专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07255536B2 Turbine airfoil platform cooling circuit 有权
标题翻译：涡轮机翼平台冷却回路
公开(公告)号：US07255536B2
公开(公告)日：2007-08-14
申请号：US11134927
申请日：2005-05-23
申请人： Frank J. Cunha , Eric Couch , Keith A. Santeler , Scott W. Gayman , Eric A. Hudson , Christopher Joe , Eric Letizia
发明人： Frank J. Cunha , Eric Couch , Keith A. Santeler , Scott W. Gayman , Eric A. Hudson , Christopher Joe , Eric Letizia
IPC分类号： F01D5/18
CPC分类号： F01D9/02 , F01D5/187 , F01D25/12 , F05D2240/81 , Y02T50/676
摘要： An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.
摘要翻译：机翼组件包括远离平台延伸的翼型件。通过平台形成一个或多个冷却回路以提供平台的冷却。冷却回路可以包括从平台下方接收冷却空气的向下定向的入口。然后将冷却空气沿大致平行于平台的外表面的方向引导并通过平台的外表面形成的出口。冷却回路可以可选地包括从冷却回路的外壁延伸到内壁的多个基座，以增加冷却回路的刚度和冷却功能。

2. 发明授权

US07097425B2 Microcircuit cooling for a turbine airfoil 有权
标题翻译：用于涡轮机翼的微电路冷却
公开(公告)号：US07097425B2
公开(公告)日：2006-08-29
申请号：US10802260
申请日：2004-03-16
申请人： Frank J. Cunha , Keith Santeler , Scott W. Gayman , Eric Couch
发明人： Frank J. Cunha , Keith Santeler , Scott W. Gayman , Eric Couch
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2250/25 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A turbine airfoil includes a plurality of cooling circuits embedded within the pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.
摘要翻译：涡轮机翼片包括嵌入压力和抽吸侧壁内的多个冷却回路以及第一和第二流动通道。第一流动通道将冷却剂流体供给到仅在压力侧壁内嵌入的冷却回路，而第二流动通道将冷却剂流体供给到仅嵌入在吸力侧壁内的冷却回路。本发明的方法实施例包括将嵌入在第一侧壁内的冷却回路的入口放置成仅与流动通道中的一个流体连通，并且将嵌入在第二侧壁内的冷却回路的入口与至少一个其他流动通道以最小化吸入和压力侧壁的吸收压力的差异，以确保将冷却剂流体摄入相应冷却回路的入口。

3. 发明授权

US06896487B2 Microcircuit airfoil mainbody 有权
标题翻译：微电脑机翼主体
公开(公告)号：US06896487B2
公开(公告)日：2005-05-24
申请号：US10637352
申请日：2003-08-08
申请人： Frank J. Cunha , Keith A. Santeler
发明人： Frank J. Cunha , Keith A. Santeler
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A cooling circuit disposed within a first wall portion and a second wall portion of a wall for use in a gas turbine engine is provided. The cooling circuit includes a plurality of inlet apertures disposed in the first wall portion to provide a flow path of cooling air into the cooling circuit, a first exit slot disposed in the second wall portion to provide a cooling air flow path out of the cooling circuit, a plurality of pedestals arranged in rows extending between the first wall portion and the second wall portion and a first elongated pedestal disposed radially and extending between the first and second wall portions. The first elongated pedestal is positioned between the pedestals and the first exit slot.
摘要翻译：提供了一种设置在用于燃气涡轮发动机的壁的第一壁部分和第二壁部分内的冷却回路。冷却回路包括设置在第一壁部分中的多个入口孔，以提供冷却空气进入冷却回路的流动路径，第一出口狭槽设置在第二壁部分中，以将冷却空气流动路径提供出冷却回路在所述第一壁部分和所述第二壁部分之间延伸设置的行的多个基座和径向设置并在所述第一和第二壁部分之间延伸的第一细长台座。第一细长基座位于基座和第一出口槽之间。

