公开(公告)号：EP3011139A2

公开(公告)日：2016-04-27

申请号：EP14834000.3

申请日：2014-05-22

Applicant: United Technologies Corporation

Inventor： BURD, Steven W. ,  HARRIS, Meggan ,  OLS, John T. ,  ASKEY, William G.

IPC: F01D5/02 ,  F01D5/30

CPC classification number: F01D5/3069 ,  B22D25/02 ,  B23P15/006 ,  F01D5/02 ,  F01D5/12 ,  F01D5/3023 ,  F01D5/3061 ,  F01D5/34 ,  F01D9/044 ,  F01D25/24 ,  F01D25/30 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/232 ,  F05D2230/25 ,  F05D2230/60 ,  F05D2240/24

Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.

Abstract translation: 整体式一体式轮毂具有第一和第二环以及布置在第一和第二环之间的中间部分。 中间部分包括构造成接收多个横向构件的多个窗口。 窗户包括构造成围绕横梁的唇缘。 还公开了燃气涡轮发动机和提供用于燃气涡轮发动机的毂的方法。

公开(公告)号：EP3059399A1

公开(公告)日：2016-08-24

申请号：EP16156096.6

申请日：2016-02-17

Applicant: United Technologies Corporation

Inventor： FARAH, Jorge I. ,  OLS, John T.

IPC: F01D25/16 ,  F01D25/28

CPC classification number: F01D9/041 ,  F01D9/042 ,  F01D9/065 ,  F01D11/005 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F05D2220/3213 ,  F05D2230/21 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/31

Abstract: A gas turbine engine 20 includes a core flow path that extends axially about an engine axis. A turbine section 28 is arranged in the core flow path. A mid-turbine frame 82 includes multiple circumferentially spaced vanes that extend radially between and interconnect inner 113 and outer flow path surfaces 115 that define a portion of the core flow path. The vanes and inner and outer flow path surfaces are provided by a unitary, one-piece cast structure. The inner flow path surface 113 provides inlet and exit inner diameters relative to the engine axis. The outer flow path surface 115 provides inlet and exit outer diameters relative to the engine axis. The inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter. A ratio of the exit outer diameter to the axial length is greater than 3.0 to 1.

Abstract translation: 燃气涡轮发动机20包括围绕发动机轴线轴向延伸的铁心流路。 涡轮机部分28布置在核心流动路径中。 中涡轮机框架82包括多个周向间隔开的叶片，该叶片径向延伸并且互连内部113和限定芯部流动路径的一部分的外部流动路径表面115。 叶片和内部和外部流动路径表面由单一的一体式铸造结构提供。 内部流路表面113提供相对于发动机轴线的入口和出口内径。 外部流路表面115相对于发动机轴线提供入口和出口外径。 内部流路表面从入口内径延伸到出口内径的轴向长度。 出口外径与轴向长度的比值大于3.0比1。

公开(公告)号：EP3052764A1

公开(公告)日：2016-08-10

申请号：EP14850260.2

申请日：2014-09-22

Applicant: United Technologies Corporation

Inventor： OLS, John T. ,  ALLEN, Richard N. ,  PORTER, Steven D. ,  SANCHEZ, Paul K.

IPC: F01D9/02 ,  F02C7/20

CPC classification number: F01D9/041 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/80 ,  F05D2260/941 ,  Y02T50/671

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, a radially outer platform and a radially inner platform. A rib is on one of the radially inner and radially outer platforms, and is adjacent the trailing edge of the airfoil. A mid-turbine frame is also disclosed.

公开(公告)号：EP3027855A2

公开(公告)日：2016-06-08

申请号：EP14832509.5

申请日：2014-06-19

Applicant: United Technologies Corporation

Inventor： OLS, John T. ,  PORTER, Steven D.

IPC: F01D9/04 ,  F01D11/00

Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.

