-
公开(公告)号：US4297077A
公开(公告)日：1981-10-27
申请号：US55833
申请日：1979-07-09
申请人： George A. Durgin , Daniel E. Demers
发明人： George A. Durgin , Daniel E. Demers
CPC分类号： F01D5/189 , F05D2260/201
摘要： A hollow gas turbine vane is shown enclosing, in spaced relation, a vane insert for receiving cooling air. The insert has a plurality of apertures for selectively directing jets of the cooling air against the internal walls of the vane. A portion of the air is discharged from within the vane chamber through a slit in the trailing edge which contains cooling pins extending transversely thereacross to maintain the slit dimensionally stable and also induce turbulence in the exhausting cooling air to improve its cooling effectiveness. Certain apertures in the insert adjacent the trailing edge are selectively directed to cause jets of the cooling air to impinge at the base of certain of the pins in the inlet area of the slit to promote turbulence in the air entering the slit and adjacent the internal face, thereby maximizing heat transfer from the slit walls to the air.
摘要翻译： 中空燃气涡轮机叶片被示出为间隔开地封闭用于接收冷却空气的叶片插入件。 插入件具有多个孔，用于选择性地将冷却空气的喷射限制在叶片的内壁上。 空气的一部分通过后缘的狭缝从叶片室内排出，其中包含横向横向延伸的冷却销，以保持狭缝的尺寸稳定性，并且还引起排气冷却空气中的湍流以提高其冷却效果。 与后缘相邻的插入件中的某些孔被选择性地导向，使得冷却空气的喷嘴在狭缝的入口区域中的某些销的基部处撞击，以促进进入狭缝的空气和邻近内表面的湍流 从而使从狭缝壁到空气的热传递最大化。
-
公开(公告)号：US6050079A
公开(公告)日：2000-04-18
申请号：US997980
申请日：1997-12-24
摘要： A modulated flow transfer apparatus for transferring a fluid flow from a static element to a rotor of a gas turbine engine has an annular static inducer for accelerating the fluid flow in a substantially circumferential direction. The inducer has an annular row of identical first and second flow passages with first and second inlets respectively and outlets. First and second flow means direct first and second portions of the flow to the first and second flow passages, respectively. A valve is used for selectively modulating the second portion of the flow which together with a controller may be used for selectively preventing the second portion of flow from flowing through the second flow passages during a first cruise of engine operation and allowing substantially unrestricted flow therethrough during a takeoff mode of engine operation. The second flow means preferably includes an inducer manifold disposed between the valve and the second inlets. Exhaust ducts connect corresponding ones of the second inlets to the inducer manifold. The inducer manifold is preferably disposed inside a plenum used to feed cooling air to the first passages.
摘要翻译： 用于将流体流从静态元件传递到燃气涡轮发动机的转子的调制流传递装置具有用于在大致圆周方向上加速流体流动的环形静态诱导器。 导流器具有一排相同的第一和第二流动通道，分别具有第一和第二入口以及出口。 第一和第二流动装置分别将流体的第一和第二部分直接引导到第一和第二流动通道。 阀用于选择性地调节流量的第二部分，其与控制器一起可以用于在发动机操作的第一次巡航期间选择性地防止第二部分流动流过第二流动通道，并且允许基本上不受限制的流过其中 发动机运转的起飞模式。 第二流动装置优选地包括设置在阀和第二入口之间的导流器歧管。 排气管将相应的第二入口连接到导流器歧管。 导流器歧管优选地设置在用于将冷却空气供给到第一通道的增压室内部。
-
公开(公告)号：US06220817B1
公开(公告)日：2001-04-24
申请号：US08971305
申请日：1997-11-17
申请人： George A. Durgin , Ching-Pang Lee
发明人： George A. Durgin , Ching-Pang Lee
IPC分类号： F01D508
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits having outer and inner serpentine portions, respectively, in different longitudinal tiers with the outer serpentine position being disposed longitudinally above the inner tier serpentine position for differentially longitudinally cooling the airfoil. The outer and inner serpentine portions include outer and inner exits and entrances wherein the outer and inner exits are positioned aft of the outer and inner entrances, respectively, so as to have a chordal flow direction aftwards from the leading edge to the trailing edge within the serpentine portions.
