公开(公告)号：EP2912277B1

公开(公告)日：2018-12-05

申请号：EP13870915.9

申请日：2013-10-25

Applicant: United Technologies Corporation

Inventor： HOUSTON, David P.

IPC: F01D5/30 ,  F01D5/02 ,  F02C7/04 ,  F01D21/04 ,  F02K3/04

CPC classification number: F01D5/3007 ,  F01D21/045 ,  F02K3/04 ,  F05D2220/36 ,  Y10T29/49321

Abstract: An airfoil attachment according to one example of this disclosure includes an airfoil and a disk supporting the airfoil. Further, there are primary contact surfaces and secondary contact surfaces between the airfoil and the disk. The secondary contact surfaces are not engaged during a normal operating condition.

公开(公告)号：EP3115292A1

公开(公告)日：2017-01-11

申请号：EP16170111.5

申请日：2013-01-30

Applicant: United Technologies Corporation

Inventor： HOUSTON, David P. ,  KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

IPC: B63H5/10 ,  B64C11/48 ,  B64C27/10 ,  F02K3/02 ,  F02K3/00 ,  F02C1/06 ,  F02C3/10 ,  F02C6/00 ,  F02C1/00 ,  F02C3/00 ,  F02K3/072 ,  F01D5/02 ,  F01D5/06 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107

CPC classification number: F02K3/06 ,  F01D5/02 ,  F01D5/026 ,  F01D5/066 ,  F02C3/107 ,  F02C7/36 ,  F05D2240/24 ,  F05D2260/40311 ,  F05D2270/02 ,  F05D2270/07 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.

Abstract translation: 燃气涡轮发动机包括可围绕轴线旋转的风扇，压缩机部分，与压缩机部分流体连通的燃烧器以及与燃烧器流体连通的涡轮部分。 涡轮机部分包括风扇驱动涡轮机和第二涡轮机。 第二涡轮机设置在风扇驱动涡轮机的前方。 风扇驱动涡轮机包括至少三个转子和具有孔半径（R）和活边半径（r）的至少一个转子，并且r / R的比率在约2.00和约2.30之间。 变速系统由风扇驱动涡轮机驱动，用于围绕轴旋转风扇。

公开(公告)号：EP3070315A1

公开(公告)日：2016-09-21

申请号：EP16161464.9

申请日：2016-03-21

Applicant: United Technologies Corporation

Inventor： HOUSTON, David P. ,  KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

IPC: F02K3/06 ,  F02C3/067 ,  F02C7/36

CPC classification number: F02K3/06 ,  F02C3/067 ,  F02C3/107 ,  F05D2250/00 ,  F05D2260/40311 ,  Y02T50/671

Abstract: A gas turbine engine (20) includes a fan (42) rotatable about an axis (A), a compressor section (24), a combustor (56) in fluid communication with the compressor section (24), and a turbine section (28) in fluid communication with the combustor (56). The turbine section (28) includes a fan drive turbine (46), a second turbine that drives a compressor rotor and one other turbine driving another compressor rotor of the compressor section (24). The second turbine (54) is disposed forward of the fan drive turbine (46). The fan drive turbine (46) includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system (48) is driven by the fan drive turbine (46) for rotating the fan (42) about the axis (A).

Abstract translation: 燃气涡轮发动机（20）包括可绕轴线（A）旋转的风扇（42），压缩机部分（24），与压缩机部分（24）流体连通的燃烧器（56），以及涡轮部分 ）与燃烧器（56）流体连通。 涡轮机部分（28）包括风扇驱动涡轮机（46），驱动压缩机转子的第二涡轮机和驱动压缩机部分（24）的另一压缩机转子的另一涡轮机。 第二涡轮机（54）配置在风扇驱动涡轮机（46）的前方。 风扇驱动涡轮机（46）包括至少三个转子和至少一个具有孔径半径（R）和活动轮缘半径（r）的转子，并且r / R的比率在约2.00和约2.30之间。 变速系统（48）由风扇驱动涡轮（46）驱动，以使风扇（42）绕轴线（A）旋转。

公开(公告)号：EP2841709A1

公开(公告)日：2015-03-04

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: F01D5/18 ,  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: 翼型包括具有前缘和后缘以及第一侧壁和与第一侧壁间隔开的第二侧壁的翼型体。 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。