公开(公告)号：US20050161527A1

公开(公告)日：2005-07-28

申请号：US10766398

申请日：2004-01-28

申请人： Michael Murphy ,  Curtis Cowan ,  Stephen Paul ,  James Allore ,  Meggan Harris

发明人： Michael Murphy ,  Curtis Cowan ,  Stephen Paul ,  James Allore ,  Meggan Harris

IPC分类号： B05B1/24 ,  B05B7/16 ,  B05C1/00 ,  F02K1/12 ,  F02K1/82

CPC分类号： F02K1/1223 ,  F02K1/822 ,  Y02T50/675

摘要： A nozzle system includes a multiple of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of a gas path. Each divergent flap includes a multiple of cooling channels with respective intakes and outlets. As the nozzle transitions between positions, the divergent flap seals move relative a divergent flap longitudinal axis to modulate the cooling airflow which enters the separate intakes.

摘要翻译： 喷嘴系统包括多个周向分布的会聚翼片，发散翼片和翼片间密封件，其围绕发动机中心线并限定气体路径的径向外部边界。 每个发散片包括多个具有各自的入口和出口的冷却通道。 当喷嘴在位置之间转换时，发散翼片密封件相对于发散的翼片纵向轴线移动，以调节进入分开的进气口的冷却气流。

公开(公告)号：US20060266016A1

公开(公告)日：2006-11-30

申请号：US11140667

申请日：2005-05-27

申请人： Curtis Cowan ,  Stephen Paul ,  Meggan Harris ,  Paul Attridge

发明人： Curtis Cowan ,  Stephen Paul ,  Meggan Harris ,  Paul Attridge

IPC分类号： F02K11/00

CPC分类号： F02K1/1223 ,  F02K1/805 ,  F02K1/822 ,  F05D2260/202 ,  F05D2260/205 ,  Y02T50/675

摘要： An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining cooling air inlet holes at an upstream portion, cooling air exit holes at a downstream portion, and cooling air channels disposed within the divergent flap and seal, and communicating at a first end with the inlet holes and at a second end with the exit holes for conducting cooling air therethrough. Some of the exit holes of the divergent flap are disposed along lateral edge regions thereof. The divergent seals are interposed between adjacent divergent flaps, and each include lateral edge regions extending laterally beyond the exit holes. The lateral edge regions of each divergent seal have an outer surface overlying at least a portion of the exit holes of an adjacent divergent flap.

摘要翻译： 用于燃气涡轮发动机的轴对称喷嘴具有围绕其中心纵向轴线设置的发散的翼片和密封件。 发散翼片和密封件各自具有内表面，其限定在上游部分处的冷却空气入口孔，在下游部分处冷却空气出口孔，以及设置在发散片和密封件内的冷却空气通道，并且在第一端与入口 并且在第二端具有用于传导冷却空气的出口孔。 发散翼片的一些出口孔沿其侧边缘区域设置。 发散的密封件插入在相邻的发散片之间，并且每个都包括侧向延伸超出出口的侧边缘区域。 每个发散密封件的横向边缘区域具有覆盖相邻发散片的至少一部分出口孔的外表面。

公开(公告)号：US20130297497A1

公开(公告)日：2013-11-07

申请号：US13936847

申请日：2013-07-08

申请人： William Curtis Cowan, JR.

发明人： William Curtis Cowan, JR.

IPC分类号： G06Q20/30 ,  G06Q20/24

CPC分类号： G06Q20/30 ,  G06Q20/20 ,  G06Q20/24 ,  G06Q30/06 ,  G06Q99/00

摘要： Embodiments of the invention provide systems and methods for allowing merchants to perform remote credit card transactions by facilitating non-CNP transactions via a package delivery service. A non-CNP transaction includes a credit card transaction where the card is physically presented to the merchant and a receipt may be signed. Various embodiments may also include transactions in which an imprint of the card is taken.

公开(公告)号：US20130036045A1

公开(公告)日：2013-02-07

申请号：US13628864

申请日：2012-09-27

申请人： William Curtis Cowan, JR.

发明人： William Curtis Cowan, JR.

IPC分类号： G06Q20/30

CPC分类号： G06Q20/30 ,  G06Q20/20 ,  G06Q20/24 ,  G06Q30/06 ,  G06Q99/00

摘要： Embodiments of the invention provide systems and methods for allowing merchants to perform remote credit card transactions by facilitating non-CNP transactions via a package delivery service. A non-CNP transaction includes a credit card transaction where the card is physically presented to the merchant and a receipt may be signed. Various embodiments may also include transactions in which an imprint of the card is taken.

