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

US5829245A Cooling system for gas turbine vane 失效
标题翻译：燃气轮机叶片冷却系统
公开(公告)号：US5829245A
公开(公告)日：1998-11-03
申请号：US775434
申请日：1996-12-31
申请人： Gerard McQuiggan , Raymond Scott Nordlund , Leslie Roy Southall , William Edward North , Zachary Sinnott
发明人： Gerard McQuiggan , Raymond Scott Nordlund , Leslie Roy Southall , William Edward North , Zachary Sinnott
IPC分类号： F01D9/02 , F01D5/18 , F02C7/16 , F02C7/12
CPC分类号： F02C7/16 , F01D5/187 , F05D2240/81 , F05D2260/2322
摘要： A gas turbine that has turbine vanes that can be cooled with either steam or air includes a compressor that compresses air, a combustor enclosed within a shell and in flow communication with the compressor, a turbine in flow communication with the combustor and receiving hot gas from the combustor and turbine vanes. The turbine vanes having an airfoil, a shroud and a cooling circuit that cools the airfoil and the shrouds with either steam or air.
摘要翻译：具有可以用蒸汽或空气冷却的涡轮叶片的燃气轮机包括压缩空气的压缩机，封闭在壳体内并与压缩机流动连通的燃烧器，与燃烧器流动连通的涡轮机，并接收来自燃烧器和涡轮叶片。涡轮叶片具有翼型，护罩和冷却回路，其用蒸汽或空气冷却翼型件和护罩。

2. 发明授权

US5813827A Apparatus for cooling a gas turbine airfoil 失效
标题翻译：用于冷却燃气涡轮机翼型的装置
公开(公告)号：US5813827A
公开(公告)日：1998-09-29
申请号：US843414
申请日：1997-04-15
申请人： Raymond Scott Nordlund , Kent Goran Hultgren , Robert Kenmer Scott , Zachary Sinnott , William Edward North , Steven Douglas Ward
发明人： Raymond Scott Nordlund , Kent Goran Hultgren , Robert Kenmer Scott , Zachary Sinnott , William Edward North , Steven Douglas Ward
IPC分类号： F01D9/02 , F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2230/00
摘要： An apparatus for cooling the trailing edge portion of a gas turbine vane. Two radially extending passages connected to the outer shroud direct cooling fluid to a plenum formed about mid-span adjacent the trailing edge. Two arrays of cooling fluid passages extend from the plenum. One array extends radially outward toward the outer shroud while the other array extends radially inward toward the inner shroud. The plenum distributes the cooling fluid to the two arrays of passages so that it flows radially inward and outward to manifolds formed in the inner and outer shrouds. The manifolds direct the spent cooling fluid to a discharge passage.
摘要翻译：一种用于冷却燃气轮机叶片的后缘部分的装置。两个径向延伸的通道连接到外护罩直接冷却流体到形成在靠近后缘的中间跨度的增压室。冷却流体通道的两个阵列从气室延伸。一个阵列径向向外延伸到外护罩，而另一个阵列径向向内延伸到内护罩。通风室将冷却流体分配到两个通道阵列，使得它们径向向内和向外流动到形成在内部和外部护罩中的歧管。歧管将废冷却流体引导到排放通道。

3. 发明授权

US08015818B2 Cooled transition duct for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的冷却过渡管道
公开(公告)号：US08015818B2
公开(公告)日：2011-09-13
申请号：US11062970
申请日：2005-02-22
申请人： Jody W. Wilson , Raymond Scott Nordlund , Adam Weaver
发明人： Jody W. Wilson , Raymond Scott Nordlund , Adam Weaver
IPC分类号： F02C1/00
CPC分类号： F01D25/12 , F01D9/023 , F05D2250/312 , F05D2260/20
摘要： A transition duct (30) for a gas turbine engine (2) having improved cooling and reduced stress levels. The transition duct may be formed of two panels ((36, 38) joined together with welds (40) disposed remote from the bent corner regions (34) of the panels. Cooling channels (32) extending longitudinally in the direction of flow of the hot combustion gas carried by the duct are formed within each panel, including the corner regions. Because the entire annular width (W) of the transition duct is cooled, the gap (G) separating adjacent ducts around the inlet to the turbine (4) may be reduced when compared to prior art designs. Two-panel construction with welds remote from the corner regions is facilitated by maintaining the minimum bend radius in the corners (R2) and in the direction of flow (R4) to be greater than in prior art designs.
摘要翻译：一种用于具有改进的冷却和降低的应力水平的燃气涡轮发动机（2）的过渡管道（30）。过渡管道可以由两个面板（（36,38）形成，所述两个面板（36,38）与远离所述面板的弯曲拐角区域（34）设置的焊缝（40）连接在一起。冷却通道（32）由于过渡管道的整个环形宽度（W）被冷却，所以在每个面板内形成由管道承载的热燃烧气体，包括拐角区域，使围绕涡轮机（4）的入口周围的相邻管道的间隙（G）与现有技术的设计相比，可以减少远离拐角区域的焊接的双面板结构，通过将拐角（R2）和流动方向（R4）上的最小弯曲半径保持为大于先前的角度艺术设计。

