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公开(公告)号：US20170268428A1
公开(公告)日：2017-09-21
申请号：US15447703
申请日：2017-03-02
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.
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公开(公告)号：US09267380B2
公开(公告)日：2016-02-23
申请号：US13454488
申请日：2012-04-24
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。
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公开(公告)号：US20130276457A1
公开(公告)日：2013-10-24
申请号：US13454488
申请日：2012-04-24
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。
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公开(公告)号：US5924699A
公开(公告)日：1999-07-20
申请号：US772962
申请日：1996-12-24
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。
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公开(公告)号：US5785499A
公开(公告)日：1998-07-28
申请号：US773017
申请日：1996-12-24
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。
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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
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。
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公开(公告)号：US20130280074A1
公开(公告)日：2013-10-24
申请号：US13454599
申请日：2012-04-24
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。
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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
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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公开(公告)号：US09074482B2
公开(公告)日：2015-07-07
申请号：US13454599
申请日：2012-04-24
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。
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10.发明申请公开(公告)号：US20130142640A1
公开(公告)日：2013-06-06
申请号：US13309685
申请日：2011-12-02
CPC分类号： F01D9/041 , F01D25/06 , F05D2260/961 , Y10T29/49323
摘要： A stator for a turbo-machine having a plurality of airfoils extending radially therefrom has a base from which the airfoils depend, and slits disposed in the base, each slit disposed adjacent a pair of airfoils, wherein a first set of adjacent slits and a distance between a second set of adjacent slits varies
摘要翻译： 一种用于涡轮机的定子，其具有从其径向延伸的多个翼型件，其具有基座，翼型件从该基座所依赖的基座和设置在基座中的狭缝，每个狭缝设置成邻近一对翼型件，其中，第一组相邻狭缝和距离 在第二组相邻狭缝之间变化
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