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公开(公告)号：US5271715A
公开(公告)日：1993-12-21
申请号：US993584
申请日：1992-12-21
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/2212
摘要： An air cooled gas engine turbine blade that includes a plurality of longitudinally spaced cavities adjacent the leading edge of the blade is designed to include angularly disposed impingement passages flowing cooling air into each of the cavities in a direction extending from the root to the tip of the blade and including an annular projection upstream of the impingement passage but adjacent thereto for directing air into the respective cavities with total instead of static pressure. The impingement holes are oriented to align with the film cool holes in the blade surface at the leading edge. Ribs formed between cavities are also oriented to be parallel to the impingement holes.
摘要翻译： 包括与叶片的前缘相邻的多个纵向隔开的空腔的空气冷却燃气发动机涡轮机叶片被设计成包括角度设置的冲击通道，其将冷却空气沿从根部延伸到每个空腔的方向 叶片并且包括在冲击通道上游但邻近的环形突起，用于将空气全部导入相应的空腔中而不是静压力。 冲击孔定位成与前缘处的叶片表面中的膜冷却孔对准。 在空腔之间形成的肋还被定向成平行于冲击孔。
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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。
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公开(公告)号：US4773593A
公开(公告)日：1988-09-27
申请号：US45345
申请日：1987-05-04
CPC分类号： F02K1/822 , F01D5/184 , F23R3/002 , F28F13/02 , F05D2260/202 , F23R2900/00005 , Y02T50/676
摘要： A coolable thin metal sheet incorporated in an exhaust nozzle for a gas turbine powered aircraft includes a hot surface, a cool surface and a plurality of triangular sloped depressions which project through the cold gas side of the sheet. Each depression includes a gradually sloped essentially triangular surface which extends gradually in the direction of flow, from a deep, flat faced apex to a flush base, with the apex providing a flat surface perpendicular to the sloped surface. A hole, drilled through the apex admits cooling air which forms a film on the hot gas surface. Utilizing a plurality of such depressions provides precise control of the quantity and direction of cooling gas admitted while allowing use of the thinnest material meeting mechanical requirements, providing optimized film cooling while minimizing nozzle weight.
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公开(公告)号：US4187054A
公开(公告)日：1980-02-05
申请号：US898061
申请日：1978-04-20
申请人： Delmer H. Landis, Jr. , Paul W. Lozier , Louis Lievestro , Thomas A. Auxier , John H. Starkweather
发明人： Delmer H. Landis, Jr. , Paul W. Lozier , Louis Lievestro , Thomas A. Auxier , John H. Starkweather
CPC分类号： F01D9/042 , F01D25/12 , F01D5/18 , F05D2240/10 , F05D2240/81 , F05D2260/201 , Y02T50/676
摘要： A gas turbine engine comprising a number of annular wall sectors which form a complete circular wall defining a hot gas passage is provided with a cooling system incorporating a plurality of hollow impingement vessels disposed in a circular array within an annular chamber behind the wall. Cooling fluid is routed to the self-contained impingement pressure vessels which are provided with perforations to disperse the cooling fluid into impingement upon the wall. Unlike prior systems, the impingement vessels are not physically attached to the band but, rather, are supported by a structural frame which partially defines the annular chamber and, in the preferred embodiment, also supports the wall sectors. Since the impingement vessel, and not the backside of the wall, is the pressure vessel for the pressurized cooling fluid, leakage between adjacent wall sectors is greatly reduced with no loss in cooling effectiveness when compared to conventional cooling systems. Thus, turbine cycle performance is improved.
摘要翻译： 包括形成限定热气体通道的完整圆形壁的多个环形壁扇区的燃气涡轮发动机设置有冷却系统，该冷却系统结合有多个中空冲击容器，该多个中空冲击容器以围绕壁的环形室内的圆形阵列设置。 冷却流体被引导到设置有穿孔的独立的冲击压力容器，以将冷却流体分散到壁上。 与现有系统不同，冲击容器不物理地附接到带上，而是由部分地限定环形室的结构框架支撑，并且在优选实施例中也支撑壁扇区。 由于冲击容器而不是墙的后侧是用于加压冷却流体的压力容器，与传统的冷却系统相比，相邻的壁扇区之间的泄漏大大降低，同时冷却效率没有损失。 因此，提高了涡轮循环性能。
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公开(公告)号：US6164912A
公开(公告)日：2000-12-26
申请号：US217697
申请日：1998-12-21
申请人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier , Frederick Steinbauer, Jr.
发明人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier , Frederick Steinbauer, Jr.
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/25
摘要： A hollow airfoil is provided which includes a body having an external wall and an internal cavity. The external wall includes a suction side portion and a pressure side portion. The portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. A stagnation line extends along the leading edge. A plurality of cooling apertures, disposed spanwise along the leading edge. According to one aspect of the present invention, the apertures extend through the external wall along a helical path. According to another aspect of the present invention, the apertures are alternately directed towards the suction side portion and the pressure side portions of the airfoil.
摘要翻译： 提供了一种空心翼片，其包括具有外壁和内腔的主体。 外壁包括吸力侧部分和压力侧部分。 这些部分在前缘和后缘之间并行延伸，并且在内径向表面和外径向表面之间展开。 停滞线沿着前缘延伸。 沿着前缘沿翼展方向设置的多个冷却孔。 根据本发明的一个方面，孔径沿着螺旋路径延伸穿过外壁。 根据本发明的另一方面，所述孔交替地指向翼型的吸入侧部分和压力侧部分。
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公开(公告)号：US6129515A
公开(公告)日：2000-10-10
申请号：US979718
申请日：1992-11-20
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , Y02T50/676
摘要： Film cooling effectiveness for internally air cooled turbine blades of gas turbine engines is enhanced by including an interconnecting passage to the film cooling hole that is in communication with a lower internal pressure in the blade to create a suction at the exit end of the film hole to limit penetration into the gas stream.
