公开(公告)号：US20160097294A1

公开(公告)日：2016-04-07

申请号：US14852819

申请日：2015-09-14

Applicant: United Technologies Corporation

Inventor： Ross Wilson ,  Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John W. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Edwin Otero ,  Alan W. Stoner

IPC: F01D11/08 ,  F16J15/3268 ,  F16J15/3288 ,  F01D5/02 ,  F01D25/28

CPC classification number: F01D11/08 ,  F01D5/02 ,  F01D11/001 ,  F01D11/025 ,  F01D25/28 ,  F05D2220/32 ,  F05D2240/56 ,  F16J15/3268 ,  F16J15/3288 ,  F16J15/442

Abstract: A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.

Abstract translation: 刷密封板可以包括具有从平环的内径突出的刷毛的平环。 刷密封板可以具有跑道槽，以允许平环相对于保持销在径向方向上移动。 刷毛可以一定角度从平环的内径突出。 可以通过平环形成槽，并且槽可以成角度。 平环可以是周向不连续的。 平环可以进一步包括保持开口，该保持开口构造成相对于保持销将平环固定就位。

公开(公告)号：US20160069193A1

公开(公告)日：2016-03-10

申请号：US14841265

申请日：2015-08-31

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Elizabeth F. Vinson

IPC: F01D5/18 ,  F02C3/04

CPC classification number: F01D5/187 ,  F01D5/082 ,  F02C3/04 ,  F04D29/053 ,  F04D29/321 ,  F04D29/584 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/201 ,  Y02T50/676

Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor and mechanically connected to the compressor section via a shaft. Multiple rotors are disposed in one of the compressor section and the turbine section. Each of the rotors includes a rotor disk portion having a radially inward bore, and is static relative to the shaft. Each rotor is axially adjacent at least one other rotor and a gap is defined between each rotor and an adjacent rotor. A cooling passage for a cooling flow is defined between the shaft and the rotors, and a cooling flow redirection component is disposed at the gap and is operable to redirect the cooling flow in the cooling passage into the gap.

Abstract translation: 燃气涡轮发动机包括压缩机部分，流体连接到压缩机部分的燃烧器和流体连接到燃烧器并经由轴机械连接到压缩机部分的涡轮部分。 多个转子设置在压缩机部分和涡轮部分之一中。 每个转子包括具有径向向内的孔的转子盘部分，并且相对于轴是静态的。 每个转子轴向相邻至少一个其他转子，并且在每个转子和相邻转子之间限定间隙。 用于冷却流的冷却通道限定在轴和转子之间，并且冷却流重定向部件设置在间隙处，并且可操作以将冷却通道中的冷却流重定向到间隙中。

公开(公告)号：US20160053624A1

公开(公告)日：2016-02-25

申请号：US14781263

申请日：2014-04-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey ,  Brandon T. Rouse ,  Mark Borja ,  Igor S. Garcia ,  John R. Farris ,  Thomas Almy ,  Brian R. Pelletier

IPC: F01D11/08 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D11/12 ,  F01D11/14 ,  F01D11/20 ,  F01D11/22 ,  F01D11/24 ,  F01D25/24 ,  Y02T50/672

Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.

Abstract translation: 用于燃气涡轮发动机级的径向位置控制组件包括壳体结构。 支撑结构由壳体结构可操作地支撑。 支撑环可操作地支撑所支撑的结构。 支撑结构和支撑环具有不同的热膨胀系数。 密封结构与支撑结构相邻。 基于相邻的支撑结构之间的周向间隙，并且基于支撑环和支撑结构之间的径向间隙，支撑环在热瞬变期间的间隙处相对于密封结构保持支撑结构。 销支撑相对于壳体结构的支撑结构，并且被配置为将支撑环与支撑结构上的负载隔离开。

公开(公告)号：US20160047258A1

公开(公告)日：2016-02-18

申请号：US14737852

申请日：2015-06-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Theodore W. Hall ,  Michael G. McCaffrey ,  Zachary Mott

IPC: F01D11/00 ,  F01D11/08 ,  F01D9/04

CPC classification number: F01D11/005 ,  F01D9/04 ,  F01D11/08 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/56 ,  F05D2240/80 ,  F05D2260/205

Abstract: A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.

Abstract translation: 燃气涡轮发动机的涡轮机部分包括在叶片平台和叶片外部空气密封件之间延伸的密封件。

公开(公告)号：US20160032754A1

公开(公告)日：2016-02-04

申请号：US14749695

申请日：2015-06-25

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/20 ,  F02C7/28 ,  F01D25/24 ,  F02C3/04

CPC classification number: F01D11/20 ,  F01D11/22 ,  F01D25/24 ,  F02C3/04 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2240/55 ,  Y10T29/49318

Abstract: An adjustable blade outer air seal apparatus includes a case that extends circumferentially around an axis, a support ring non-rigidly mounted to the case on spring connections radially inwards of the case, whereby the support ring floats with respect to the case, and at least one blade outer air seal segment that is radially adjustable relative to the support ring.

