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1. 发明授权

US5313786A Gas turbine blade damper 失效
标题翻译：燃气轮机叶片阻尼器
公开(公告)号：US5313786A
公开(公告)日：1994-05-24
申请号：US980085
申请日：1992-11-24
申请人： Wieslaw A. Chlus , Michael Gonsor , David P. Houston , Paul D. Kudra
发明人： Wieslaw A. Chlus , Michael Gonsor , David P. Houston , Paul D. Kudra
IPC分类号： F01D5/26 , F01D5/22 , F01D11/00 , F02C3/00
CPC分类号： F01D5/22 , F01D11/006 , F05D2260/97 , Y10S416/50
摘要： An integrated damper and windage cover 52 has a windage cover portion 56 cantilevered at the upstream end, free of contact with the blade platform 24, 32. The contact portion 54 is rigid and bears against the underside of the blade platform 24, spanning blade platform clearance 50.
摘要翻译：集成的阻尼器和风挡盖52具有在上游端悬臂的防风罩部分56，与叶片平台24,32没有接触。接触部分54是刚性的，并且抵靠在叶片平台24的下侧，跨越叶片平台清关50。

2. 发明授权

US5284421A Rotor blade with platform support and damper positioning means 失效
标题翻译：转子叶片带平台支撑和阻尼器定位装置
公开(公告)号：US5284421A
公开(公告)日：1994-02-08
申请号：US980848
申请日：1992-11-24
申请人： Wieslaw A. Chlus , David P. Houston
发明人： Wieslaw A. Chlus , David P. Houston
IPC分类号： F01D5/26 , F01D5/22 , F01D5/10
CPC分类号： F01D5/22 , Y10S416/50
摘要： A rotor blade having axially spaced gussets disposed between a root portion and a platform is disclosed. Various construction details are developed which provide a gusset providing both platform support and damper positioning means. In one particular embodiment, a rotor blade assembly includes a plurality of circumferentially spaced rotor blades having dampers disposed between adjacent blades, wherein each blade includes an axially spaced pair of gussets extending laterally from the rotor blade. The gussets extend from a root portion of the rotor blade to a platform and provide radial support of the platform during rotation of the rotor assembly. The gussets include a curved lateral edge which, during rotation of the rotor assembly, urges the damper away from the root portion of the blade.
摘要翻译：公开了一种具有设置在根部和平台之间的具有轴向间隔的角撑板的转子叶片。开发了各种构造细节，其提供提供平台支撑和阻尼器定位装置的角撑板。在一个具体实施例中，转子叶片组件包括多个周向间隔开的转子叶片，其具有设置在相邻叶片之间的阻尼器，其中每个叶片包括从转子叶片横向延伸的轴向间隔开的一对角撑板。角撑板从转子叶片的根部延伸到平台并且在转子组件旋转期间提供平台的径向支撑。角撑板包括弯曲的侧边缘，其在转子组件的旋转期间促使阻尼器远离叶片的根部。

3. 发明授权

US5785499A Turbine blade damper and seal 失效
标题翻译：涡轮叶片阻尼器和密封
公开(公告)号：US5785499A
公开(公告)日：1998-07-28
申请号：US773017
申请日：1996-12-24
申请人： David P. Houston , Natalie A. Pelland , Michael Gonsor , David Airey
发明人： David P. Houston , Natalie A. Pelland , Michael Gonsor , David Airey
IPC分类号： F01D5/26 , F01D5/30 , F01D11/00 , F04D29/18
CPC分类号： F01D11/008 , Y02T50/671 , Y10S416/50
摘要： An integral damper and seal for a turbine blade in a gas turbine engine includes a damper portion which contacts the platform and at least one sealing portion, angled radially inward from the damper portion, which makes contact with and seals against the platform.
摘要翻译：用于燃气涡轮发动机中的涡轮叶片的整体式阻尼器和密封件包括阻尼部分，该阻尼器部分接触平台和至少一个密封部分，该阻挡部分与阻尼部分径向向内成角度，其与平台接触并密封。

4. 发明授权

US5827047A Turbine blade damper and seal 失效
标题翻译：涡轮叶片阻尼器和密封
公开(公告)号：US5827047A
公开(公告)日：1998-10-27
申请号：US671462
申请日：1996-06-27
申请人： Michael Gonsor , Sanford E. Kelley, III , David P. Houston
发明人： Michael Gonsor , Sanford E. Kelley, III , David P. Houston
IPC分类号： F01D5/10 , F01D5/22 , F01D5/26 , F01D5/30 , F01D11/00 , F16F7/00 , F16F15/02
CPC分类号： F01D5/22 , F01D11/008 , F01D5/26 , Y10S416/50
摘要： A damper for a turbine blade in a gas turbine engine includes a main body and may include at least one extended end which is adapted to clear radially inner surfaces of two adjacent blade platforms, to enhance the damping profile of the damper and radial support for a seal. An associated seal for the turbine blade includes supported and sealing portions and may further include a locator that interfaces with a catch structure on the blade to maintain the seal in the proper axial position with respect to the radially inner surfaces of the adjacent platforms. The seal may further include a projection adapted to provide interference with the blade in the event that the damper and seal are installed improperly with respect to each other to prevent such improper assembly.
摘要翻译：用于燃气涡轮发动机中的涡轮叶片的阻尼器包括主体，并且可以包括至少一个延伸端，其适于清除两个相邻叶片平台的径向内表面，以增强阻尼器的阻尼曲线和径向支撑件密封。用于涡轮机叶片的相关密封件包括支撑和密封部分，并且还可以包括与叶片上的捕获结构相接合的定位器，以将密封件相对于相邻平台的径向内表面保持在适当的轴向位置。密封件还可包括适于在阻尼器和密封件相对于彼此不适当地安装以防止这种不正确组装的情况下提供与叶片的干涉的突起。

