公开(公告)号：EP3951136B1

公开(公告)日：2024-09-11

申请号：EP21188094.3

申请日：2021-07-27

IPC: F01D5/00

CPC classification number: F05D2300/22220130101 ,  F05D2300/226120130101 ,  F05D2300/60320130101 ,  F05D2300/603320130101 ,  F05D2230/8020130101 ,  F01D5/005 ,  Y02T50/60

公开(公告)号：EP4419844A2

公开(公告)日：2024-08-28

申请号：EP22940472.8

申请日：2022-10-21

Applicant: Raytheon Technologies Corporation

Inventor： MARTIN, Thomas J. ,  SRINIVASAN, Gajawalli V. ,  CROTEAU, Paul F. ,  KENNEDY, Matthew B.

IPC: F23R3/06 ,  F01D5/18

CPC classification number: Y02T50/60 ,  F23R3/007 ,  F23R3/06 ,  F23R3/002 ,  F01D5/186 ,  F05D2260/20220130101 ,  F05D2300/22220130101 ,  F01D5/187

公开(公告)号：EP3459733B1

公开(公告)日：2024-04-24

申请号：EP18192517.3

申请日：2018-09-04

IPC: B32B18/00 ,  C04B35/573 ,  C04B35/80 ,  F01D5/28 ,  F02K1/82

CPC classification number: F05D2300/226120130101 ,  C04B35/573 ,  F01D5/282 ,  F01D5/284 ,  F02K1/822 ,  C04B2235/524420130101 ,  C04B2235/526420130101 ,  C04B2235/61620130101 ,  C04B2235/72820130101 ,  C04B2235/8020130101 ,  C04B2237/3820130101 ,  F05D2300/603320130101 ,  F05D2300/22220130101 ,  B32B18/00 ,  C04B2235/382620130101 ,  C04B2235/42220130101 ,  C04B2235/61420130101 ,  C04B35/80 ,  B32B7/02

公开(公告)号：EP3337773B1

公开(公告)日：2024-09-25

申请号：EP16760601.1

申请日：2016-08-17

IPC: C04B41/00 ,  C04B41/89 ,  C04B41/52 ,  F01D5/28 ,  C23C4/10 ,  C23C28/04 ,  C23C4/067 ,  C23C24/08 ,  C23C4/18

CPC classification number: C04B41/89 ,  C04B41/009 ,  C04B41/52 ,  C23C4/10 ,  C23C28/042 ,  F01D5/288 ,  C23C4/18 ,  C23C24/08 ,  C23C28/044 ,  C23C4/067 ,  F05D2300/210220130101 ,  F05D2300/22220130101

公开(公告)号：EP4403748A1

公开(公告)日：2024-07-24

申请号：EP24152997.3

申请日：2024-01-19

Applicant: RTX Corporation

Inventor： WHITE, Robert A. III ,  HAZEL, Brian T. ,  SURACE, Raymond

IPC: F01D9/04 ,  C04B41/00 ,  C04B41/50 ,  C04B41/53 ,  C04B41/89 ,  F01D11/00 ,  F01D25/24

CPC classification number: F01D9/04 ,  F01D11/005 ,  F01D25/24 ,  F05D2230/9020130101 ,  F05D2240/1120130101 ,  F05D2300/22220130101 ,  F05D2300/61120130101 ,  C04B41/009 ,  C04B41/5024 ,  C04B41/53 ,  C04B41/89 ,  C04B41/52

Abstract: A section of a gas turbine engine includes a ceramic component (104), a metallic component (102), a seal (105) situated between the metallic component (102) and the ceramic component (104) at a sealing interface (106), a silicon-based coating (108) disposed on the ceramic component (104) at the sealing interface (106), and a non-reactive coating (110) disposed on the metallic component (102) at the sealing interface (106). The non-reactive coating (110) provides thermochemical protection against interaction between the ceramic component (104) and the metallic component (102), and/or between the silicon-based coating (108) and the metallic component (102).

公开(公告)号：EP4386180A1

公开(公告)日：2024-06-19

申请号：EP23213102.9

申请日：2023-11-29

Applicant: RTX Corporation

Inventor： WHITE III, Robert A. ,  ABDI, Ahmed Abdillahi ,  LITTON, David A. ,  ROGERS, Daniel S.

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/24 ,  F16J15/02

CPC classification number: F05D2300/2020130101 ,  F05D2300/61120130101 ,  F05D2300/603320130101 ,  F05D2230/9020130101 ,  F01D11/005 ,  F01D9/04 ,  F05D2300/22220130101 ,  F05D2240/1020130101 ,  F05D2240/1120130101 ,  F01D25/24

Abstract: A section of a gas turbine engine includes a ceramic component (104) and a metallic component (102) situated adjacent the ceramic component (104). The ceramic component (104) and the metallic component (102) are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface (106) between the ceramic component (104) and the metallic component (102) and a mullite-based coating (200) disposed at the interface (106). The coating (200) provides thermal protection to the ceramic component (104) and the metallic component (102), and provides thermochemical protection against interaction between the ceramic component (104) and the metallic component (102). A gas turbine engine and a method of protecting components (102, 104) in a gas turbine engine are also disclosed.

