公开(公告)号：US20080138209A1

公开(公告)日：2008-06-12

申请号：US11636801

申请日：2006-12-11

申请人： Francisco J. Cunha ,  Scott W. Gayman

发明人： Francisco J. Cunha ,  Scott W. Gayman

IPC分类号： F01D5/18

CPC分类号： B22C9/103 ,  B22C9/04 ,  F01D5/186 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/202 ,  Y02T50/676

摘要： A turbine engine component, such as a turbine blade, has an airfoil portion having a pressure side wall and a suction side wall, a first cooling circuit embedded within the pressure side wall, which first cooling circuit has at least two passageways embedded within the pressure side wall, a second cooling circuit embedded within the suction side wall, which second cooling circuit has at least two passageways embedded within the suction side wall, at least one cooling fluid supply cavity located between the pressure and suction side walls, each cooling fluid supply cavity having at least one projecting portion extending between adjacent ones of the embedded passageways in the first cooling circuit or adjacent ones of the embedded passageways in the second cooling circuit, and each projecting portion communicating with at least one film cooling hole. A method for forming the turbine blade component is also described.

摘要翻译： 诸如涡轮叶片的涡轮发动机部件具有翼型部分，其具有压力侧壁和吸力侧壁，嵌入在压力侧壁内的第一冷却回路，该第一冷却回路具有嵌入在压力内的至少两个通道 侧壁，嵌入在吸入侧壁内的第二冷却回路，该第二冷却回路具有嵌入吸入侧壁内的至少两个通道，位于压力侧和吸力侧壁之间的至少一个冷却流体供应腔，每个冷却流体供应 空腔具有在第一冷却回路中相邻的嵌入通道之间延伸的至少一个突出部分或第二冷却回路中相邻的嵌入通道中的一个突出部分，并且每个突出部分与至少一个膜冷却孔连通。 还描述了用于形成涡轮叶片部件的方法。

公开(公告)号：US20080019841A1

公开(公告)日：2008-01-24

申请号：US11491405

申请日：2006-07-21

申请人： Francisco J. Cunha

发明人： Francisco J. Cunha

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/188

摘要： A turbine engine component has an airfoil portion with a pressure side and a suction side. The turbine engine component further has a first cooling microcircuit for cooling the suction side of the airfoil portion. The first cooling microcircuit is embedded within a first wall forming the suction side. The first cooling microcircuit has a circuit for allowing a cooling fluid in the first cooling microcircuit to exit at a tip of the airfoil portion. The turbine engine component also has a second cooling microcircuit embedded within a second wall forming the pressure side of the airfoil portion.

摘要翻译： 涡轮发动机部件具有压力侧和吸力侧的翼型部。 涡轮发动机部件还具有用于冷却翼型部分的吸入侧的第一冷却微型电路。 第一冷却微电路嵌入形成吸入侧的第一壁内。 第一冷却微电路具有允许第一冷却微电路中的冷却流体在翼型部分的尖端处离开的电路。 涡轮发动机部件还具有嵌入到形成翼型部分的压力侧的第二壁内的第二冷却微电路。

公开(公告)号：US20080008599A1

公开(公告)日：2008-01-10

申请号：US11484143

申请日：2006-07-10

申请人： Francisco J. Cunha ,  William Abdel-Messeh

发明人： Francisco J. Cunha ,  William Abdel-Messeh

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2230/21 ,  F05D2250/185 ,  Y02T50/676

摘要： A turbine engine component, such as a turbine blade, has an airfoil portion having a tip and a root portion and a cooling microcircuit arrangement within the airfoil portion. The cooling microcircuit arrangement comprises a multi-leg main body portion for allowing a flow of coolant to convectively cool the airfoil portion and at least one integrally formed tip cooling microcircuit for cooling the tip.

摘要翻译： 诸如涡轮叶片的涡轮发动机部件具有在翼型部分内具有尖端和根部部分以及冷却微电路装置的翼型部分。 冷却微电路装置包括多腿主体部分，用于允许冷却剂的流动对流地冷却翼型部分和至少一个整体形成的尖端冷却微电路以冷却尖端。

公开(公告)号：US5634766A

公开(公告)日：1997-06-03

申请号：US414697

申请日：1995-03-31

申请人： Francisco J. Cunha ,  David A. DeAngelis ,  Theresa A. Brown ,  Sanjay Chopra ,  Victor H. S. Correia ,  Daniel R. Predmore

发明人： Francisco J. Cunha ,  David A. DeAngelis ,  Theresa A. Brown ,  Sanjay Chopra ,  Victor H. S. Correia ,  Daniel R. Predmore

IPC分类号： F01D9/02 ,  F01D5/18 ,  F01D9/04 ,  F01D11/00 ,  F02C7/16 ,  F01D9/06

CPC分类号： F01D5/189 ,  F01D11/005 ,  F01D5/187 ,  F01D5/188 ,  F05D2240/10 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/2322 ,  Y02T50/67 ,  Y02T50/676

摘要： Turbine stator vane segments have inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall passes through the impingement plate for impingement cooling of the outer wall surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. The trailing edge is air-cooled.

