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公开(公告)号：US20180245541A1
公开(公告)日：2018-08-30
申请号：US15962039
申请日：2018-04-25
Applicant: United Technologies Corporation
Inventor： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
IPC: F02K3/06 , F02C7/36 , F02K3/072 , F01D9/04 , F02C9/18 , F01D5/06 , F01D9/02 , F02C3/04 , F02K1/78 , F04D27/00 , F04D29/32 , F02C3/107 , F01D25/16 , F02C7/06 , F01D5/02
CPC classification number: F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US09394793B1
公开(公告)日：2016-07-19
申请号：US13854354
申请日：2013-04-01
Applicant: United Technologies Corporation
Inventor： Bryan C. Atkins , Robert J. Esteve , Richard A. Lomenzo, Jr. , David P. Houston
CPC classification number: F01D5/16 , F01D5/14 , F01D5/141 , F01D5/186 , F01D5/30 , F05D2220/32 , F05D2240/30 , F05D2260/202 , F05D2300/175 , Y02T50/673
Abstract: A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. At least three of the following resonance frequencies are present. A first mode resonance frequency is 2591.5±10% Hz. A second mode resonance frequency is 4675.2±10% Hz. A third mode resonance frequency is 7892.9±10% Hz. A fourth mode resonance frequency is 10098.2±10% Hz. A fifth mode resonance frequency is 14808.2±10% Hz.
Abstract translation: 涡轮机翼型元件具有翼型。 翼型件具有内侧端部，外侧端部，前缘部，后缘部，压力侧部和吸力侧。 内侧和外侧之间的距离为1.4-1.6英寸。 50％跨度的弦长为0.9-1.4英寸。 存在以下共振频率中的至少三个。 第一模式谐振频率为2591.5±10％Hz。 第二模式谐振频率为4675.2±10％Hz。 第三模式谐振频率为7892.9±10％Hz。 第四模式谐振频率为10098.2±10％Hz。 第五种谐振频率为14808.2±10％Hz。
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公开(公告)号：US20150345426A1
公开(公告)日：2015-12-03
申请号：US14662387
申请日：2015-03-19
Applicant: United Technologies Corporation
Inventor： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
CPC classification number: F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , 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至少一个具有孔半径（R）和活边半径（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：US20190219484A1
公开(公告)日：2019-07-18
申请号：US16264760
申请日：2019-02-01
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Marnie A. Rizo , David P. Houston , David M. Nissley , Paul J. Hiester , Timothy Dale , Timothy B. Winfield , Madeline Campbell , James R. Midgley
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). A system is also disclosed.
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公开(公告)号：US10288010B2
公开(公告)日：2019-05-14
申请号：US15405498
申请日：2017-01-13
Applicant: United Technologies Corporation
Inventor： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
IPC: F02K3/06 , F02K3/072 , F02C7/36 , F01D25/16 , F01D5/02 , F02C7/06 , F01D5/06 , F01D9/02 , F02C3/04 , F02C3/107 , F02C9/18 , F02K1/78 , F04D27/00 , F04D29/32 , F01D9/04
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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Patent Agency Ranking
公开(公告)号：US10151204B2
公开(公告)日：2018-12-11
申请号：US15042840
申请日：2016-02-12
Applicant: United Technologies Corporation
Inventor： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
IPC: F01D5/16 , B22F3/105 , B22F5/04 , F01D9/04 , F01D25/04 , F04D29/38 , F04D29/54 , F04D29/66 , B22F5/10
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 between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.
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公开(公告)号：US20170298833A1
公开(公告)日：2017-10-19
申请号：US15488580
申请日：2017-04-17
Applicant: United Technologies Corporation
Inventor： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
CPC classification number: F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US20160319670A1
公开(公告)日：2016-11-03
申请号：US15211510
申请日：2016-07-15
Applicant: United Technologies Corporation
Inventor： Bryan C. Atkins , Robert J. Esteve , Richard A. Lomenzo, JR. , David P. Houston
CPC classification number: F01D5/16 , F01D5/14 , F01D5/141 , F01D5/186 , F01D5/30 , F05D2220/32 , F05D2240/30 , F05D2260/202 , F05D2300/175 , Y02T50/673
Abstract: A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. At least three of the following resonance frequencies are present. A first mode resonance frequency is 2591.5±10% Hz. A second mode resonance frequency is 4675.2±10% Hz. A third mode resonance frequency is 7892.9±10% Hz. A fourth mode resonance frequency is 10098.2±10% Hz. A fifth mode resonance frequency is 14808.2±10% Hz.
Abstract translation: 涡轮机翼型元件具有翼型。 翼型件具有内侧端部，外侧端部，前缘部，后缘部，压力侧部和吸力侧。 内侧和外侧之间的距离为1.4-1.6英寸。 50％跨度的弦长为0.9-1.4英寸。 存在以下共振频率中的至少三个。 第一模式谐振频率为2591.5±10％Hz。 第二模式谐振频率为4675.2±10％Hz。 第三模式谐振频率为7892.9±10％Hz。 第四模式谐振频率为10098.2±10％Hz。 第五种谐振频率为14808.2±10％Hz。
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公开(公告)号：US20160160651A1
公开(公告)日：2016-06-09
申请号：US15042840
申请日：2016-02-12
Applicant: United Technologies Corporation
Inventor： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
CPC classification number: F01D5/16 , B22F3/1055 , B22F5/04 , B22F5/10 , F01D9/041 , F01D25/04 , F04D29/38 , F04D29/542 , F04D29/668 , F05D2220/32 , F05D2230/21 , F05D2240/50 , F05D2250/232 , Y02P10/295
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 between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in 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将前缘和后缘连接在径向外端和径向内端之间。 第一侧壁和第二侧壁至少部分地限定在翼型件本体中径向延伸的空腔。 阻尼器构件在空腔中具有自由的径向内端，并且在空腔中具有自由的径向外端。 阻尼器构件在空腔中自由浮动。
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公开(公告)号：US20140119927A1
公开(公告)日：2014-05-01
申请号：US13660455
申请日：2012-10-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David P. Houston
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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