公开(公告)号：EP4403749A1

公开(公告)日：2024-07-24

申请号：EP23214100.2

申请日：2023-12-04

Applicant: RTX Corporation

Inventor： White III, Robert A. ,  Hazel, Brian T. ,  Ding, Zhongfen

IPC: F01D11/00 ,  C04B41/50

CPC classification number: F01D11/005 ,  F01D5/284 ,  F01D5/288 ,  F02C7/28 ,  C04B41/5024 ,  F05D2240/1120130101 ,  F05D2230/9020130101 ,  F05D2240/5720130101 ,  F05D2300/17520130101 ,  F05D2300/22220130101 ,  F05D2300/5021120130101 ,  F05D2300/51420130101 ,  F05D2300/61120130101 ,  F05D2300/60320130101 ,  F05D2300/603320130101 ,  C04B41/52 ,  C04B41/89 ,  C04B41/009 ,  C04B41/522 ,  F01D5/282 ,  F01D25/007 ,  F05D2300/1520130101 ,  F05D2300/21120130101 ,  F05D2300/211820130101 ,  F05D2300/211220130101 ,  F05D2300/21220130101 ,  F05D2300/228320130101

Abstract: A seal system 60 comprising a ceramic component 62 having a surface region 70 defining a first surface roughness, a metallic component 64 situated adjacent the surface region, and a coating system 71 disposed on the surface region 70. The coating system 71 includes a silicon-containing layer 66 on the surface region and a barrier layer 68 on the silicon-containing layer. The silicon-containing layer 66 has a surface in contact with the barrier layer 68. The barrier layer 68 has a surface in contact with the metallic component 64. The surface of the barrier layer 68 has a second surface roughness that is less than the first surface roughness. The barrier layer 68 limits interaction between silicon of the silicon-containing layer 66 and elements of the metallic component 64. The barrier layer 68 has a coefficient of thermal expansion that is within about 60% of a coefficient of thermal expansion of the ceramic component 62. A gas turbine engine and a method are also disclosed.

公开(公告)号：EP4397788A1

公开(公告)日：2024-07-10

申请号：EP23198923.7

申请日：2023-09-21

Applicant: General Electric Company

Inventor： ADHARAPURAPU, Raghavendra Rao

IPC: C23C24/08 ,  C23C24/10 ,  C23C30/00 ,  B22F3/105 ,  B22F7/00 ,  C22C45/00 ,  F01D5/28

CPC classification number: C23C24/085 ,  C23C24/10 ,  C23C30/00 ,  B22F10/28 ,  B22F7/08 ,  B22F7/06 ,  B22F5/04 ,  C22C2200/0220130101 ,  B33Y80/00 ,  B33Y10/00 ,  B22F2007/06820130101 ,  B33Y40/20 ,  B22F10/64 ,  C22C32/0073 ,  C22C32/0078 ,  C22C1/053 ,  F01D5/147 ,  F05D2220/3620130101 ,  F05D2240/30320130101 ,  F05D2240/30420130101 ,  F01D5/288 ,  F05D2300/210220130101 ,  F05D2300/22220130101 ,  F05D2300/21120130101 ,  F05D2300/12320130101 ,  F05D2300/12120130101 ,  F05D2300/603320130101 ,  F05D2300/13320130101 ,  F05D2300/1120130101 ,  F05D2300/13220130101 ,  F05D2300/16120130101 ,  F05D2300/13420130101 ,  F05D2300/13120130101 ,  F05D2300/1320130101 ,  F05D2300/143220130101 ,  F05D2300/143520130101 ,  F05D2300/143120130101 ,  F05D2300/22820130101 ,  F05D2300/2220130101 ,  B32B15/01 ,  C22C45/10 ,  C22C45/08 ,  C22C45/02 ,  C22C45/04

Abstract: A wear resistant article (105) including a substrate (130) and a bulk metallic glass coating (110) including an alloy of a base metal, a transition metal, boron, and silicon, wherein the bulk metallic glass coating (110) has a thickness of about 0.05 millimeter or greater and a functionally graded microstructure. A method of producing an article (105) with a wear resistant coating (110) by additively printing a bulk metallic glass coating (110) onto at least a portion of the article (105).

公开(公告)号：EP4386181A1

公开(公告)日：2024-06-19

申请号：EP23213427.0

申请日：2023-11-30

Applicant: RTX Corporation

Inventor： Rogers, Daniel S ,  White III, Robert A

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

CPC classification number: F01D9/04 ,  F01D11/005 ,  F01D25/24 ,  F05D2230/9020130101 ,  F05D2240/1120130101 ,  F05D2300/2020130101 ,  F05D2300/22220130101 ,  F05D2300/603320130101 ,  F05D2300/61120130101 ,  F05D2240/1020130101

Abstract: A section of a gas turbine engine includes a ceramic component and a metallic component situated adjacent the ceramic component. The ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface between the ceramic component and a metallic component and a mullite-based coating disposed at the interface. The coating provides thermal protection to the ceramic component and the metallic component, and provides thermochemical protection against interaction between the ceramic component and the metallic component. A gas turbine engine and a method of protecting components in a gas turbine engine are also disclosed.

公开(公告)号：EP4379188A1

公开(公告)日：2024-06-05

申请号：EP23212419.8

申请日：2023-11-27

Applicant: RTX Corporation

Inventor： CAMPBELL, Christian X.

IPC: F01D5/28 ,  F01D9/04 ,  F01D5/14

CPC classification number: F01D9/044 ,  F01D5/284 ,  F05D2230/23720130101 ,  F01D5/282 ,  F05D2300/22220130101 ,  F05D2240/8020130101 ,  F05D2240/8120130101 ,  F05D2240/1220130101 ,  F01D5/147 ,  F05D2300/603320130101

Abstract: A multiple static vane component includes a plurality of airfoils (120) each formed of ceramic matrix composite materials. Each of the airfoils (120) are attached to an inner platform (126) and an outer platform (116) both formed of ceramic matrix composite materials. There is a plurality of individual parts forming the plurality of airfoils (120), the inner platform (126) or the outer platform (116), bonded to each other with a braze joint. A gas turbine engine (20) and a method are also disclosed.