Abstract translation: 可调节叶片外部空气密封装置包括围绕轴线周向延伸的壳体，在壳体的径向向内的弹簧连接处非刚性地安装到壳体上的支撑环，由此支撑环相对于壳体浮动，并且至少 一个叶片外部空气密封段，其相对于支撑环可径向调节。

公开(公告)号：US20150337673A1

公开(公告)日：2015-11-26

申请号：US14759317

申请日：2013-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey ,  Igor Garcia ,  John R. Farris ,  Brian R. Pelletier ,  Thomas Almy ,  Brandon T. Rouse ,  Mark Borja

IPC: F01D11/08 ,  B23P19/00 ,  F01D9/04

CPC classification number: F01D11/08 ,  B23P19/00 ,  F01D9/04 ,  F01D11/20 ,  F01D25/246 ,  Y10T29/49325

Abstract: A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.

Abstract translation: 公开了具有至少两个段的间隙控制环。 每个片段与相邻的片段互锁以形成完整的箍间隙控制环。 分离的载体和密封件或一体式载体和密封件可以安装在间隙控制环上。 间隙控制环的分段结构允许与现有技术的单件间隙控制环相比，用于燃气涡轮发动机的分段壳体更简单的组装。 分段结构还可以与单件预组装和多级转子一起使用。

公开(公告)号：US20150252686A1

公开(公告)日：2015-09-10

申请号：US14492737

申请日：2014-09-22

Applicant: United Technologies Corporation

Inventor： David J. Wasserman ,  Michael G. McCaffrey ,  Michael G. Abbott

IPC: F01D21/00 ,  F01D11/12

CPC classification number: F01D21/003 ,  F01D11/12 ,  F05D2250/232 ,  F05D2260/80 ,  Y02T50/672

Abstract: A system includes, in one example, a shroud configured to circumscribe a plurality of rotor blades of a gas rotor engine, and at least one rub button including a head portion having a height configured to extend into a flow path region of the shroud along a central axis of the rub button that extends radially into the flow path region. The head portion includes a profile, orthogonal to the central axis, that varies according to a defined function of the height of the head portion.

Abstract translation: 在一个示例中，系统包括被配置为围绕气体转子发动机的多个转子叶片的护罩，以及至少一个摩擦按钮，其包括具有高度的头部，所述头部具有被配置为沿着护罩的一个 摩擦按钮的中心轴线径向延伸到流路区域。 头部包括与中心轴正交的轮廓，其根据头部高度的限定函数而变化。

公开(公告)号：US20140255174A1

公开(公告)日：2014-09-11

申请号：US13723941

申请日：2012-12-21

Applicant: United Technologies Corporation

Inventor： Shelton O. Duelm ,  Michael G. McCaffrey

IPC: F01D5/28 ,  F01D9/04

Abstract: A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform. An outer wrap is disposed about an outer periphery of the annular ring and over an interface between outer platforms of adjacent ones of the plurality of vane segments.

Abstract translation: 公开了一种用于燃气涡轮发动机的叶片组件，并且包括形成环形环的多个单独叶片段。 多个叶片段中的每一个由包括在内平台和外平台之间延伸的至少一个翼型的陶瓷基复合材料形成。 围绕环形圈的外周并且在多个叶片段中的相邻叶片段的外平台之间的界面上设置外包裹物。

公开(公告)号：US11773723B2

公开(公告)日：2023-10-03

申请号：US16685457

申请日：2019-11-15

Applicant: United Technologies Corporation

Inventor： Bryan P. Dube ,  Michael G. McCaffrey

IPC: F01D5/14

CPC classification number: F01D5/14 ,  F05D2220/32 ,  F05D2260/22141 ,  F05D2300/6033

Abstract: An airfoil includes an airfoil section that has a ceramic airfoil wall that defines a suction side and a pressure side. There is an interior cavity in the airfoil section. A rib spans across the interior cavity and connects the suction side and the pressure side. The rib has a thermal conductance element that is configured to conduct heat away from the suction side and the pressure side.

公开(公告)号：US11624287B2

公开(公告)日：2023-04-11

申请号：US16797123

申请日：2020-02-21

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Bryan P. Dube

IPC: F01D5/18 ,  F01D5/28 ,  C04B35/628 ,  C04B35/80 ,  C23C16/04

Abstract: Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.