公开(公告)号：WO2013163046A1

公开(公告)日：2013-10-31

申请号：PCT/US2013/037498

申请日：2013-04-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FISK, Benjamin T. ,  PROPHETER-HINCKLEY, Tracy A. ,  DOLANSKY, Gregory M. ,  TRACY, Anita L.

IPC: F01D5/12 ,  F01D5/18 ,  F01D9/00 ,  F02C7/12 ,  F02K3/00

CPC classification number: F01D5/147 ,  F05D2230/31

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall.

Abstract translation: 翼型件包括限定纵向轴线的翼型件。 翼型体包括前缘和后缘以及与第一侧壁间隔开的第一侧壁和第二侧壁。 第一侧壁和第二侧壁连接前缘和后缘，并且在翼型体中至少部分地限定空腔。 第一侧壁和第二侧壁中的至少一个包括纵向逐渐变细的至少一个纵向细长的支撑。 至少一个纵向细长的支撑件分别限定了第一侧壁或第二侧壁的增加的厚度。 所述至少一个纵向细长的支撑件部分地穿过所述空腔朝向所述第一侧壁或所述第二侧壁中的另一个突出。

公开(公告)号：WO2013163047A1

公开(公告)日：2013-10-31

申请号：PCT/US2013/037499

申请日：2013-04-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FISK, Benjamin T. ,  PROPHETER-HINCKLEY, Tracy A. ,  DOLANSKY, Gregory M.

IPC: F01D5/12 ,  F01D5/18 ,  F01D9/00 ,  F02C7/00 ,  F02C7/12 ,  F02K3/00

CPC classification number: F01D5/16 ,  B23P15/02 ,  F01D5/26

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.

Abstract translation: 翼型件包括限定纵向轴线的翼型件。 机翼本体包括前缘和后缘以及与第一侧壁相对的第一侧壁和第二侧壁。 第一侧壁和第二侧壁连接前缘和后缘，并且至少部分地限定翼型本体中的空腔。 阻尼器构件封装在空腔中。 阻尼器构件包括第一端和第二端。 第一端在第一纵向位置处以第一接头连接到第一侧壁，并且第二端在第二不同的纵向位置处以第二接头连接到第二侧壁。

公开(公告)号：WO2014052323A1

公开(公告)日：2014-04-03

申请号：PCT/US2013/061432

申请日：2013-09-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BALES, Daniel A. ,  KLUCHA, Agnes ,  DOLANSKY, Gregory M.

IPC: F02C7/12 ,  F01D5/18 ,  F02K3/00

CPC classification number: F01D5/187 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B22F2998/10 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/00 ,  B33Y70/00 ,  B33Y80/00 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2230/42 ,  F05D2230/90 ,  F05D2300/606 ,  Y02P10/295 ,  B22F3/15 ,  B22F2003/248 ,  C23C28/00

Abstract: A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer.

Abstract translation: 具有内部冷却通道的燃气轮机翼型通过附加制造形成。 超级合金粉末的层通过能量束熔合，使用二维图案，提供在其中形成通道的未熔化区域。 使用足够的二维图案加入并熔化粉末层，以形成具有所需图案的内部冷却通道的整个翼型。 在翼型形成完成之后，可以进行热等静压，定向重结晶，粘结涂层，并覆盖有热障层。

公开(公告)号：WO2013162887A1

公开(公告)日：2013-10-31

申请号：PCT/US2013/035939

申请日：2013-04-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FISK, Benjamin T. ,  PROPHETER-HINCKLEY, Tracy A. ,  DOLANSKY, Gregory M. ,  HOUSTON, David P. ,  TRACY, Anita L.

IPC: F01D5/18 ,  F02C7/00 ,  F02C3/00 ,  F02K3/00

CPC classification number: F01D5/16

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

Abstract translation: 翼型件包括具有前缘和后缘的翼型件主体和与第一侧壁间隔开的第一侧壁和第二侧壁。 第一侧壁和第二侧壁连接前缘和后缘，并且至少部分地限定翼型本体中的空腔。 阻尼器构件被封闭在空腔中并且在空腔内自由浮动。

公开(公告)号：WO2014011289A2

公开(公告)日：2014-01-16

申请号：PCT/US2013/036510

申请日：2013-04-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FISK, Benjamin T. ,  PROPHETER-HINCKLEY, Tracy A. ,  DOLANSKY, Gregory M. ,  TRACY, Anita L. ,  TAFFET, Steven

CPC classification number: F01D5/147 ,  B23P15/02 ,  F01D5/187 ,  F05D2260/22141 ,  Y10T29/49336

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.

