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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.
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。
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公开(公告)号：WO2014109813A2
公开(公告)日：2014-07-17
申请号：PCT/US2013/066780
申请日：2013-10-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： HOUSTON, David P.
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.
Abstract translation: 根据本公开的一个示例的翼型件附件包括翼型件和支撑翼型件的盘。 此外，在翼型件和盘之间存在主接触表面和次级接触表面。 次级接触面在正常工作状态下不接合。
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公开(公告)号：WO2013130290A1
公开(公告)日：2013-09-06
申请号：PCT/US2013/026537
申请日：2013-02-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： KORN, Nathan D. , GENDRICH, Charles P. , DAGGETT, Jonathan E. , SHEPLER, Robert E. , HOUSTON, David P. , NISSLEY, David M. , HOYT, Stephen D. , PRIHAR, Ron I.
CPC classification number: F01D5/005 , F05D2230/80 , Y10T29/49325
Abstract: A component blending tool assembly, includes a material removing surface that is moved to provide a blended area in a component, the material removing surface having a spherical contour mimicking a predetermined depth ratio of the blended area.
Abstract translation: 组分共混工具组件包括移动以提供部件中的混合区域的材料去除表面，材料去除表面具有模拟混合区域的预定深度比的球形轮廓。
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公开(公告)号：WO2013116262A1
公开(公告)日：2013-08-08
申请号：PCT/US2013/023730
申请日：2013-01-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： HOUSTON, David P. , KUPRATIS, Daniel Bernard , SCHWARZ, Frederick M.
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驱动，用于围绕轴旋转风扇。
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公开(公告)号：EP2809931A1
公开(公告)日：2014-12-10
申请号：EP13743042.7
申请日：2013-01-30
Applicant: United Technologies Corporation
Inventor： HOUSTON, David P. , KUPRATIS, Daniel Bernard , SCHWARZ, Frederick M.
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.
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Patent Agency Ranking
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.
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公开(公告)号：EP2809931B1
公开(公告)日：2016-07-20
申请号：EP13743042.7
申请日：2013-01-30
Applicant: United Technologies Corporation
Inventor： HOUSTON, David P. , KUPRATIS, Daniel Bernard , SCHWARZ, Frederick M.
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
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公开(公告)号：EP3633149A1
公开(公告)日：2020-04-08
申请号：EP19213135.7
申请日：2013-04-20
Applicant: United Technologies Corporation
IPC: F01D5/16
Abstract: An airfoil (60) includes an airfoil body (68) that has a leading edge (LE) and a trailing edge (TE) and a first sidewall (74) and a second sidewall (76) that is spaced apart from the first sidewall (74). The first sidewall (74) and the second sidewall (76) join the leading edge (LE) and the trailing edge (TE) and at least partially define a cavity (78) in the airfoil body (68). A damper member (88) is enclosed in the cavity (78) and is loose within the cavity (78).
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9.发明公开
公开(公告)号：EP3249200A1
公开(公告)日：2017-11-29
申请号：EP17172582.3
申请日：2017-05-23
Applicant: United Technologies Corporation
Inventor： SCHWARZ, Frederick M. , RIZO, Marnie A. , HOUSTON, David P. , NISSLEY, David M. , HIESTER, Paul J. , DALE, Timothy , WINFIELD, Timothy B. , CAMPBELL, Madeline N. , MIDGLEY, James R.
CPC classification number: G01M15/14 , B64D27/10 , F02C9/00 , F05D2220/323 , F05D2230/72 , F05D2260/80 , F05D2260/82 , F05D2260/94 , G05B23/0283
Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d).
Abstract translation: 一种监测燃气涡轮发动机的方法包括以下步骤：（a）从包括待监测发动机的飞机的实际飞行接收信息，并且包括起飞时的环境温度和内部发动机压力，温度和温度中的至少一个 速度; （b）根据步骤（a）中收到的数据，评估累积在发动机部件上的损害; （c）存储来自步骤（b）的确定的损伤; （d）重复步骤（a） - （c）; （e）基于步骤（a） - （d）建议组件的建议未来使用。
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公开(公告)号：EP2912277A2
公开(公告)日：2015-09-02
申请号：EP13870915.9
申请日：2013-10-25
Applicant: United Technologies Corporation
Inventor： HOUSTON, David P.
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.
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