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公开(公告)号：US10704401B2
公开(公告)日：2020-07-07
申请号：US16100615
申请日：2018-08-10
发明人： Nicholas Aiello , James Cosby
摘要： An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.
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公开(公告)号：US20160146023A1
公开(公告)日：2016-05-26
申请号：US14933129
申请日：2015-11-05
CPC分类号： B23P15/006 , F01D5/282 , F01D5/34 , F05D2300/6033
摘要： A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.
摘要翻译： 构造成用于在燃气涡轮机内操作的推进式发动机转子包括多个间隔开的叶片叶片，周向地固定在外箍型轮缘上。 至少两个翼型叶片具有构造成从轮缘延伸穿过或至少径向向内延伸的整体根部。 编织纤维系统规定，在将纤维和包裹的根部浸入陶瓷或其它复合基质材料中以形成复合环之前，叶片根部被多个编织纤维叉指地包裹。 复合环限定转子的内部主体，包括通过转子的旋转轴线并且具有比转子轮辋更低的质量的孔。 根部之间的机织纤维界面增加了翼型相对于复合环的拉伸载荷能力，并提高了转子的自维持半径。
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公开(公告)号：US20160003076A1
公开(公告)日：2016-01-07
申请号：US14769951
申请日：2014-02-12
发明人： Nicholas Aiello , Uyen Phan
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D5/20 , F01D11/02 , F01D11/08 , F01D11/122 , F01D11/127 , F05D2220/32 , F05D2240/55 , F05D2250/13 , F05D2250/292 , F05D2300/175 , F16J15/445 , Y02T50/671
摘要： A knife edge seal includes a pedestal and a knife edge with a tip and a base. The base rests on the pedestal. The base has a first width and the tip has a second width, and the ratio of the first width to the second width is in the range of 5:1 to 15:1. A gas turbine engine and a method of sealing a high pressure area from a low pressure area are also disclosed.
摘要翻译： 刀刃密封件包括底座和具有尖端和底座的刀刃。 基座搁在基座上。 底座具有第一宽度，并且尖端具有第二宽度，并且第一宽度与第二宽度的比率在5:1至15:1的范围内。 还公开了一种燃气涡轮发动机和从低压区域密封高压区域的方法。
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公开(公告)号：US20140127007A1
公开(公告)日：2014-05-08
申请号：US13671205
申请日：2012-11-07
IPC分类号： F01D11/00
CPC分类号： F01D11/001
摘要： A rotary seal for sealing a bladed rotor of a gas turbine engine to a stator thereof comprises a sealing element and a sealing element support comprising a radially outer edge portion on which the sealing element is fixed, a radially inner mounting portion adapted to be attached to a supported rotor hub, and a flexible, medial web portion extending between the radially outer edge portion and the radially inner mounting portion.
摘要翻译： 用于将燃气涡轮发动机的叶片转子密封到其定子的旋转密封件包括密封元件和密封元件支撑件，所述密封元件和密封元件支撑件包括固定密封元件的径向外边缘部分，适于附接到 支撑的转子轮毂和在径向外边缘部分和径向内部安装部分之间延伸的柔性内侧腹板部分。
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公开(公告)号：US20140086742A1
公开(公告)日：2014-03-27
申请号：US13627036
申请日：2012-09-26
发明人： Nicholas Aiello , Raji Mali
CPC分类号： F01D5/3038 , Y10T29/49332
摘要： An example turbomachine rotor provides a groove that is annular and is configured to receive a root of an airfoil, the groove having a radial cross-sectional area. A ratio of the radial cross-sectional area of the groove to a radial cross-sectional area of the root received within the annular groove is from 2 to 5.
摘要翻译： 涡轮机转子的一个实例提供了一个环形槽，并被构造为容纳翼型的根部，该槽具有径向横截面积。 槽的径向横截面积与在环形槽内容纳的根部的径向横截面积的比为2〜5。
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公开(公告)号：US10029336B2
公开(公告)日：2018-07-24
申请号：US14933129
申请日：2015-11-05
摘要： A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.
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公开(公告)号：US20160138399A1
公开(公告)日：2016-05-19
申请号：US14929771
申请日：2015-11-02
CPC分类号： F01D5/02 , F01D5/06 , F01D5/34 , F02C3/04 , F05D2220/32 , F05D2230/31 , F05D2230/60 , F05D2240/20 , F05D2240/35 , F05D2300/224 , F05D2300/48 , F05D2300/603 , F05D2300/6032 , F05D2300/614 , Y02T50/672
摘要： A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.
摘要翻译： 公开了一种用于燃气涡轮发动机的结构增强转子盘。 转子盘可以包括主体，其包括构造成支撑翼型件（其可以与翼型件分离或一体的）的边缘，设置在轮辋径向内侧的轴向延伸的孔以及连接轮辋和钻孔的径向延伸的腹板 。 孔可以包括轴向外边缘和在外边缘和腹板之间轴向形成的至少一个周向延伸的环形凹部。 转子盘还可以包括保持在环形凹部中的环形圈，并且环形圈可以由与转子盘的主体不同的材料形成，以便增加转子盘的自维持半径。
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公开(公告)号：US20160076386A1
公开(公告)日：2016-03-17
申请号：US14787013
申请日：2014-02-27
发明人： Nicholas Aiello , John C. Duong
CPC分类号： F01D5/26 , F01D5/141 , F01D5/3007 , F01D5/3038 , F02C3/04 , F04D29/322 , F05D2220/32 , F05D2230/50 , F05D2240/30 , F05D2250/70
摘要： A root extending from a platform of an airfoil is disclosed. The root may include a first portion having a generally cylindrical shape, and a second portion extending from the first portion to the platform. The second portion may have a circumference larger than a circumference of the first portion.
摘要翻译： 公开了从翼型的平台延伸的根部。 根部可以包括具有大致圆柱形形状的第一部分和从第一部分延伸到平台的第二部分。 第二部分可以具有大于第一部分的圆周的圆周。
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公开(公告)号：US20160069203A1
公开(公告)日：2016-03-10
申请号：US14783925
申请日：2013-04-12
发明人： Nicholas Aiello
CPC分类号： F01D11/006 , F01D5/02 , F01D5/3007 , F01D5/34 , F04D29/322 , F04D29/329 , F05D2220/32 , F05D2240/20 , F05D2240/55 , F05D2260/941 , Y02T50/671
摘要： An integrally bladed rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a radially inner hoop extending circumferentially about an axis, a plurality of circumferentially spaced, axially extending slots, separated by respective blade supports, and a seal system that includes seal fingers extending axially through the slots.
摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机的整体叶片转子包括径向内环，其围绕轴线周向延伸，多个沿周向间隔开的轴向延伸的槽，由相应的叶片支撑件分开， 以及密封系统，其包括轴向延伸穿过狭槽的密封指。
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公开(公告)号：US10648481B2
公开(公告)日：2020-05-12
申请号：US14929701
申请日：2015-11-02
摘要： A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.
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