4. 发明授权

US07178341B2 Multi-zone tubing assembly for a transition piece of a gas turbine 有权
标题翻译：用于燃气轮机过渡件的多区域管道组件
公开(公告)号：US07178341B2
公开(公告)日：2007-02-20
申请号：US10871476
申请日：2004-06-17
申请人： James Michael Zborovsky , Raymond Scott Nordlund
发明人： James Michael Zborovsky , Raymond Scott Nordlund
IPC分类号： F02C7/12
CPC分类号： F01D9/023
摘要： A replaceable section (25) of force-cooling tubing assembly (21, 22) for attachment to a transition piece (5) of a gas turbine is comprised of two ends (54, 70) fashioned for attachment by removable unions (52) to adjoining parts of a force-cooling tubing assembly. When assembled thereto to complete the assembly, the replaceable section 25 provides for fluid communication between a manifold (3) and the transition piece (5) for either the supply or return of cooling fluid. A transition piece (5) in combination with two such assemblies, one a supply assembly (21), the other a return assembly (22), comprises a field-installable transition piece assembly (10) that provides for rapid and easy installation. The features of the replaceable section (25) include a relatively inflexible bracing zone such as a bracing member (58) having a support structure such as a lateral plate (60) that extends to the transition piece (5), a formed tubing bend (64) typically forming a U-bend, and optionally a second flexible component comprised of an inline flexible coupling (56).
摘要翻译：用于连接到燃气涡轮机的过渡件（5）的力 - 冷却管道组件（21,22）的可替换部分（25）包括两个端部（54,70），其形状可通过可移动联接件（52）附接到力 - 冷却管组件的邻接部分。当组装到其上以完成组件时，可更换部分25提供用于供应或返回冷却流体的歧管（3）和过渡件（5）之间的流体连通。过渡件（5）与两个这样的组件组合，一个供应组件（21），另一个是返回组件（22），包括现场可安装的过渡件组件（10），其提供快速和容易的安装。可更换部分（25）的特征包括相对不弯曲的支撑区域，例如支撑构件（58），其具有支撑结构，例如延伸到过渡件（5）的侧板（60），形成的管弯 64），通常形成U形弯曲部，以及可选地由包括在线柔性联接件（56）的第二柔性部件构成。

5. 发明授权

US6105363A Cooling scheme for turbine hot parts 失效
标题翻译：涡轮机热部件冷却方案
公开(公告)号：US6105363A
公开(公告)日：2000-08-22
申请号：US67593
申请日：1998-04-27
申请人： Kent Goran Hultgren , Brian Charles Owen , Steven Wayne Dowman , Raymond Scott Nordlund , Ricky Lee Smith
发明人： Kent Goran Hultgren , Brian Charles Owen , Steven Wayne Dowman , Raymond Scott Nordlund , Ricky Lee Smith
IPC分类号： F01D25/12 , F02C7/12 , F02C3/00
CPC分类号： F01D25/12 , F02C7/12 , F05D2260/205 , F05D2260/2322
摘要： A closed-loop cooling scheme for cooling stationary combustion turbine components, such as vanes, ring segments and transitions, is provided. The cooling scheme comprises: (1) an annular coolant inlet chamber, situated between the cylinder and blade ring of a turbine, for housing coolant before being distributed to the turbine components; (2) an annular coolant exhaust chamber, situated between the cylinder and the blade ring and proximate the annular coolant inlet chamber, for collecting coolant exhaust from the turbine components; (3) a coolant inlet conduit for supplying the coolant to said coolant inlet chamber; (4) a coolant exhaust conduit for directing coolant from said coolant exhaust chamber; and (5) a piping arrangement for distributing the coolant to and directing coolant exhaust from the turbine components. In preferred embodiments of the invention, the cooling scheme further comprises static seals for sealing the blade ring to the cylinder and flexible joints for attaching the blade ring to the turbine components.
摘要翻译：提供了用于冷却固定燃气涡轮机部件（例如叶片，环形部分和转变）的闭环冷却方案。冷却方案包括：（1）位于涡轮机的气缸和叶片环之间的环形冷却剂入口室，用于在分配到涡轮机部件之前容纳冷却剂; （2）环形冷却剂排出室，位于气缸和叶片环之间并且靠近环形冷却剂入口室，用于从涡轮机部件收集冷却剂排出物; （3）用于将冷却剂供应到所述冷却剂入口室的冷却剂入口管道; （4）用于引导来自所述冷却剂排出室的冷却剂的冷却剂排出管道; 和（5）用于将冷却剂分配到并引导来自涡轮机部件的冷却剂排气的管道装置。在本发明的优选实施例中，冷却方案还包括用于将叶片环密封到气缸的静态密封件和用于将叶片环附接到涡轮机部件的柔性接头。