4. 发明授权

US07708528B2 Platform mate face contours for turbine airfoils 有权
标题翻译：涡轮翼型平台配合面轮廓
公开(公告)号：US07708528B2
公开(公告)日：2010-05-04
申请号：US11220291
申请日：2005-09-06
申请人： Eric Couch , Frank J. Cunha
发明人： Eric Couch , Frank J. Cunha
IPC分类号： F01D5/30
CPC分类号： F01D5/22 , F01D25/12 , F05D2240/81 , F05D2250/70 , F05D2250/71 , F05D2260/20 , F05D2260/202 , F05D2260/221
摘要： Gas turbine engine components having an airfoil extending outwardly of a platform are mounted in adjacent relationship, and such that cooling air flows outwardly of a gap between mating faces of the platforms. The location of localized hot spots is identified on the platform, and the mating faces are designed to provide cooling air through the gap to address these hot spots. A suction side edge of the platform has a curved portion extending inwardly into the platform, and the pressure side has a curved portion bulging outwardly away from the airfoil. When these two portions on adjacent components mate, a gap is provided between two platforms that provides leakage cooling air to the hot spot.
摘要翻译：具有从平台向外延伸的翼型件的燃气涡轮发动机部件以相邻的关系安装，并且使得冷却空气从平台的配合面之间的间隙向外流动。在平台上识别局部热点的位置，并且配合面设计成通过间隙提供冷却空气以解决这些热点。平台的吸入侧边缘具有向内延伸到平台中的弯曲部分，并且压力侧具有从翼型向外凸出的弯曲部分。当相邻部件上的这两个部分配合时，在两个平台之间提供间隙，这两个平台向热点提供泄漏的冷却空气。

5. 发明申请

US20090304516A1 PLATFORM MATE FACE CONTOURS FOR TURBINE AIRFOILS 有权
标题翻译：平台风力发动机风力发电机表面
公开(公告)号：US20090304516A1
公开(公告)日：2009-12-10
申请号：US11220291
申请日：2005-09-06
申请人： Eric Couch , Frank J. Cunha
发明人： Eric Couch , Frank J. Cunha
IPC分类号： F01D5/14
CPC分类号： F01D5/22 , F01D25/12 , F05D2240/81 , F05D2250/70 , F05D2250/71 , F05D2260/20 , F05D2260/202 , F05D2260/221
摘要： Gas turbine engine components having an airfoil extending outwardly of a platform are mounted in adjacent relationship, and such that cooling air flows outwardly of a gap between mating faces of the platforms. The location of localized hot spots is identified on the platform, and the mating faces are designed to provide cooling air through the gap to address these hot spots. A suction side edge of the platform has a curved portion extending inwardly into the platform, and the pressure side has a curved portion bulging outwardly away from the airfoil. When these two portions on adjacent components mate, a gap is provided between two platforms that provides leakage cooling air to the hot spot.
摘要翻译：具有从平台向外延伸的翼型件的燃气涡轮发动机部件以相邻的关系安装，并且使得冷却空气从平台的配合面之间的间隙向外流动。在平台上识别局部热点的位置，并且配合面设计成通过间隙提供冷却空气以解决这些热点。平台的吸入侧边缘具有向内延伸到平台中的弯曲部分，并且压力侧具有从翼型向外凸出的弯曲部分。当相邻部件上的这两个部分配合时，在两个平台之间提供间隙，这两个平台向热点提供泄漏的冷却空气。

6. 发明授权

US09404654B2 Gas turbine engine combustor with integrated combustor vane 有权
标题翻译：具有集成燃烧器叶片的燃气轮机发动机燃烧器
公开(公告)号：US09404654B2
公开(公告)日：2016-08-02
申请号：US13627697
申请日：2012-09-26
申请人： Frank J. Cunha , Nurhak Erbas-Sen
发明人： Frank J. Cunha , Nurhak Erbas-Sen
IPC分类号： F23R3/16 , F23R3/06 , F23R3/26
CPC分类号： F23R3/16 , F23R3/06 , F23R3/26 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , F23R2900/03045 , Y02T50/675
摘要： A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.
摘要翻译：用于燃气涡轮发动机的燃烧器部分包括至少部分地延伸到燃烧室中的燃烧器叶片。

7. 发明申请

US20140338336A1 GAS TURBINE ENGINE COMBUSTOR WITH INTEGRATED COMBUSTOR VANE 有权
公开(公告)号：US20140338336A1
公开(公告)日：2014-11-20
申请号：US13627722
申请日：2012-09-26
申请人： Frank J. Cunha , Nurhak Erbas-Sen
发明人： Frank J. Cunha , Nurhak Erbas-Sen
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F01D9/023 , F01D9/065 , F05D2260/202 , F23R3/04 , F23R3/16 , F23R3/26 , F23R2900/00018 , F23R2900/03044 , Y02T50/676
摘要： A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.