摘要翻译： 涡轮机定子叶片段具有内壁和外壁，叶片间延伸有叶片。 内壁和外壁分隔开并具有冲击板。 流入外壁的蒸汽通过冲击板，用于冲击冷却外壁表面。 废冲击蒸汽流入具有用于冲击冷却叶片壁的插入件的叶片的空腔中。 蒸汽进入内壁并通过冲击板，用于内壁表面的冲击冷却，并通过具有用于叶片表面的冲击冷却的插入件的返回腔返回。 后缘是风冷的。

公开(公告)号：US5611662A

公开(公告)日：1997-03-18

申请号：US509918

申请日：1995-08-01

申请人： Francisco J. Cunha

发明人： Francisco J. Cunha

IPC分类号： F01D5/18 ,  F01D9/02 ,  F04D29/38

CPC分类号： F01D5/187 ,  F01D9/02 ,  F05D2260/201 ,  F05D2260/22141

摘要： A cooling air circuit for the trailing edge cavity of a nozzle segment for a gas turbine includes a plurality of cooling sections radially spaced one from the other along the vane. Air flows radially inwardly and is turned by guide vanes for axial flow for impingement cooling of the trailing edge. The flow is such that vortices are formed and heat is carried away from the trailing edge by cooling flow directed forwardly from the trailing edge through another series of guide vanes. The rearward and forward sequential flows are provided in repeated patterns at radially spaced positions along the trailing edge until finally the cooling air flows through a trailing edge cavity outlet into a diaphragm. The diaphragm has channels for directing the cooling flow from the diaphragm at an angle into the wheelspace for cooling the seal cavity.

摘要翻译： 用于燃气涡轮机的喷嘴段的后缘空腔的冷却空气回路包括沿着叶片径向间隔开的多个冷却部分。 空气径向向内流动，并被导向叶片转动，用于轴向流动，用于后缘的冲击冷却。 流动使得形成涡流，并且通过从后缘向前指向另一系列导向叶片的冷却流将后退边缘的热量带走。 向后和向前的顺序流以沿着后缘的径向间隔的位置以重复的图案提供，直到最终冷却空气流过后缘空腔出口为隔膜。 隔膜具有用于将来自隔膜的冷却流以一定角度引导到车轮空间中以用于冷却密封腔的通道。

公开(公告)号：US5591002A

公开(公告)日：1997-01-07

申请号：US509917

申请日：1995-08-01

申请人： Francisco J. Cunha ,  Alan Walker

发明人： Francisco J. Cunha ,  Alan Walker

IPC分类号： F01D5/18 ,  F01D11/00 ,  F01D9/06

CPC分类号： F01D5/187 ,  F01D11/005 ,  F01D5/188 ,  F01D5/189 ,  F05D2240/10 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/2322

摘要： The nozzle segment includes a vane having a plurality of axially spaced cavities for transmission of a cooling medium. In a closed circuit cooling system, air is transmitted radially inwardly and outwardly through inserts in leading and intermediate cavities, respectively, for flow through holes for impingement cooling of the adjoining vane surfaces. Radial inlet flow of cooling medium to an aft cavity likewise flows through an insert for impingement cooling of the aft cavity walls. The cooling medium flows from the aft cavity into a trailing edge cavity for impingement cooling of the trailing edge. The spent cooling flow passes through a channel in the diaphragm into the wheelspace. In the open air circuit, the spent impingement flow in the leading and intermediate cavities passes through openings in the vane wall for thin film cooling of the vane. An insert is received in the trailing edge cavity for impingement cooling of the trailing edge walls and flow towards the trailing edge on opposite sides of a tongue for turbulent flow through a multiplicity of openings through the trailing edge into the hot gas stream.

摘要翻译： 喷嘴段包括具有多个轴向隔开的空腔的叶片，用于传输冷却介质。 在闭路冷却系统中，空气分别径向向内和向外地传送通过前导和中间空腔中的插入件，用于流过通孔，用于相邻叶片表面的冲击冷却。 冷却介质向后空腔的径向入口流动同样流过插入件，用于对后腔壁进行冲击冷却。 冷却介质从尾腔流入后缘腔，用于后缘的冲击冷却。 废冷却流通过隔膜中的通道进入车轮空间。 在露天回路中，先导和中间空腔中的消耗冲击流通过叶片壁中的开口，用于叶片的薄膜冷却。 插入件被容纳在后缘空腔中，用于后缘壁的冲击冷却并且朝向舌片的相对侧上的后缘流动，用于湍流通过后缘进入热气流的多个开口。