摘要翻译： 涡轮机翼片包括多个内部肋条，其限定至少两个独立的蛇形冷却回路，分别在不同的纵向层中具有外部和内部蛇形部分，其中外部蛇形位置纵向设置在内部蛇形位置上方，用于差异地纵向冷却翼型件 。 外部和内部蛇形部分包括外部和外部出口和入口，其中外部出口和内部出口分别位于外部入口和内部入口的后方，以便在内部出口和内部出口之间具有从前缘到后缘的弦向流动方向 蛇纹石部分。
-
公开(公告)号：US5591007A
公开(公告)日：1997-01-07
申请号：US455869
申请日：1995-05-31
CPC分类号： F01D5/187 , Y02T50/676
摘要： A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits arranged in part in different longitudinal tiers, with an outer tier circuit being disposed in part longitudinally above an inner tier circuit for differentially longitudinally cooling the airfoil.
摘要翻译： 涡轮机翼片包括限定至少两个独立的蛇形冷却回路的多个内部肋条，其部分地布置在不同的纵向层中，外层电路部分地纵向地设置在内层电路的上方，用于差异地纵向冷却翼型件。
-
公开(公告)号：US06207295B1
公开(公告)日：2001-03-27
申请号：US09353031
申请日：1999-07-13
IPC分类号： B32B1500
CPC分类号： C23C28/3215 , C23C28/321 , C23C28/345 , C23C28/3455 , C23C28/36 , C23C28/42 , F01D5/288 , F05C2201/0463 , F05C2201/0466 , F05D2230/90 , F05D2300/121 , F05D2300/132 , F05D2300/211 , F05D2300/2112 , F05D2300/611 , Y02T50/672 , Y02T50/673 , Y10T428/12493 , Y10T428/12576 , Y10T428/12674 , Y10T428/12771 , Y10T428/12826 , Y10T428/12833
摘要： A coated article comprises a substrate, an inner environmental resistant coating portion including Al on the substrate, and an outer heat energy reflecting and oxygen diffusion inhibiting coating portion outward of the inner portion. The outer coating portion is multi-layer, comprising 6-48 discrete stacked layers and a total outer coating portion thickness in the range of about 2.5-25 microns.
摘要翻译： 涂布制品包括基材，在基材上包含Al的内部耐环境涂层部分和外部热能反射和氧扩散抑制涂层部分在内部外部。 外涂层部分是多层的，包括6-48个分立的堆叠层，总外涂层部分厚度在约2.5-25微米的范围内。
-
公开(公告)号：US6155778A
公开(公告)日：2000-12-05
申请号：US223065
申请日：1998-12-30
申请人： Ching-Pang Lee , George A. Durgin
发明人： Ching-Pang Lee , George A. Durgin
CPC分类号： F01D5/20 , F01D11/08 , F01D25/12 , F28F13/02 , F05D2240/11 , F05D2260/202 , Y02T50/676 , Y10S415/914
摘要： A turbine shroud includes a panel having inner and outer surfaces extending between forward and aft opposite ends. The panel includes forward and aft hooks for supporting the panel radially atop a row of turbine rotor blades. The panel includes a plurality of recesses in the inner surface thereof which face tips of the blades. The recesses extend only in part into the panel for reducing surface area exposed to the blade tips.
摘要翻译： 涡轮机罩包括具有在前后相对端之间延伸的内表面和外表面的面板。 面板包括用于在一排涡轮转子叶片的径向上支撑面板的前钩和后钩。 面板包括面向刀片顶端的内表面的多个凹部。 这些凹槽仅部分地延伸到面板中，以减少暴露于叶片尖端的表面积。
-
公开(公告)号：US06174134B1
公开(公告)日：2001-01-16
申请号：US09264384
申请日：1999-03-05
申请人： Ching-Pang Lee , George A. Durgin
发明人： Ching-Pang Lee , George A. Durgin
IPC分类号： F01D518
CPC分类号： F01D5/187 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and spaced apart to define first and second cavities separated by a septum therebetween. An aft bridge extends along the first cavity and includes a row of outlet holes therein. The septum includes a row of inlet holes. And, turbulators are disposed in rows inside the first cavity, and extend from the first sidewall toward the second sidewall. The turbulators are aligned with the inlet holes for multiple impingement cooling thereof.