5. 发明授权

US09267380B2 Airfoil including loose damper 有权
标题翻译：机翼包括松动阻尼器
公开(公告)号：US09267380B2
公开(公告)日：2016-02-23
申请号：US13454488
申请日：2012-04-24
申请人： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
发明人： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
IPC分类号： F01D5/16 , B22F3/105 , B22F5/04 , B22F5/10
CPC分类号： 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
摘要： 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 loose within the cavity.
摘要翻译：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松动。

6. 发明申请

US20130276457A1 AIRFOIL INCLUDING LOOSE DAMPER 有权
标题翻译：飞机包括松动阻尼器
公开(公告)号：US20130276457A1
公开(公告)日：2013-10-24
申请号：US13454488
申请日：2012-04-24
申请人： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
发明人： David P. Houston , Tracy A. Propheter-Hinckley , Benjamin T. Fisk , Anita L. Tracy
IPC分类号： F01D5/16 , F02C3/04
CPC分类号： 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
摘要： 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 loose within the cavity.
摘要翻译：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松动。

7. 发明授权

US5924699A Turbine blade platform seal 失效
标题翻译：涡轮叶片平台密封
公开(公告)号：US5924699A
公开(公告)日：1999-07-20
申请号：US772962
申请日：1996-12-24
申请人： David Airey , Natalie A. Pelland , David P. Houston
发明人： David Airey , Natalie A. Pelland , David P. Houston
IPC分类号： F01D5/30 , F01D11/00 , F16J15/02 , F01D11/02
CPC分类号： F01D11/008 , Y10S416/50
摘要： A seal for a turbine blade in a gas turbine engine has a sealing portion with two subportions, where the subportions are longitudinally offset from one another, so that the seal may provide sealing for adjacent turbine blades having longitudinally offset inner platform surfaces. The offset between the sealing subportions should correspond generally to the offset between the platform surfaces.
摘要翻译：用于燃气涡轮发动机中的涡轮叶片的密封件具有密封部分，其具有两个子部分，其中子部分彼此纵向偏移，使得密封件可以为具有纵向偏移的内平台表面的相邻涡轮叶片提供密封。密封子部分之间的偏移量通常应对应于平台表面之间的偏移。

8. 发明申请

US20170268428A1 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
公开(公告)号：US20170268428A1
公开(公告)日：2017-09-21
申请号：US15447703
申请日：2017-03-02
申请人： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
发明人： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
IPC分类号： F02C7/36 , F01D25/16 , F02C7/06 , F02K3/072 , F01D5/02
CPC分类号： 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
摘要： 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.

9. 发明申请

US20130280074A1 AIRFOIL SUPPORT METHOD AND APPARATUS 有权
标题翻译： AIRFOIL支持方法和设备
公开(公告)号：US20130280074A1
公开(公告)日：2013-10-24
申请号：US13454599
申请日：2012-04-24
申请人： Tracy A. Propheter-Hinckley , David P. Houston , Anita L. Tracy
发明人： Tracy A. Propheter-Hinckley , David P. Houston , Anita L. Tracy
IPC分类号： F04D29/34 , B23P15/00
CPC分类号： F01D5/147 , B22F3/1055 , B22F5/04 , B33Y80/00 , F04D29/324 , F04D29/388 , F05D2230/30 , Y02P10/295 , Y02T50/673 , Y10T29/49236
摘要： A support for an airfoil includes a trunk and a limb extending from the trunk for distribution within the airfoil.
摘要翻译：对翼型的支撑包括一个行李箱和一个从躯干延伸的肢体，用于分配在翼型内。

10. 发明申请

US20130276455A1 AIRFOIL WITH BREAK-WAY, FREE-FLOATING DAMPER MEMBER 有权
标题翻译：具有断路，自由浮动阻尼器构件的空气动力
公开(公告)号：US20130276455A1
公开(公告)日：2013-10-24
申请号：US13454183
申请日：2012-04-24
申请人： Benjamin T. Fisk , Tracy A. Propheter-Hinckley , Gregory M. Dolansky , David P. Houston , Anita L. Tracy
发明人： Benjamin T. Fisk , Tracy A. Propheter-Hinckley , Gregory M. Dolansky , David P. Houston , Anita L. Tracy
IPC分类号： F01D5/16 , B05D1/36 , F02C3/04
CPC分类号： F01D5/16
摘要： 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.
摘要翻译：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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