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1. 发明申请

US20060266016A1 System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle 有权
标题翻译：用于冷却轴对称喷嘴的发散密封的侧边缘区域的系统和方法
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。

2. 发明申请

US20050161527A1 Convergent/divergent nozzle with modulated cooling 有权
标题翻译：具有调制冷却的收敛/扩散喷嘴
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。

3. 发明申请

US20060112676A1 Cooled duct for gas turbine engine 有权
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.

4. 发明申请

US20050086944A1 Turbine engine fuel injector 有权
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.

5. 发明申请

US20070062199A1 Turbine engine nozzle 审中-公开
标题翻译：涡轮发动机喷嘴
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。

6. 发明申请

US20060283192A1 Engine fueling method 有权
标题翻译：发动机加油方式
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。

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