Abstract translation: 翼型件包括限定纵向轴线的翼型件。 翼型本体包括前缘和后缘以及与第一侧壁间隔开的第一侧壁和第二侧壁，以在其间限定弧形线。 第一侧壁和第二侧壁连接前缘和后缘，并且在翼型体中至少部分地限定空腔。 多个肋在空腔中纵向延伸并且相对于纵向轴线彼此横向间隔开。 在垂直于纵向轴线的至少一个平面中，每个肋条沿垂直于弯度线的相应的最小距离方向连接第一侧壁和第二侧壁。 各个最小距离方向中的至少两个是不平行的。

公开(公告)号：WO2013163048A1

公开(公告)日：2013-10-31

申请号：PCT/US2013/037500

申请日：2013-04-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FISK, Benjamin T. ,  PROPHETER-HINCKLEY, Tracy A. ,  DOLANSKY, Gregory M. ,  TREEN, Robert J.

IPC: F01D5/12 ,  F01D5/18 ,  F01D9/00 ,  F02C7/00 ,  F02C7/12 ,  F02K3/00

CPC classification number: F01D5/16 ,  F01D5/26 ,  F01D25/06 ,  Y10T29/49316

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.

Abstract translation: 翼型件包括限定纵向轴线的翼型件。 翼型体包括前缘和后缘以及与第一侧壁间隔开的第一侧壁和第二侧壁。 第一侧壁和第二侧壁连接前缘和后缘，并且至少部分地限定翼型本体中的至少一个纵向细长的空腔。 多个松散颗粒被封闭在至少一个纵向细长的空腔中。

公开(公告)号：EP2841709B1

公开(公告)日：2018-07-11

申请号：EP13781623.7

申请日：2013-04-10

Applicant: United Technologies Corporation

Inventor： FISK, Benjamin T. ,  PROPHETER-HINCKLEY, Tracy A. ,  DOLANSKY, Gregory M. ,  HOUSTON, David P. ,  TRACY, Anita L.

IPC: F01D5/16

CPC classification number: F01D5/16

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

公开(公告)号：EP2841699A1

公开(公告)日：2015-03-04

申请号：EP13780621.2

申请日：2013-04-20

Applicant: United Technologies Corporation

Inventor： FISK, Benjamin T. ,  PROPHETER-HINCKLEY, Tracy A. ,  DOLANSKY, Gregory M.

IPC: F01D5/12 ,  F01D5/18 ,  F01D9/00 ,  F02C7/00 ,  F02C7/12 ,  F02K3/00

CPC classification number: F01D5/16 ,  B23P15/02 ,  F01D5/26

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.

公开(公告)号：EP3434866A1

公开(公告)日：2019-01-30

申请号：EP18183751.9

申请日：2018-07-16

Applicant: United Technologies Corporation

Inventor： XU, JunQuan ,  LEVASSEUR, Glenn ,  DOLANSKY, Gregory M.

IPC: F01D5/14 ,  F01D5/20 ,  F01D5/22 ,  F01D11/08

Abstract: A rotor blade (100) includes a main body (102) that extends radially outward from a first end (104) to a second end (106), and includes a platform (108) at the second end (106) that extends circumferentially between opposing first and second sidewalls (112,114). The platform (108) includes a first lateral wall (116) that is situated between leading and trailing edges (109,110) of the platform (108). The first lateral wall (116) extends circumferentially between the first and second sidewalls (112,114) and radially outward from the platform (108). The first lateral wall (116) includes an extension (240) that extends the first lateral wall (116) circumferentially outward from the first sidewall (112). Respective portions of the first and second sidewalls (112,114) adjacent to the first lateral wall (116) reside in respective first and second planes (P1,P2), and the extension (240) includes an outer face (242) situated outside of the first and second planes (P1,P2). A majority of the first lateral wall (116) includes a first material, and the outer face (24) includes a second material having a different resistance to wear than the first material.

公开(公告)号：EP2952689A1

公开(公告)日：2015-12-09

申请号：EP15171030.8

申请日：2015-06-08

Applicant: United Technologies Corporation

Inventor： PACK, David R. ,  PARTYKA, Julian ,  HILL, James D. ,  SUCIU, Gabriel L. ,  DOLANSKY, Gregory M. ,  MERRY, Brian D.

IPC: F01D11/00

CPC classification number: F01D11/008 ,  F01D5/06 ,  F01D11/001 ,  F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  Y02T50/671

Abstract: A seal segment (102) for a gas turbine engine (20) includes a first axial span (134) that extends between a first radial span (130) and a second radial span (132). A second axial span (136) extends between the first radial span (130) and the second radial span (132), the first radial span (130), the second radial span (132), the first axial span (134) and the second axial span (136) form a torque box. A plurality of seal segments (102) may be located between first and second rotor disks (68, 70).

Abstract translation: 用于燃气涡轮发动机（20）的密封段（102）包括在第一径向跨度（130）和第二径向跨度（132）之间延伸的第一轴向跨度（134）。 第二轴向跨度（136）在第一径向间距（130）和第二径向跨度（132）之间延伸，第一径向跨度（130），第二径向跨度（132），第一轴向跨度（134）和 第二轴向跨度（136）形成扭矩箱。 多个密封段（102）可以位于第一和第二转子盘（68,70）之间。