Abstract translation: 用于燃气涡轮发动机的叶片组包括叶片的环形排列。 一个环被固定在叶片周围并且延伸到叶片的轴向端部。

公开(公告)号：EP3027855B1

公开(公告)日：2020-09-09

申请号：EP14832509.5

申请日：2014-06-19

Applicant: United Technologies Corporation

Inventor： OLS, John T. ,  PORTER, Steven D.

IPC: F01D9/04 ,  F01D11/02 ,  F01D25/16 ,  F01D11/00

公开(公告)号：EP3062953A1

公开(公告)日：2016-09-07

申请号：EP14857767.9

申请日：2014-10-24

Applicant: United Technologies Corporation

Inventor： OLS, John T. ,  LIN, Wangen ,  WHITMAN, Giovanni

IPC: B23K26/34

CPC classification number: B23K26/342 ,  B22F5/009 ,  B22F7/062 ,  B22F2007/068 ,  B22F2999/00 ,  B23K26/144 ,  B23K26/323 ,  B23K35/0244 ,  B23K35/3033 ,  B23K2201/001 ,  B23K2203/26 ,  B23P6/007 ,  C22F1/10 ,  F01D5/005 ,  F01D9/041 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/234 ,  F05D2230/31 ,  F05D2230/42 ,  F05D2300/175 ,  F05D2300/177 ,  B22F3/105

Abstract: A method is provided for reworking a component. The method includes at least partially filling a cavity in a non-fusion weldable base alloy with a multiple of layers of a multiple of laser powder deposition spots formed of a filler alloy. Each of the multiple of laser powder deposition spots at least partially overlaps at least one of another of the multiple of laser powder deposition spots. The filler alloy may be different than the non-fusion weldable base alloy.

Abstract translation: 提供了一个方法来修改组件。 该方法包括利用由填充合金形成的多个激光粉末沉积点的多个层来至少部分地填充非熔融可焊接基础合金中的空腔。 多个激光粉末沉积斑点中的每一个至少部分地与多个激光粉末沉积斑点中的另一个中的至少一个重叠。 填充合金可以与不可熔焊接的基础合金不同。

公开(公告)号：EP3037627A1

公开(公告)日：2016-06-29

申请号：EP15201381.9

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： PORTER, Steven D. ,  OLS, John T. ,  LANA, Kyle C.

IPC: F01D11/00 ,  F01D5/08

CPC classification number: F01D9/02 ,  F01D1/04 ,  F01D5/081 ,  F01D11/001 ,  F05D2240/80 ,  Y02T50/676

Abstract: A gas-turbine engine (20) is provided. The gas-turbine engine (20) comprises a high pressure turbine (54) with an aft blade platform (106). A static structure may be disposed aft of the high pressure turbine (54) and proximate a cavity (104) defined by the aft blade platform (106). A vane of the static structure may have a vane platform (102) with a shaped tip (126; 200; 202; 204) extending into the cavity (104).

Abstract translation: 提供一种燃气涡轮发动机（20）。 燃气涡轮发动机（20）包括具有后叶片平台（106）的高压涡轮机（54）。 静态结构可以设置在高压涡轮机（54）的后方并靠近由后叶片平台（106）限定的空腔（104）。 静态结构的叶片可以具有叶片平台（102），其具有延伸到空腔（104）中的成形尖端（126; 200; 202; 204）。

公开(公告)号：EP3022400A1

公开(公告)日：2016-05-25

申请号：EP14825846.0

申请日：2014-06-25

Applicant: United Technologies Corporation

Inventor： OLS, John T. ,  MENTZ, Karl A. ,  ALLEN, Richard N. ,  PORTER, Steven D. ,  JUREK, Renee J. ,  SANCHEZ, Paul K. ,  PINERO, Sandra S.

IPC: F01D9/04 ,  F01D5/14 ,  F02C7/04

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/143 ,  F01D9/04 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  F05D2250/71 ,  F05D2250/90 ,  Y02T50/673

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

公开(公告)号：EP3037627B1

公开(公告)日：2020-02-05

申请号：EP15201381.9

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： PORTER, Steven D. ,  OLS, John T. ,  LANA, Kyle C.

IPC: F01D11/00 ,  F01D5/08