公开(公告)号：US06499949B2

公开(公告)日：2002-12-31

申请号：US09818385

申请日：2001-03-27

申请人： Robert Edward Schafrik ,  Ramgopal Darolia ,  Ching-Pang Lee

发明人： Robert Edward Schafrik ,  Ramgopal Darolia ,  Ching-Pang Lee

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F05D2230/14 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/4932

摘要： The present invention provides active convection cooling through micro channels within or adjacent to a bond coat layer applied to the trailing edge of a turbine engine high pressure airfoil. When placed adjacent to or within a porous TBC, the micro channels additionally provide transpiration cooling through the porous TBC. The micro channels communicate directly with at least one cooling circuit contained within the airfoil from which they receive cooling air, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate includes an actively cooled flow path surface region that can reduce the cooling requirement for the substrate, the engine can run at a higher firing temperature without the need for additional cooling air, achieving a better, more efficient engine performance. In one embodiment, a metallic bond coat is added to an airfoil with pressure side bleed film cooling slots. The bond coat is grooved such that the grooves are structured, with at least one structured micro groove communicating with at least one cooling fluid supply contained within the airfoil. A TBC layer is applied, using a shadowing technique, over the structured grooves, resulting in the formation of hollow micro channels for the transport of the cooling fluid. In different embodiments, the location of the structured grooves, hence, the resulting micro channels are placed within the airfoil substrate at the substrate/bond coat interface or within the TBC layer.

摘要翻译： 本发明提供了在施加到涡轮发动机高压翼型件的后缘上的粘合涂层之内或附近的微通道的主动对流冷却。 当放置在多孔TBC附近或内部时，微通道另外通过多孔TBC提供蒸腾冷却。 微通道与包含在翼片内的至少一个冷却回路直接连通，从而从它们接收冷却空气，从而为粘结涂层提供直接和有效的冷却。 因为基板包括可以降低基板的冷却要求的主动冷却的流动路径表面区域，所以发动机可以在更高的点火温度下运行，而不需要额外的冷却空气，实现更好，更有效的发动机性能。 在一个实施例中，将金属粘合涂层加入到具有压力侧泄放膜冷却槽的翼型件上。 接合涂层是开槽的，使得凹槽被构造成具有与包含在翼型内的至少一个冷却流体供应源连通的至少一个结构化微槽。 使用阴影技术在结构化凹槽上施加TBC层，导致形成用于输送冷却流体的中空微通道。 在不同的实施例中，结构化凹槽的位置，因此，所得到的微通道在衬底/粘结涂层界面处或在TBC层内被放置在翼型衬底内。

公开(公告)号：US06474947B1

公开(公告)日：2002-11-05

申请号：US09807748

申请日：2001-04-18

申请人： Masanori Yuri

发明人： Masanori Yuri

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2260/22141

摘要： The interior of a gas turbine moving blade is sectioned by a rib into cooling passage portions. Cooling air enters one of the cooling passage portions and turns to flow into the other cooling passage portion. A stagnation area occurs in an end corner portion of the one cooling passage portion, but a cooling hole is provided so that air flow comes outside of the blade through the cooling hole, and thus cooling air flow occurs thereat. Also, a separation area occurs in a tip end portion of the rib due to separation of air flow, but another cooling hole is provided so that air flow comes outside of the blade and cooling air flow occurs thereat. Further, in a gas turbine moving blade having turbulators provided in multi-stages on a cooling passage inner wall, a film cooling hole structure for eliminating separation of cooling air flow between the turbulators is also provided.

摘要翻译： 燃气轮机动叶片的内部由肋分成冷却通道部分。 冷却空气进入冷却通道部分之一并转向另一个冷却通道部分。 在一个冷却通路部的端部角部发生停滞区域，但是设置有冷却孔，使得气流通过冷却孔进入叶片的外侧，因此在那里发生冷却空气流。 此外，由于空气流的分离，在肋的末端部分发生分离区域，而是设置另一个冷却孔，使得空气流进入叶片外部，并且在那里发生冷却空气流。 此外，在具有设置在冷却通路内壁上的多级的紊流器的燃气轮机动叶片中，还提供了用于消除湍流器之间的冷却气流分离的膜冷却孔结构。

