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1. 发明申请

US20130001319A1 IMPINGEMENT COOLED NOZZLE LINER 有权
标题翻译： IMPINGEMENT冷却喷嘴线
公开(公告)号：US20130001319A1
公开(公告)日：2013-01-03
申请号：US13173903
申请日：2011-06-30
申请人： Curtis C. Cowan , Jorge I. Farah
发明人： Curtis C. Cowan , Jorge I. Farah
IPC分类号： B64D33/04
CPC分类号： F01D11/005 , F01D5/18 , F02C7/28 , F02K1/006 , F02K1/12 , F02K1/1223 , F02K1/822 , F16J15/025 , F16J15/027 , F16J15/0893 , Y02T50/675
摘要： A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.
摘要翻译：用于可旋转喷嘴的喷嘴衬套包括密封台面和用于与喷嘴一起移动的可旋转密封件。如果可旋转密封件处于第一位置，密封件具有用于分配冷却空气的第一扩散孔和用于在可旋转密封件处于第一位置并且如果处于第二位置时分配冷却空气的第二扩散孔。

2. 发明授权

US09932845B2 Impingement cooled nozzle liner 有权
公开(公告)号：US09932845B2
公开(公告)日：2018-04-03
申请号：US13173903
申请日：2011-06-30
申请人： Curtis C. Cowan , Jorge I. Farah
发明人： Curtis C. Cowan , Jorge I. Farah
IPC分类号： F02K1/82 , F01D11/00 , F02K1/12 , F02C7/28 , F16J15/08 , F02K1/00 , F16J15/02 , F01D5/18
CPC分类号： F01D11/005 , F01D5/18 , F02C7/28 , F02K1/006 , F02K1/12 , F02K1/1223 , F02K1/822 , F16J15/025 , F16J15/027 , F16J15/0893 , Y02T50/675
摘要： A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.

3. 发明申请

US20090072490A1 Convergent Divergent Nozzle with Edge Cooled Divergent Seals 有权
标题翻译：具有边缘冷却发散密封的会聚发散喷嘴
公开(公告)号：US20090072490A1
公开(公告)日：2009-03-19
申请号：US11671591
申请日：2007-02-06
申请人： Curtis C. Cowan , James P. Allore , Paul Attridge
发明人： Curtis C. Cowan , James P. Allore , Paul Attridge
IPC分类号： F16J15/32
CPC分类号： F02K1/1223 , F02K1/805 , F02K1/822 , Y02T50/672 , Y02T50/675 , Y10S277/93
摘要： A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes a multiple of divergent seal intakes adjacent to a joint structure to receive cooling airflow. Each divergent seal body is manufactured of a metallic hot sheet inner skin and a metallic cold sheet outer skin. The skins form a multiple of longitudinal channels which communicate with a multiple of edge channels formed within the first longitudinal side and the second longitudinal side of each divergent seal. The multiple of edge channels are located transverse to the longitudinal axis and are raked aft to facilitate cooling of the gas path surface of each divergent seal and adjacent divergent flaps.
摘要翻译：喷嘴系统包括围绕发动机中心线的多个周向分布的发散密封件。每个发散密封件包括与接头结构相邻的发散密封进口的多个以接收冷却气流。每个发散密封体由金属热板内皮和金属冷板外皮制成。表皮形成多个纵向通道，其与形成在每个发散密封件的第一纵向侧面和第二纵向侧面中的多个边缘通道连通。多个边缘通道横向于纵向轴线定位，并且被后倾，以便于冷却每个发散密封件和相邻发散板的气体路径表面。

4. 发明申请

US20090065610A1 Rollertrack pivoting axi-nozzle 有权
标题翻译：卷轴旋转轴喷嘴
公开(公告)号：US20090065610A1
公开(公告)日：2009-03-12
申请号：US11894314
申请日：2007-08-21
申请人： Curtis C. Cowan , Robert H. Bush
发明人： Curtis C. Cowan , Robert H. Bush
IPC分类号： B64C9/38
CPC分类号： F02K1/1223
摘要： A mechanism included in a convergent-divergent nozzle connected to an aftward portion of a gas turbine engine, which mechanism includes at least one actuator configured to be connected to the aftward portion of the engine and to move through one or more positions, a first link pivotally connected to the at least one actuator, a convergent flap pivotally connected to the first link, a divergent flap rotatably connected to the convergent flap and configured to be kinematically connected to an annular ring connected to the at least one actuator, and at least one track configured to extend from the aftward portion of the engine and to movably and pivotally receive the pivotal connection between the convergent flap and the first link.
摘要翻译：包括在连接到燃气涡轮发动机的后部的收敛扩散喷嘴中的机构，该机构包括至少一个致动器，其构造成连接到发动机的后部并且移动通过一个或多个位置，第一连杆枢转地连接到所述至少一个致动器，枢转地连接到所述第一连杆的会聚舌片，可旋转地连接到所述会聚舌片并被构造成运动学地连接到连接到所述至少一个致动器的环形环的发散片，以及至少一个轨道构造成从发动机的后部延伸并且可移动地和枢转地接收收敛翼片和第一连杆之间的枢转连接。