摘要翻译： 本发明的实施例提供了允许商家通过经由包裹递送服务促进非CNP交易来执行远程信用卡交易的系统和方法。 非CNP交易包括信用卡交易，其中卡被物理呈现给商家并且可以签收收据。 各种实施例还可以包括其中记录卡的印记的交易。

公开(公告)号：US20070062199A1

公开(公告)日：2007-03-22

申请号：US11232508

申请日：2005-09-22

申请人： Curtis Cowan ,  Debora Kehret

发明人： Curtis Cowan ,  Debora Kehret

IPC分类号： B63H11/10

CPC分类号： F02K1/1223 ,  F02K1/1292 ,  F02K1/38 ,  Y02T50/671

摘要： A turbine engine nozzle assembly has an upstream flap assembly having a main flap and a liner, a cooling passageway formed between the main flap and liner. A downstream flap is pivotally coupled to the upstream flap assembly for relative rotation about a hinge axis. The liner has a trailing end spaced upstream from a trailing end of the main flap by at least 40% of a length of the main flap.

摘要翻译： 涡轮发动机喷嘴组件具有具有主瓣和衬垫的上游翼片组件，形成在主翼片和衬垫之间的冷却通道。 下游翼片枢转地联接到上游翼片组件，以围绕铰链轴线相对旋转。 衬里具有与主瓣的后端上游相距主瓣的至少40％的后端。

公开(公告)号：US20060283192A1

公开(公告)日：2006-12-21

申请号：US11184264

申请日：2005-07-18

申请人： Curtis Cowan

发明人： Curtis Cowan

IPC分类号： F02C7/22

CPC分类号： F23D17/002 ,  F23C2700/026 ,  F23N2037/02 ,  F23R3/286 ,  F23R3/30 ,  F23R3/36

摘要： A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.

摘要翻译： 燃气涡轮发动机被引导，其中以作为液体输送到燃烧器的燃料的先导流。 燃料的第一附加流动也作为液体输送到燃烧器。 燃料的第二附加流动被蒸发并作为蒸汽输送到燃烧器。 燃料喷射器可以具有与三个流中的每一个相关联的通路。

公开(公告)号：US20060112676A1

公开(公告)日：2006-06-01

申请号：US11000829

申请日：2004-12-01

申请人： Curtis Cowan ,  Jorge Farah ,  Debora Kehret ,  Stanley Keysa ,  Jeffrey Lavin ,  Michael Murphy ,  Stephen Paul ,  Richard Scott

发明人： Curtis Cowan ,  Jorge Farah ,  Debora Kehret ,  Stanley Keysa ,  Jeffrey Lavin ,  Michael Murphy ,  Stephen Paul ,  Richard Scott

IPC分类号： F02K1/00

CPC分类号： F02K1/827 ,  F02K1/004 ,  F02K1/82 ,  F02K1/822 ,  Y02T50/675

摘要： A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.

公开(公告)号：US20100063945A1

公开(公告)日：2010-03-11

申请号：US12617371

申请日：2009-11-12

申请人： William Curtis Cowan, JR.

发明人： William Curtis Cowan, JR.

IPC分类号： G06Q90/00

CPC分类号： G06Q20/30 ,  G06Q20/20 ,  G06Q20/24 ,  G06Q30/06 ,  G06Q99/00

摘要： Embodiments of the invention provide systems and methods for allowing merchants to perform remote credit card transactions by facilitating non-CNP transactions via a package delivery service. A non-CNP transaction includes a credit card transaction where the card is physically presented to the merchant and a receipt may be signed. Various embodiments may also include transactions in which an imprint of the card is taken.

摘要翻译： 本发明的实施例提供了允许商家通过经由包裹递送服务促进非CNP交易来执行远程信用卡交易的系统和方法。 非CNP交易包括信用卡交易，其中卡被物理呈现给商家并且可以签收收据。 各种实施例还可以包括其中记录卡的印记的交易。

公开(公告)号：US20050086944A1

公开(公告)日：2005-04-28

申请号：US10691791

申请日：2003-10-23

申请人： Curtis Cowan

发明人： Curtis Cowan

IPC分类号： F02C7/22 ,  F02C7/224 ,  F23D11/10 ,  F23D17/00 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34 ,  F23R3/36

CPC分类号： F23D17/002 ,  F23C2700/026 ,  F23N2037/02 ,  F23R3/286 ,  F23R3/30 ,  F23R3/36

摘要： A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.