公开(公告)号：US06461107B1

公开(公告)日：2002-10-08

申请号：US09818312

申请日：2001-03-27

申请人： Ching-Pang Lee ,  Ramgopal Darolia ,  Robert Edward Schafrik

发明人： Ching-Pang Lee ,  Ramgopal Darolia ,  Robert Edward Schafrik

IPC分类号： F01D518

CPC分类号： F01D5/288 ,  F01D5/183 ,  F01D5/187 ,  F01D5/20 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49318

摘要： The present invention provides for cooling the squealer tip region of a high pressure turbine blade used in a gas turbine engine comprising coating the squealer tip with a metallic bond coat. Micro grooves oriented in the radial direction are fabricated into the airfoil on the interior surface of the squealer tip above and substantially perpendicular to the tip cap. A micro groove oriented in the axial direction is fabricated along the joint corner between the squealer tip side wall and the, tip cap to connect and act as a plenum with all of the micro grooves oriented in the radial direction. Tip cap cooling holes are drilled through the tip cap and connected to the micro groove that ultimately forms a plenum. TBC ceramic is then deposited on both blade external surfaces and the tip cavity, forming micro channels from micro grooves as a result of self shadowing. In this manner, cooling fluid passes from a cooling fluid source through the tip cap holes and into the plenum created by the micro channel, subsequently passing into the micro channels that are oriented in the radial direction. Cooling fluid is thereby directed through the micro channels to cool the squealer, exiting in the vicinity of the tip. Since the TBC is porous, some of the cooling fluid will also flow through the TBC to provide transpiration cooling. The present invention further comprises both the cooled blade and squealer tip region formed by the foregoing methods and the blade and squealer tip with the micro channels for cooling the squealer tip.

摘要翻译： 本发明提供了用于冷却在燃气涡轮发动机中使用的高压涡轮机叶片的鸣响器尖端区域，其包括用金属粘结涂层涂覆尖叫尖端。 在径向方向上定向的微槽在尖端顶部的内表面上被制造成位于尖端顶部的内表面上且基本上垂直于顶盖。 沿着轴向定向的微槽沿着尖叫尖端侧壁和尖端盖之间的接合角制造，以连接并充当具有沿径向方向定向的所有微槽的集气室。 顶盖冷却孔穿过尖端盖并连接到最终形成增压室的微槽。 然后将TBC陶瓷沉积在两个叶片外表面和尖端腔上，由于自身阴影而从微槽形成微通道。 以这种方式，冷却流体从冷却流体源通过顶盖孔并进入由微通道产生的增压室，随后进入沿径向定向的微通道。 因此，冷却流体被引导通过微通道，以冷却在尖端附近离开的鸣叫器。 由于TBC是多孔的，一些冷却流体也将流经TBC以提供蒸发冷却。 本发明还包括通过上述方法形成的冷却刀片和鸣响器尖端区域以及具有用于冷却鸣叫器尖端的微通道的刀片和尖叫尖端。

公开(公告)号：US06422817B1

公开(公告)日：2002-07-23

申请号：US09482361

申请日：2000-01-13

申请人： Ariel C. P. Jacala

发明人： Ariel C. P. Jacala

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F02C7/18 ,  F05D2260/205 ,  F05D2260/22141 ,  F05D2260/2322

摘要： A closed internal cooling circuit for a gas turbine bucket includes axial supply and return passages in the dovetail of the bucket. A first radial outward supply passage provides cooling medium to and along a passageway adjacent the leading edge and then through serpentine arranged passageways within the airfoil to a chamber adjacent the airfoil tip. A second radial passage crosses over the radial return passage for supplying cooling medium to and along a pair of passageways along the trailing edge of the airfoil section. The last passageway of the serpentine passageways and the pair of passageways communicate one with the other in the chamber for returning spent cooling medium radially inwardly along divided return passageways to the return passage. In this manner, both the leading and trailing edges are cooled using the highest pressure, lowest temperature cooling medium.