8. 发明申请

US20130327049A1 COMBUSTOR LINER WITH REDUCED COOLING DILUTION OPENINGS 有权
标题翻译：具有减少冷却水平开口的COMBUSTOR衬里
公开(公告)号：US20130327049A1
公开(公告)日：2013-12-12
申请号：US13490809
申请日：2012-06-07
申请人： Frank J. Cunha , Nurhak Erbas-Sen
发明人： Frank J. Cunha , Nurhak Erbas-Sen
IPC分类号： F23R3/06
CPC分类号： F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
摘要： A combustor liner is arcuate in shape and defines an axis and a circumferential direction. The combustor liner includes a first row of dilution openings and a second row of dilution openings. The first row runs in the circumferential direction. The second row runs parallel to the first row and is axially spaced from the first row. Each dilution opening of the second row overlaps in an axial direction a portion of each of two adjacent dilution openings of the first row.
摘要翻译：燃烧器衬套的形状为弧形，并且限定了轴线和圆周方向。燃烧器衬套包括第一排稀释开口和第二排稀释开口。第一列沿圆周方向延伸。第二排平行于第一排延伸并且与第一排轴向间隔开。第二排的每个稀释开口在轴向上与第一排的两个相邻的稀释开口中的每一个的一部分重叠。

9. 发明授权

US07220103B2 Impingement cooling of large fillet of an airfoil 有权
标题翻译：机翼大圆角的冲击冷却
公开(公告)号：US07220103B2
公开(公告)日：2007-05-22
申请号：US10967557
申请日：2004-10-18
申请人： Frank J. Cunha , Jason E. Albert , Edward F. Pietraszkiewicz
发明人： Frank J. Cunha , Jason E. Albert , Edward F. Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/145 , F01D5/081 , F01D5/143 , F01D5/187 , F05D2240/80 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which, together with an impingement rib, defines a fillet cavity therebetween, and cooling air is provided to flow through impingement holes in the impingement rib and impinge on the rear surface of the fillet. The impingement holes are elongated in cross sectional shape with their elongations being orient in a direction generally transverse to a radial direction.
摘要翻译：燃气涡轮发动机叶片具有较大的圆角以改善其上的空气流的特性。圆角具有薄壁，其与冲击肋一起在其间限定圆角腔，并且提供冷却空气以流过冲击肋中的冲击孔并撞击圆角的后表面。冲击孔的横截面形状是细长的，它们的伸长方向在大致横向于径向的方向上定向。

10. 发明授权

US09335050B2 Gas turbine engine combustor 有权
标题翻译：燃气轮机发动机燃烧器
公开(公告)号：US09335050B2
公开(公告)日：2016-05-10
申请号：US13627688
申请日：2012-09-26
申请人： Frank J. Cunha , Nurhak Erbas-Sen
发明人： Frank J. Cunha , Nurhak Erbas-Sen
IPC分类号： F02C7/22 , F23R3/28 , F23R3/14 , F23R3/34
CPC分类号： F23R3/14 , F23R3/16 , F23R3/286
摘要： A swirler assembly for a gas turbine engine includes an outer annular injector which at least partially surrounds an inner injector. In sonic embodiments, a combustor section for a gas turbine engine comprises an inner injector which defines an axis, an outer annular injector which surrounds said inner injector, and a combustor vane along said axis.
摘要翻译：用于燃气涡轮发动机的旋流器组件包括至少部分地围绕内部喷射器的外部环形喷射器。在声音实施例中，用于燃气涡轮发动机的燃烧器部分包括限定轴线的内部喷射器，围绕所述内部喷射器的外部环形喷射器和沿所述轴线的燃烧器叶片。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式