摘要翻译： 燃气涡轮发动机的内部空气冷却涡轮叶片的薄膜冷却效果通过在薄膜冷却孔中包括相互连通的通道而增强，所述连接通道与叶片中的较低内部压力连通，以在薄膜孔的出口端产生吸力， 限制渗透气流。
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公开(公告)号：US5131222A
公开(公告)日：1992-07-21
申请号：US621695
申请日：1990-11-28
IPC分类号： F02K1/82
CPC分类号： F02K1/822 , Y02T50/675
摘要： Flow rate of coolant air is increased upon elevated nozzle gas temperatures to increase nozzle liner cooling effect. A hot side curved plate is superposed over a cold side curved plate which overlays a pressurized cooling air cavity. First and second sets of apertures are formed through the first and second plates respectively. At low temperature operation, the gap between the plates is small and the staggering of the apertures restricts the flow rate of cooling gas through the plates. As temperatures rise, the hot side plate thermally expands and the gap between the plates increases to reduce the mechanical impedance effect of the staggering and to thus increase coolant flow rates.
摘要翻译： 在喷嘴气体温度升高时，冷却剂空气的流量增加，从而增加喷嘴衬套的冷却效果。 热侧弯曲板叠加在覆盖加压冷却空气腔的冷侧弯曲板上。 分别通过第一和第二板形成第一和第二组孔。 在低温运行时，板间的间隙很小，孔的交错限制了冷却气体通过板的流量。 随着温度升高，热侧板热膨胀并且板之间的间隙增加以减小交错的机械阻抗效应并因此增加冷却剂流速。
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公开(公告)号：US4864828A
公开(公告)日：1989-09-12
申请号：US187762
申请日：1988-04-29
IPC分类号： F23R3/08
CPC分类号： F23R3/08 , Y02T50/675
摘要： Aircraft engine cooling apparatus having a plurality of cooling gas inlet nozzles, producing first streams of cooling gas moving in a forward direction, a plurality of first direction reversal members for splitting the first streams into second and third streams straddling the nozzles, and substantially reversed in direction relative to the direction of the first streams, a plurality of second direction reversal members, positioned between pairs of adjacent nozzles, for again substantially reversing the directions of the second and third streams, while combining the second and third streams to form a fourth stream of laminar flow cooling film, and wherein adjacent pairs of the first direction reversal members have wall portions configured to form gradually diverging channels through which the fourth stream cooling film moves.
摘要翻译： 具有多个冷却气体入口喷嘴的飞机发动机冷却装置，产生沿向前方向移动的冷却气体的第一流;多个第一方向反转构件，用于将第一流分离成跨过喷嘴的第二和第三流， 相对于第一流的方向的多个第二方向反转构件，位于相邻喷嘴对之间的多个第二方向反转构件，用于再次大体上反转第二和第三流的方向，同时组合第二和第三流以形成第四流 层流冷却膜，并且其中相邻的第一方向反转构件对具有壁部，其被配置为形成逐渐发散的通道，第四流冷却膜通过该通道移动。
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公开(公告)号：US4770608A
公开(公告)日：1988-09-13
申请号：US812108
申请日：1985-12-23
申请人： Leon R. Anderson , Thomas A. Auxier
发明人： Leon R. Anderson , Thomas A. Auxier
IPC分类号： F01D5/18
CPC分类号： F01D5/186
摘要： The film of cooling air adjacent the outer surface of the airfoil of a turbine of a gas turbine engine issuing from internally of the turbine subsequent to cooling is controlled by regulating the pressure ratio of the internal to external pressures by forming an internal chamber extending longitudinally in the turbine and having fixed orifices admitting cooling air therein bearing a predetermined relationship to the exit orifices forming the film of cooling air. By regulating this pressure ratio the diameter of the exit holes can be longer than heretofore designs for a given application so that they can be precast rather than drilled and can be arranged to give fuller coverage of films of cooling air on the outer surface of the airfoil.
摘要翻译： 通过在内部与外部压力之间形成一个纵向延伸的内部腔室来控制在冷却之后从涡轮内部发出的燃气涡轮发动机涡轮机的翼面的外表面附近的冷却空气薄膜 涡轮机并且具有固定孔口，其中承载与形成冷却空气薄膜的出口的预定关系的冷却空气。 通过调节该压力比，出口孔的直径可以比给定应用的设计长，使得它们可以是预制的而不是钻孔的，并且可以布置成在翼型件的外表面上更全面地覆盖冷却空气膜 。
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公开(公告)号：US06247896B1
公开(公告)日：2001-06-19
申请号：US09338376
申请日：1999-06-23
申请人： Thomas A. Auxier , James P. Downs , William S. Kvasnak , Friedrich O. Soechting , William H. Calhoun , Douglas A. Hayes
发明人： Thomas A. Auxier , James P. Downs , William S. Kvasnak , Friedrich O. Soechting , William H. Calhoun , Douglas A. Hayes
IPC分类号： F01D518
CPC分类号： F01D5/18 , F01D5/187 , F05D2230/14 , F05D2250/15 , F05D2250/70 , F05D2260/2214
摘要： A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.
摘要翻译： 提供了一种用于冷却燃气涡轮发动机内的壁的方法和装置，其包括以下步骤：（1）提供具有内表面和外表面的壁; （2）在所述壁内提供具有在所述内表面和所述外表面之间延伸的用于冷却空气的通道的所述壁内的冷却微电路; 和（3）通过增加微电路内的每单位流动的平均热传递系数来增加从通道内的壁到流体流的传热。 根据一个方面，本发明的方法和装置可以被调整以使手上的壁的热分布基本匹配。
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