摘要翻译： 用于燃气轮机铲斗的封闭内部冷却回路包括在铲斗的燕尾槽中的轴向供应和返回通道。 第一径向向外供应通道向邻近前缘的通道提供冷却介质，然后将冷却介质通过翼型内的蛇形设置的通道连接到邻近翼型端的腔室。 第二径向通道跨越径向返回通道，用于将冷却介质沿着沿翼型部分的后缘沿着一对通道供应。 蛇形通道和一对通道的最后一个通道在腔室中与另一个通道连通，用于将分散的返回通道径向向内的废冷却介质返回到返回通道。 以这种方式，使用最高压力，最低温度的冷却介质来冷却前缘和后缘。

公开(公告)号：US06402470B1

公开(公告)日：2002-06-11

申请号：US09412950

申请日：1999-10-05

申请人： William S. Kvasnak ,  Ronald S. LaFleur ,  Friedrich O. Soechting ,  Christopher R. Joe ,  Joe Moroso ,  Douglas A. Hayes

发明人： William S. Kvasnak ,  Ronald S. LaFleur ,  Friedrich O. Soechting ,  Christopher R. Joe ,  Joe Moroso ,  Douglas A. Hayes

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F01D25/12 ,  F05D2260/2212 ,  F05D2260/2214

摘要： A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

摘要翻译： 设置在用于燃气涡轮发动机，一个或多个入口孔和一个或多个出口孔的壁的第一壁部分和第二壁部分之间的冷却回路。 入口孔提供冷却回路中的冷却气流通道，出口孔提供冷却回路外的冷却气流路径。 冷却回路包括在第一壁部和第二壁部之间延伸的多个第一基座。 第一基座布置成一排或多列。

公开(公告)号：US06341939B1

公开(公告)日：2002-01-29

申请号：US09628152

申请日：2000-07-31

申请人： Ching-Pang Lee

发明人： Ching-Pang Lee

IPC分类号： F01D518

CPC分类号： F01D25/12 ,  F01D5/18 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

摘要： A turbine blade includes an integral airfoil, platform, shank, and dovetail, with a pair of holes in tandem extending through the platform and shank in series flow communication with an airflow channel inside the shank. Cooling air discharged through the tandem holes effects multiple, convection, impingement, and film cooling using the same air.

摘要翻译： 涡轮机叶片包括整体的翼型件，平台，柄和燕尾榫，其中一对孔串联延伸穿过平台并且与柄内的气流通道串联地流动连通。 通过串联孔排出的冷却空气使用相同的空气进行多次，对流，冲击和薄膜冷却。

公开(公告)号：US06315518B1

公开(公告)日：2001-11-13

申请号：US09230751

申请日：1999-02-01

申请人： Kazuo Uematsu ,  Kiyoshi Suenaga

发明人： Kazuo Uematsu ,  Kiyoshi Suenaga

IPC分类号： F01D518

CPC分类号： F02C7/16 ,  F01D5/186 ,  F01D5/187 ,  F01D11/04 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2260/2322

摘要： In a stationary blade of a gas turbine, the pressure resisting strength can be decreased by using low-pressure cooling air, and effective cooling can be performed by means of a simple construction. An inside shroud 1 and an outside shroud 2 are cooled by cooling air passing through an impingement plate. A trailing edge portion of a blade portion 6, which is thin in shape, is cooled by cooling air flowing in an air passage 10. Part of this air is discharged through a hole 12 on the side of the inside shroud 1 as inside seal air for a combustion gas passage.

摘要翻译： 在燃气轮机的固定叶片中，可以通过使用低压冷却空气来降低耐压强度，并且可以通过简单的结构进行有效的冷却。 内部护罩1和外部护罩2由通过冲击板的冷却空气冷却。 叶片部分6的后缘部分的形状很薄，由在空气通道10中流动的冷却空气冷却。这种空气的一部分通过作为内部密封空气的内侧护罩1侧的孔12排出 用于燃烧气体通道。

公开(公告)号：US06280140B1

公开(公告)日：2001-08-28

申请号：US09442922

申请日：1999-11-18

申请人： Friedrich O. Soechting ,  William A. Kvasnak ,  Thomas A. Auxier ,  James P. Downs ,  William H. Calhoun ,  Douglas A. Hayes

发明人： Friedrich O. Soechting ,  William A. Kvasnak ,  Thomas A. Auxier ,  James P. Downs ,  William H. Calhoun ,  Douglas A. Hayes

IPC分类号： F01D518

CPC分类号： F23R3/002 ,  F01D5/184 ,  F01D5/186 ,  F05D2250/70 ,  F05D2260/221 ,  F05D2260/2214

摘要： An apparatus and method for cooling a wall for use in a gas turbine engine is provided that includes a cooling air passage having a plurality of segments connected in series by one or more chambers, an inlet aperture, and an exit aperture. The inlet aperture connects the cooling air passage to one side of the wall. The exit aperture connects the cooling air passage to the opposite side of the wall. Cooling air on the inlet aperture side of the wall enters the cooling air passage through the inlet aperture and exits through the exit aperture.

