) are circumferentially spaced in a row axially intermediate rows of turbine blades. Each stator vane (106A,106B) has at least an outer platform with mount structure. Each of the stator vanes (106A,106B) are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes (106B) is circumferentially adjacent to a second of the stator vanes (106A). An orientation of the first of the stator vanes (106B) is re-staggered relative to the second of the stator vanes (106A). The sacrificial material of the first of the stator vanes (106B) is machined away such that a final trailing edge (122B) of the first of the stator vanes mount structure is now better axially aligned with the trailing edge (122B) of the second of the stator vanes mount structure.

公开(公告)号：EP4375485A1

公开(公告)日：2024-05-29

申请号：EP23212567.4

申请日：2023-11-28

Applicant: RTX Corporation

Inventor： JOLY, Michael M. ,  MEDIC, Gorazd

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/54 ,  F01D9/04

CPC classification number: F01D5/141 ,  F01D5/148 ,  F01D9/041 ,  F05D2250/7020130101 ,  F04D29/324 ,  F05D2240/30120130101 ,  F04D29/544 ,  F01D5/145 ,  F05D2250/71320130101

Abstract: An apparatus is provided for a gas turbine engine. This engine apparatus includes an airfoil (46) extending spanwise along a span line from a base to a tip. The airfoil (46) extends laterally between a pressure side (54) and a suction side (56). The airfoil (46) extends longitudinally along a camber line (58) from a leading edge (60) to a trailing edge (62). The airfoil (46) includes a first section (84B) and a second section (84C) arranged longitudinally between the first section (84B) and the trailing edge (62) along the camber line (58). An angle (64) between the camber line (58) and a reference plane (66; 72) changes according to a slope as the airfoil (46) extends longitudinally along the camber line (58). The slope in the second section (84C) is greater than the slope in the first section (84B).

公开(公告)号：EP4374046A1

公开(公告)日：2024-05-29

申请号：EP21754931.0

申请日：2021-07-21

Applicant: Safran Aero Boosters ,  General Electric Company

Inventor： PRINCIVALLE, Rémy, Henri, Pierre

IPC: F01D9/04 ,  F01D9/06 ,  F01D25/08 ,  F02K3/077

CPC classification number: F01D9/041 ,  F01D9/065 ,  F05D2260/20520130101 ,  F05D2240/1220130101 ,  F01D25/08 ,  F05D2260/21320130101 ,  Y02T50/60 ,  F02K3/02 ,  F02C7/14

公开(公告)号：EP3853445B1

公开(公告)日：2024-04-17

申请号：EP19791320.5

申请日：2019-09-20

IPC: F01D9/04 ,  F01D11/00

CPC classification number: F01D9/041 ,  F01D11/005 ,  F05D2250/28320130101