摘要翻译： 涡轮机翼片包括在前缘和后缘处连接在一起的第一和第二侧壁，并且间隔开以限定由它们之间的隔膜隔开的第一和第二腔。 后桥沿着第一腔延伸并且在其中包括一排出口孔。 隔膜包括一排入口孔。 并且，在第一空腔内排列有紊流器，并且从第一侧壁向第二侧壁延伸。 紊流器与入口孔对齐，用于多次冲击冷却。
-
公开(公告)号：US5967752A
公开(公告)日：1999-10-19
申请号：US1659
申请日：1997-12-31
CPC分类号： F01D5/187 , F05D2240/126 , Y02T50/676
摘要： A turbine airfoil includes a plurality of internal ribs joined to laterally opposite first and second sidewalls to define a serpentine cooling circuit therein. A span rib extends longitudinally between a root and tip of the airfoil. And, a slant rib extends obliquely to the span rib to define respective portions of the serpentine circuit longitudinally above and below the slant rib.
摘要翻译： 涡轮机翼片包括与横向相对的第一和第二侧壁连接的多个内肋，以在其中限定蛇形冷却回路。 跨度肋在翼型的根部和尖端之间纵向延伸。 并且，倾斜的肋部倾斜地延伸到跨肋，以在纵向肋部的上方和下方纵向限定蛇形回路的相应部分。
-
公开(公告)号：US5749701A
公开(公告)日：1998-05-12
申请号：US740450
申请日：1996-10-28
申请人： Jonathon P. Clarke , Charles E. Steckle , Kevin W. McMahan , George A. Durgin , Randall C. Bauer
发明人： Jonathon P. Clarke , Charles E. Steckle , Kevin W. McMahan , George A. Durgin , Randall C. Bauer
CPC分类号： F01D11/001 , F05D2260/20
摘要： A seal assembly positioned between forward and aft rotor stages of a turbine separates a forward cavity and an aft cavity on each side thereof. The seal assembly includes a seal body connected to a platform portion of a stator nozzle located between the forward and aft rotor stages, wherein an inner seal cavity in flow communication with an insert in the stator nozzle is formed therebetween. A static seal member is arranged in sealing relationship with a rotary toothed member between the forward and aft cavities, with the static seal member being connected to the seal body. An intermediate member is positioned between the seal body and the static seal member to define a plenum therebetween in flow communication with the inner seal cavity, the intermediate member having a plurality of angled passages formed therein in which a first end thereof is in flow communication with the plenum and a second end thereof is in flow communication with the aft cavity. Accordingly, air entering the stator nozzle insert flows into the inner seal cavity and then into the plenum so that it exits through the angled passages into the aft cavity at an angle with respect to an axis of rotation of the aft rotor stage. In this way, such air will acquire a tangential velocity component in the direction of rotation of the aft rotor stage.
摘要翻译： 定位在涡轮机的前后转子级之间的密封组件在其每侧分离前腔和后空腔。 密封组件包括密封体，其连接到位于前部和后部转子级之间的定子喷嘴的平台部分，其中在其间形成有与定子喷嘴中的插入件流动连通的内部密封腔。 静密封构件与前后空腔之间的旋转齿形构件密封关系，静密封构件与密封体连接。 中间构件位于密封体和静态密封构件之间，以在其间限定与内密封腔流动连通的中间构件，中间构件具有形成在其中的多个成角度的通道，其中第一端与第一端部 气室和其第二端与后腔流体连通。 因此，进入定子喷嘴插入件的空气流入内密封空腔，然后进入通风室，使得其相对于后转子级的旋转轴线成角度地离开成角度的通道进入后空腔。 以这种方式，这样的空气将在后转子级的旋转方向上获得切向速度分量。
-
公开(公告)号：US06196792B1
公开(公告)日：2001-03-06
申请号：US09239638
申请日：1999-01-29
申请人： Ching-Pang Lee , George A. Durgin
发明人： Ching-Pang Lee , George A. Durgin
IPC分类号： F04D3100
CPC分类号： F01D11/08 , F01D25/12 , F05D2260/202 , Y02T50/676
摘要： A turbine shroud includes a panel having a forward end, an opposite aft end, and a middle therebetween. Cooling holes extend through the panel for channeling cooling air therethrough. The holes are arranged in a pattern of greater density aft of the panel middle than forward of the panel middle for effecting preferential cooling.
摘要翻译： 涡轮罩包括具有前端，相对的后端以及中间的面板。 冷却孔延伸穿过面板，用于将冷却空气引导通过。 这些孔以面板中间的较大密度的方式布置成与面板中间的前方相比较，以实现优先冷却。
-
-
-
-
-
-
-
-
-
搜索结果
11 条记录 (耗时 0.016 秒)