摘要翻译： 提供一种用于冷却用于燃气涡轮发动机的壁的装置和方法，其包括具有通过一个或多个室串联连接的多个段的冷却空气通道，入口孔和出口孔。 入口孔将冷却空气通道连接到墙的一侧。 出口孔将冷却空气通道连接到壁的相对侧。 壁的入口孔侧的冷却空气通过入口孔进入冷却空气通道，并通过出口孔离开。

公开(公告)号：US06267552B1

公开(公告)日：2001-07-31

申请号：US09312061

申请日：1999-05-17

申请人： Bernhard Weigand

发明人： Bernhard Weigand

IPC分类号： F01D518

CPC分类号： F01D5/186 ,  F05D2260/202

摘要： Arrangement of holes for forming a cooling film on a wall (50) which is subjected to a flow of hot gas. Two rows (1, 2) of holes (10, 20) are provided which are arranged adjacent to one another, the diameter (d1) of the upstream holes (10) being smaller than the diameter (d2) of the upstream holes (20). The number of upstream holes (10) is equal to or smaller than the number of downstream holes (20). The use of such an arrangement of holes achieves the formation of an extremely effective cooling film with a simultaneously small consumption of cooling air.

摘要翻译： 在经受热气流的壁（50）上形成用于形成冷却膜的孔的布置。 设置有彼此相邻布置的两排（1,2）孔（10,20），上游孔（10）的直径（d1）小于上游孔（20）的直径（d2） ）。 上游孔（10）的数量等于或小于下游孔（20）的数量。 使用这种孔的布置实现了同时少量冷却空气的非常有效的冷却膜的形成。

公开(公告)号：US06264426B1

公开(公告)日：2001-07-24

申请号：US09026643

申请日：1998-02-20

申请人： Hiroki Fukuno ,  Yasuoki Tomita ,  Kiyoshi Suenaga

发明人： Hiroki Fukuno ,  Yasuoki Tomita ,  Kiyoshi Suenaga

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/2322

摘要： In cooling a gas turbine stationary blade, steam and air are used as cooling media, the steam is recovered surely without leakage and used effectively, and the amount of air required for cooling is decreased to provide a margin for combustion air, by which the gas turbine efficiency is improved. A steam cooling section is provided at the rear from the blade leading edge, and an air cooling section is provided at the blade trailing edge. The steam cooling is effected by cooling the blade by the cooling steam flowing in the serpentine flow path having turbulators after impingement cooling of an outside shroud and by impingement-cooling an inside shroud during the cooling process, the cooling steam being led to a recovery section from the outside shroud. On the other hand, the air cooling section consists of an air flow path extending from the outside shroud to the inside shroud and slot cooling at the blade trailing edge. Thus, the stationary blade is cooled by both of the steam cooling section and air cooling section.

摘要翻译： 在冷却燃气轮机固定叶片时，蒸汽和空气被用作冷却介质，蒸汽被确保地回收而没有泄漏并被有效地使用，并且减少冷却所需的空气量以提供燃烧空气的余量，由此气体 提高了涡轮效率。 在叶片前缘的后部设有蒸汽冷却部，在叶片后缘设有空气冷却部。 蒸汽冷却通过在具有湍流器的蛇形流动路径中流动的冷却蒸汽在外部护罩的冲击冷却之后冷却叶片并且在冷却过程中通过冲击冷却内部护罩来实现，冷却蒸汽被引导到回收部分 从外面的围墙。 另一方面，空气冷却部由从外侧护罩延伸到内部护罩的气流路径和在叶片后缘的冷却槽构成。 因此，固定叶片由蒸汽冷却部分和空气冷却部分两者冷却。