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1. 发明申请

US20100313573A1 APU BLEED VALVE WITH INTEGRAL ANTI-SURGE PORT 有权
标题翻译：具有整体防爆端口的APU BLEED VALVE
公开(公告)号：US20100313573A1
公开(公告)日：2010-12-16
申请号：US12483741
申请日：2009-06-12
申请人： Jeremy J. Walters , Robert W. Smith , Anthony C. Jones
发明人： Jeremy J. Walters , Robert W. Smith , Anthony C. Jones
IPC分类号： F02C6/04 , F16K1/22
CPC分类号： F16K11/0525 , F02C9/18 , F05D2220/50
摘要： A compressor bleed air valve in an auxiliary power unit (“APU”) modulates bleed air flow both for accessory pneumatic systems powered by the bleed air and for reducing or removing surge in the compressor.
摘要翻译：辅助动力单元（“APU”）中的压缩机排气阀调节由排气供电的附件气动系统和用于减少或消除压缩机浪涌的排气流。

2. 发明授权

US08356486B2 APU bleed valve with integral anti-surge port 有权
标题翻译：具有整体防喘振端口的APU放气阀
公开(公告)号：US08356486B2
公开(公告)日：2013-01-22
申请号：US12483741
申请日：2009-06-12
申请人： Jeremy J. Walters , Robert W. Smith , Anthony C. Jones
发明人： Jeremy J. Walters , Robert W. Smith , Anthony C. Jones
IPC分类号： F02C6/08 , F02C7/32 , F02C9/18
CPC分类号： F16K11/0525 , F02C9/18 , F05D2220/50
摘要： A compressor bleed air valve in an auxiliary power unit (“APU”) modulates bleed air flow both for accessory pneumatic systems powered by the bleed air and for reducing or removing surge in the compressor.
摘要翻译：辅助动力单元（APU）中的压缩机排气阀调节排放气流，用于由排气供电的附件气动系统，并用于减少或消除压缩机中的浪涌。

3. 发明授权

US10087762B2 Scallop curvature for radial turbine wheel 有权
公开(公告)号：US10087762B2
公开(公告)日：2018-10-02
申请号：US13179634
申请日：2011-07-11
申请人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
发明人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Anthony C. Jones
IPC分类号： F01D5/04
摘要： A turbine wheel is disposed about an axis and has a back face including a plurality of lobes disposed about a periphery of the back face. The lobes define scalloped areas therebetween. The scalloped areas are further defined by a radius BR2 that blends into a first lobe and into a radius BR1 that also blends into a flat area.

4. 发明授权

US09297266B2 Method of sealing combustor liner and turbine nozzle interface 有权
标题翻译：密封燃烧器衬套和涡轮喷嘴接口的方法
公开(公告)号：US09297266B2
公开(公告)日：2016-03-29
申请号：US13463900
申请日：2012-05-04
申请人： David Ronald Adair , Walter Ernest Ainslie , Gordon F. Jewess , Anthony C. Jones , Eric J. Alexander
发明人： David Ronald Adair , Walter Ernest Ainslie , Gordon F. Jewess , Anthony C. Jones , Eric J. Alexander
IPC分类号： F23R3/50 , F01D9/02 , F01D11/00 , F16J15/08
CPC分类号： F01D9/023 , F01D11/003 , F01D11/005 , F16J15/0887 , F23R3/50 , F23R2900/00012
摘要： An example method of sealing an interface within a gas turbine engine includes holding a sealing ring arrangement relative to a turbine nozzle using a flange extending from a combustor liner. The method further includes urging the sealing ring arrangement toward a sealed relationship with the turbine nozzle.
摘要翻译：密封燃气涡轮发动机内的界面的示例性方法包括使用从燃烧器衬套延伸的凸缘相对于涡轮喷嘴保持密封环装置。该方法还包括将密封环装置推向与涡轮喷嘴的密封关系。