5. 发明授权

US08205454B2 Convergent divergent nozzle with edge cooled divergent seals 有权
标题翻译：具有边缘冷却发散密封的收敛发散喷嘴
公开(公告)号：US08205454B2
公开(公告)日：2012-06-26
申请号：US11671591
申请日：2007-02-06
申请人： Curtis C. Cowan , James P. Allore , Paul Attridge
发明人： Curtis C. Cowan , James P. Allore , Paul Attridge
IPC分类号： F02K1/00 , B05B12/00
CPC分类号： F02K1/1223 , F02K1/805 , F02K1/822 , Y02T50/672 , Y02T50/675 , Y10S277/93
摘要： A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes a multiple of divergent seal intakes adjacent to a joint structure to receive cooling airflow. Each divergent seal body is manufactured of a metallic hot sheet inner skin and a metallic cold sheet outer skin. The skins form a multiple of longitudinal channels which communicate with a multiple of edge channels formed within the first longitudinal side and the second longitudinal side of each divergent seal. The multiple of edge channels are located transverse to the longitudinal axis and are raked aft to facilitate cooling of the gas path surface of each divergent seal and adjacent divergent flaps.
摘要翻译：喷嘴系统包括围绕发动机中心线的多个周向分布的发散密封件。每个发散密封件包括与接头结构相邻的发散密封进口的多个以接收冷却气流。每个发散密封体由金属热板内皮和金属冷板外皮制成。表皮形成多个纵向通道，其与形成在每个发散密封件的第一纵向侧面和第二纵向侧面中的多个边缘通道连通。多个边缘通道横向于纵向轴线定位，并且被后倾，以便于冷却每个发散密封件和相邻发散板的气体路径表面。

6. 发明授权

US08186164B2 Turbine engine fuel injector 有权
标题翻译：涡轮发动机燃油喷射器
公开(公告)号：US08186164B2
公开(公告)日：2012-05-29
申请号：US13220757
申请日：2011-08-30
申请人： Curtis C. Cowan
发明人： Curtis C. Cowan
IPC分类号： 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.
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。

7. 发明授权

US07377099B2 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：US07377099B2
公开(公告)日：2008-05-27
申请号：US11140667
申请日：2005-05-27
申请人： Curtis C. Cowan , Stephen A. Paul , Meggan Harris , Paul Attridge
发明人： Curtis C. Cowan , Stephen A. 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。

8. 发明授权

US08020386B2 Rollertrack pivoting axi-nozzle 有权
标题翻译：卷轴旋转轴喷嘴
公开(公告)号：US08020386B2
公开(公告)日：2011-09-20
申请号：US11894314
申请日：2007-08-21
申请人： Curtis C. Cowan , Robert H. Bush
发明人： Curtis C. Cowan , Robert H. Bush
IPC分类号： F02K1/12
CPC分类号： F02K1/1223
摘要： A mechanism included in a convergent-divergent nozzle connected to an aftward portion of a gas turbine engine, which mechanism includes at least one actuator configured to be connected to the aftward portion of the engine and to move through one or more positions, a first link pivotally connected to the at least one actuator, a convergent flap pivotally connected to the first link, a divergent flap rotatably connected to the convergent flap and configured to be kinematically connected to an annular ring connected to the at least one actuator, and at least one track configured to extend from the aftward portion of the engine and to movably and pivotally receive the pivotal connection between the convergent flap and the first link.
摘要翻译：包括在连接到燃气涡轮发动机的后部的收敛扩散喷嘴中的机构，该机构包括至少一个致动器，其构造成连接到发动机的后部并且移动通过一个或多个位置，第一连杆枢转地连接到所述至少一个致动器，枢转地连接到所述第一连杆的会聚舌片，可旋转地连接到所述会聚舌片并被构造成运动学地连接到连接到所述至少一个致动器的环形环的发散片，以及至少一个轨道构造成从发动机的后部延伸并且可移动地和枢转地接收收敛翼片和第一连杆之间的枢转连接。

9. 发明授权

US07032835B2 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：US07032835B2
公开(公告)日：2006-04-25
申请号：US10766398
申请日：2004-01-28
申请人： Michael J. Murphy , Curtis C. Cowan , Stephen A. Paul , James P. Allore , Meggan Harris
发明人： Michael J. Murphy , Curtis C. Cowan , Stephen A. Paul , James P. Allore , Meggan Harris
IPC分类号： B05B7/16 , B05B12/00 , B05B1/24 , B63H11/10
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。

10. 发明授权

US06935117B2 Turbine engine fuel injector 有权
标题翻译：涡轮发动机燃油喷射器
公开(公告)号：US06935117B2
公开(公告)日：2005-08-30
申请号：US10691791
申请日：2003-10-23
申请人： Curtis C. Cowan
发明人： Curtis C. 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.
摘要翻译：燃气涡轮发动机被引导为具有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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