6. 发明授权

US06890148B2 Transition duct cooling system 失效
标题翻译：过渡管冷却系统
公开(公告)号：US06890148B2
公开(公告)日：2005-05-10
申请号：US10650954
申请日：2003-08-28
申请人： Raymond Scott Nordlund
发明人： Raymond Scott Nordlund
IPC分类号： F01D9/02 , F01D25/12 , F02K9/64 , F03D11/00
CPC分类号： F01D25/12 , F01D9/023 , F02K9/64
摘要： Aspects of the present invention relate to hollow elongated turbine engine components, such as transition ducts, having a cooling system. The component can have first and second ends, and can be defined by an outer peripheral wall. The cooling system extends longitudinally within the wall between the first and second ends. While configured to cool the entire component, the cooling system is particularly configured to reduce thermal gradients that can occur in regions proximate to the first and second ends of the component caused by higher loads in those regions. The cooling system can include at least one pair of cooling channels. Each channel pair includes a first channel and a second channel. The first and second channels can be arranged such that a coolant supplied to each channel can exchange heat with itself in at least the region substantially proximate to one of the ends.
摘要翻译：本发明的方面涉及具有冷却系统的中空细长涡轮发动机部件，例如过渡管道。该部件可以具有第一端和第二端，并且可以由外周壁限定。冷却系统在第一和第二端之间的壁内纵向延伸。虽然被配置为冷却整个组件，但是冷却系统被特别地配置为减少在这些区域中较高负载引起的靠近部件的第一和第二端的区域中可能发生的热梯度。冷却系统可以包括至少一对冷却通道。每个通道对包括第一通道和第二通道。第一和第二通道可以布置成使得供应到每个通道的冷却剂可以至少在基本上接近其中一个端部的区域中与其自身交换热量。

7. 发明授权

US06454526B1 Cooled turbine vane with endcaps 有权
标题翻译：冷却涡轮叶片与端盖
公开(公告)号：US06454526B1
公开(公告)日：2002-09-24
申请号：US09672592
申请日：2000-09-28
申请人： Frank J. Cunha , Anthony L. Schiavo, Jr. , Raymond Scott Nordlund , Thomas Malow , Barry L. McKinley
发明人： Frank J. Cunha , Anthony L. Schiavo, Jr. , Raymond Scott Nordlund , Thomas Malow , Barry L. McKinley
IPC分类号： F01D2508
CPC分类号： F01D5/187 , F01D5/147 , F05D2230/21 , F05D2240/81
摘要： A turbine vane assembly which includes an outer endcap having a plurality of generally straight passages and passage segments therethrough, an inner endcap having a plurality of passages and passage segments therethrough, and a vane assembly having an outer shroud, an airfoil body, and an inner shroud. The outer shroud, airfoil body and inner shroud each have a plurality of generally straight passages and passage segments therethrough as well. The outer endcap is coupled to the outer shroud so that outer endcap passages and said outer shroud passages form a fluid circuit. The inner endcap is coupled to the inner shroud so that the inner end cap passages and the inner shroud passages from a fluid circuit. Passages in the vane casting are in fluid communication with both the outer shroud passages and the inner shroud passages. Passages in the outer endcap may be coupled to a cooling system that supplies a coolant and takes away the heated exhaust.
摘要翻译：一种涡轮叶片组件，其包括具有多个大致直的通道和通过其的通道的外端盖，具有多个通道和通过其中的通道段的内端盖，以及具有外护罩，翼型件主体和内裹尸布。外护罩，翼型件和内护罩均具有多个大致直的通道和通过其的通道。外端盖联接到外护罩，使得外端盖通道和所述外护罩通道形成流体回路。内端盖联接到内护罩，使得内端盖通道和内护罩通道从流体回路连接。叶片铸件中的通道与外护罩通道和内护罩通道两者流体连通。外端盖中的通道可以联接到供应冷却剂并且带走加热的排气的冷却系统。

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