5. 发明授权

US08839625B2 Gas turbine engine diffuser having air flow channels with varying widths 有权
标题翻译：具有不同宽度的气流通道的燃气涡轮发动机扩散器
公开(公告)号：US08839625B2
公开(公告)日：2014-09-23
申请号：US12796028
申请日：2010-06-08
申请人： James C. Napier , Anthony C. Jones
发明人： James C. Napier , Anthony C. Jones
IPC分类号： F04D29/44 , F04D29/54 , F02C7/04 , F01D9/02
CPC分类号： F02C7/04 , F01D9/02 , F04D29/444 , F04D29/547
摘要： An exemplary diffuser includes a plurality of air flow channels defined by a corresponding plurality of vanes. The vanes extend from a first side of the diffuser and define a width of the air flow channel between the corresponding plurality of vanes. The first side has at least one tapered surface extending from an inner radial position to an outer radial position. The distance between a tapered surface and a top side of the plurality of the vanes defines a depth of the air flow channel. The width of the air flow channel varies relative to the depth of the air flow channel along the length of the air flow channel.
摘要翻译：示例性扩散器包括由对应的多个叶片限定的多个空气流动通道。叶片从扩散器的第一侧延伸并且限定相应的多个叶片之间的空气流动通道的宽度。第一侧具有从内部径向位置延伸到外部径向位置的至少一个锥形表面。多个叶片的锥形表面和顶侧之间的距离限定了空气流动通道的深度。空气流动通道的宽度相对于气流通道的深度沿空气流动通道的长度变化。

6. 发明授权

US08556027B2 Eductor exhaust silencer assembly with bypass gasflow 有权
标题翻译：带旁路气流的电机排气消声器组件
公开(公告)号：US08556027B2
公开(公告)日：2013-10-15
申请号：US13170600
申请日：2011-06-28
申请人： Jay M. Francisco , Anthony C. Jones , Greg R. Giddings , Nagamany Thayalakhandan , Jason Peel
发明人： Jay M. Francisco , Anthony C. Jones , Greg R. Giddings , Nagamany Thayalakhandan , Jason Peel
IPC分类号： F02K1/82 , F02K1/34 , F01N1/14 , F02K1/00 , F01N1/00
CPC分类号： F02K1/46 , B64D33/06 , B64D2041/002 , F01N1/08 , F02K1/827 , F05D2220/50 , Y02T50/671
摘要： An exhaust silencer assembly for use with an auxiliary power unit includes an eductor and a discharge pipe. The eductor is disposed downstream of the auxiliary power unit and has an entrance opening at a forward axial end thereof. The entrance opening is configured to receive exhaust airflow from the auxiliary power unit. The discharge pipe extends from the auxiliary power unit and communicates with the exhaust silencer assembly downstream of the entrance opening of the eductor.
摘要翻译：与辅助动力单元一起使用的排气消音器组件包括喷射器和排出管。喷射器设置在辅助动力单元的下游，并且在其前轴向端部具有入口。入口开口构造成从辅助动力单元接收排气。排放管从辅助动力单元延伸，并与喷射器入口的下游的排气消声器组件连通。

7. 发明授权

US08147208B2 Axially segmented impeller 有权
标题翻译：轴向分段叶轮
公开(公告)号：US08147208B2
公开(公告)日：2012-04-03
申请号：US12392160
申请日：2009-02-25
申请人： Behzad Hagshenas , Anthony C. Jones
发明人： Behzad Hagshenas , Anthony C. Jones
IPC分类号： B63H1/26 , B63H7/02
CPC分类号： F01D5/026 , F04D29/285
摘要： An impeller with an axial inlet in relation to an impeller axis for pressurizing a fluid has: a nose section that has a nose section central hub and multiple nose vane sections, each nose vane section extending from a leading edge to a generally radial nose section interface plane; a tail section that has a tail section central hub and multiple tail vane sections, each tail vane section extending from a generally radial tail section interface plane to a vane tip; a coupling that joins the nose section central hub to the tail section central hub and aligns each one of the nose vane sections with a corresponding one of the tail vane sections with an axial gap between the radial nose section interface plane and the radial tail section interface plane.
摘要翻译：具有相对于用于加压流体的叶轮轴线的轴向入口的叶轮具有：鼻部，其具有鼻部中心毂和多个鼻叶部分，每个鼻翼部分从前缘延伸到大致径向的鼻部部分界面飞机尾部具有尾部中心毂和多个尾叶段，每个尾叶段从大致径向的尾部截面平面延伸到叶片尖端; 将所述鼻部中心毂连接到所述尾部中心毂并将所述鼻翼部分中的每一个与所述尾叶片部分中的相应一个对准，所述联接器在所述径向鼻部部分界面和所述径向尾部部分界面之间具有轴向间隙飞机

8. 发明申请

US20080135336A1 Under race bearing lubrication system for gas turbine engines 审中-公开
标题翻译：用于燃气轮机发动机的滚动轴承润滑系统
公开(公告)号：US20080135336A1
公开(公告)日：2008-06-12
申请号：US11636791
申请日：2006-12-11
申请人： Gordon F. Jewess , Mark N. Shatz , Anthony C. Jones , Eric J. Alexander , Jeffrey V. Stenberg
发明人： Gordon F. Jewess , Mark N. Shatz , Anthony C. Jones , Eric J. Alexander , Jeffrey V. Stenberg
IPC分类号： F01D25/18
CPC分类号： F01D25/18 , F01D25/16 , F05D2240/54 , F05D2250/82 , F16C33/6677 , F16C2360/23
摘要： A bearing lubrication system for a gas turbine engine that has bearings supporting a rotor shaft comprises a housing for the engine that serves as a primary static structural support; a rotor shaft for mounting rotational components of the engine; at least two bearings for supporting the rotor shaft within the housing, each bearing comprising an inner race that couples to the rotor shaft comprising a plurality of inner race lubricant apertures that extend radially through the inner race that supply pressurised lubricant to selected regions within the bearing, an outer race that couples to a primary static structural support, a plurality of ball elements between the inner race and the outer race and a ball cage to maintain the relative radial spacing of the ball elements between each other within the inner race and the outer race; and a lubricant distribution system for delivering pressurised lubricant to the inner race apertures in each of the bearings.
摘要翻译：一种用于燃气涡轮发动机的轴承润滑系统，其具有支撑转子轴的轴承，包括用作主要静态结构支撑件的用于发动机的壳体; 用于安装发动机的旋转部件的转子轴; 至少两个用于将转子轴支撑在壳体内的轴承，每个轴承包括联接到转子轴的内座圈，该内座圈包括多个径向延伸穿过内座圈的内圈润滑剂孔，该内座圈将加压润滑剂供应到轴承内的选定区域，外圈，其耦合到主静态结构支撑件，在内圈和外座圈之间的多个球元件，以及球保持架，用于在内圈和外圈之间保持球元件在彼此之间的相对径向间隔种族; 以及用于将加压润滑剂输送到每个轴承中的内圈孔的润滑剂分配系统。

9. 发明授权

US09254924B2 Pressure influencing assembly for an aircraft auxiliary system 有权
标题翻译：用于飞机辅助系统的压力影响组件
公开(公告)号：US09254924B2
公开(公告)日：2016-02-09
申请号：US13208824
申请日：2011-08-12
申请人： Eric Andrew Nager , Anthony C. Jones , Behzad Hagshenas , Nagamany Thayalakhandan
发明人： Eric Andrew Nager , Anthony C. Jones , Behzad Hagshenas , Nagamany Thayalakhandan
IPC分类号： B64D41/00 , B64D33/02
CPC分类号： B64D41/00 , B64D2033/0213 , Y10T137/0536
摘要： An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis.
摘要翻译：用于飞机辅助系统的示例性压力影响组件，到飞行器辅助系统的入口和来自飞行器辅助系统的排气口。入口开口和排气开口面两者至少部分地沿径向远离轴线。入口开口中的至少一些相对于轴线与排气口的至少一些周向对准。

10. 发明授权

US08579591B2 Centrifugal compressor impeller 有权
标题翻译：离心式压缩机叶轮
公开(公告)号：US08579591B2
公开(公告)日：2013-11-12
申请号：US12914335
申请日：2010-10-28
申请人： John Chen Chiang Ho , Bo Zheng , Timothy M. Hollman , Kevin K. Taft , Jang Y. Jo , Anthony C. Jones
发明人： John Chen Chiang Ho , Bo Zheng , Timothy M. Hollman , Kevin K. Taft , Jang Y. Jo , Anthony C. Jones
IPC分类号： F01D5/04 , F01D5/14
CPC分类号： F04D29/284 , F04D29/30
摘要： A compressor impeller includes a hub, main blades and splitter blades. The main blades are equally spaced around the circumference of the hub. Each splitter blade is equally spaced between two adjacent main blades. Each main blade and splitter blade has suction and pressure surfaces formed in substantial compliance with normalized Cartesian coordinate values of X, Y, and Z set forth in Tables 1-4. When connected by smooth, continuing arcs, the normalized Cartesian coordinates form complete main blade and splitter blade shapes that are substantially matched by the main blade and splitter blade shapes of the compressor impeller.
摘要翻译：压缩机叶轮包括轮毂，主叶片和分流叶片。主叶片围绕轮毂的圆周等间隔开。每个分流叶片在两个相邻的主叶片之间相等间隔。每个主叶片和分流叶片具有大体上符合表1-4所示的X，Y和Z的归一化笛卡尔坐标值的吸力和压力表面。当通过光滑的连续弧连接时，归一化的笛卡尔坐标形成完全的主叶片和分流叶片形状，其基本上与压缩机叶轮的主叶片和分流叶片形状基本匹配。

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