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公开(公告)号：US5374161A
公开(公告)日：1994-12-20
申请号：US166426
申请日：1993-12-13
申请人： George W. Kelch , Thomas A. Auxier
发明人： George W. Kelch , Thomas A. Auxier
CPC分类号： F01D11/005 , F01D11/08 , F01D25/12 , Y02T50/675
摘要： A cooling enhancement for a gas turbine engine blade outer air seal is made up of a plurality of arcuate seal segments, and each one has one or more internal cooling passages. Each segment has a supply surface opposite and in spaced relation to a sealing surface, and first and second end surfaces extending from the sealing surface to the supply surface. Each of the end surfaces includes a substantially planar perpendicular surface and a substantially planar canted surface intersecting at an included angle of between 100 degrees and 140 degrees, and the supply surface has a plurality of cooling orifices adjacent the second end surface. At least one cooling passage extends from the first end surface towards the second end surface, and each cooling passage intersects the first end surface and terminates short of the second end surface. Each cooling passage communicates with the supply surface through at least one of the cooling orifices. Protruding from at least one of the substantially canted surfaces is a plurality of stand-off pedestals that are integral with the canted surface.
摘要翻译： 用于燃气涡轮发动机叶片外部空气密封件的冷却增强由多个弓形密封段组成，并且每个具有一个或多个内部冷却通道。 每个段具有与密封表面相对并且间隔开的供应表面，以及从密封表面延伸到供给表面的第一和第二端表面。 每个端面包括基本上平面的垂直表面和以100度和140度之间的夹角相交的基本上平面的倾斜表面，并且供给表面具有与第二端面相邻的多个冷却孔。 至少一个冷却通道从第一端面朝向第二端面延伸，并且每个冷却通道与第一端面相交并且终止于第二端表面之外。 每个冷却通道通过冷却孔中的至少一个与供给表面连通。 从基本上倾斜的表面中的至少一个突起是与倾斜表面成一体的多个悬置基座。
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公开(公告)号：US5246341A
公开(公告)日：1993-09-21
申请号：US909471
申请日：1992-07-06
申请人： Kenneth B. Hall , Thomas A. Auxier
发明人： Kenneth B. Hall , Thomas A. Auxier
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/12 , F05D2240/126 , F05D2260/2212 , F05D2260/22141
摘要： Internal cooling of the trailing edge of the airfoil of the turbine blade for a gas turbine engine includes a cascade formed from juxtaposed rows of longitudinally extending spaced airfoil shaped vanes or ribs leading cooling air from a supply source through the space between adjacent vanes and discharging out of the blade.
摘要翻译： 用于燃气涡轮发动机的涡轮机叶片的翼缘的后缘的内部冷却包括由并排的纵向延伸的间隔开的翼型叶片或肋条排列的级联，其引导来自供应源的冷却空气通过相邻叶片之间的空间并排出 的刀片。
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公开(公告)号：US4664597A
公开(公告)日：1987-05-12
申请号：US812103
申请日：1985-12-23
CPC分类号： B23H9/10 , F01D5/186 , Y02T50/673 , Y02T50/676
摘要： The wall of a hollow airfoil has a longitudinally extending slot in its external surface which is intersected, at its base, by a plurality of coolant passages in a longitudinally extending row. Each coolant passage has a metering portion at its inner end which communicates with a coolant compartment within the hollow airfoil. Each passage includes a pair of walls downstream of the metering portion which diverge from each other in the longitudinal direction and intersect with the base of the slot to form an outlet for the passage. The diverging walls of adjacent passages substantially meet each other at the base of the slot, wherein coolant fluid from the metering portions of the passages diffuses in the longitudinal direction as it flows toward and into the slot, filling the entire slot and forming a thin, continuous film of coolant downstream of and along the entire length of the slot over the external surface of the airfoil.
摘要翻译： 中空翼型件的壁在其外表面上具有纵向延伸的槽，其在其基部处由纵向延伸的行中的多个冷却剂通道相交。 每个冷却剂通道在其内端具有计量部分，其与中空翼片内的冷却剂隔室连通。 每个通道包括在计量部分下游的一对壁，其在纵向方向上彼此分开并且与槽的基部相交以形成用于通道的出口。 相邻通道的发散壁基本上在槽的底部彼此相遇，其中来自通道的计量部分的冷却剂流体在其朝向和流入槽中的纵向方向上扩散，填充整个狭槽并形成薄的， 在翼面的外表面上沿着槽的整个长度下游的冷却剂的连续薄膜。
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公开(公告)号：US5899058A
公开(公告)日：1999-05-04
申请号：US859236
申请日：1997-05-20
CPC分类号： F02C9/18 , F01D17/105 , F02K3/075
摘要： A bypass air valve for a gas turbine engine is provided which includes a liner, a strap, and means for selectively actuating the valve. The liner includes an inner radial surface, an outer radial surface, a plurality of first regions, and a plurality of second regions. Each first region includes a plurality of first apertures. Each second region includes a plurality of second apertures. The strap includes a plurality of openings and a plurality of third regions. Each third region includes a plurality of third apertures. The valve may be selectively actuated into an open or a closed position. In the open position, the first regions are substantially aligned with the openings and the third regions are substantially aligned with the second regions. In the closed position, the first regions are substantially aligned with the third regions and the second regions are substantially aligned with the openings.
摘要翻译： 提供了一种用于燃气涡轮发动机的旁通空气阀，其包括衬套，带子和用于选择性地致动阀的装置。 衬套包括内径向表面，外径向表面，多个第一区域和多个第二区域。 每个第一区域包括多个第一孔。 每个第二区域包括多个第二孔。 该带包括多个开口和多个第三区域。 每个第三区域包括多个第三孔。 阀可以选择性地致动到打开或关闭位置。 在打开位置，第一区域基本上与开口对齐，并且第三区域基本上与第二区域对齐。 在闭合位置，第一区域基本上与第三区域对准，并且第二区域基本上与开口对准。
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公开(公告)号：US5720431A
公开(公告)日：1998-02-24
申请号：US236092
申请日：1988-08-24
CPC分类号： F01D11/10 , F01D5/186 , F01D5/20 , F05D2260/201 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： An internally air cooled turbine blade for a gas turbine engine of the type including a trailing edge section, leading edge section and mid chord section wherein each section includes a straight through radial passage communicating cooling air from the root to the tip of the blade, and the radial passages (feed channels) on the pressure side and suction side supply the cooling air to the film cooling holes in the airfoil surface and the radial passage (feed chamber) in the mid chord section replenishes the feed channels with cooling air through replenishment cooling holes interconnecting the feed channels and feed chamber. The rotation of the blade imparts a centrifugal pumping action to the air within the feed chamber for maximizing the cooling effectiveness of the cooling air. The air discharging at the tip cools the tip of the blade and provides tip aerodynamic sealing and the leading edge and trailing edge are similarly fed cooling air.
摘要翻译： 一种用于燃气涡轮发动机的内部空气冷却涡轮机叶片，其包括后缘部分，前缘部分和中间弦部分，其中每个部分包括将冷却空气从根部延伸到叶片的尖端的直通径向通道，以及 压力侧和吸入侧的径向通道（进料通道）将冷却空气提供给翼型表面中的薄膜冷却孔，并且中弦部分中的径向通道（进料室）通过补充冷却来补充具有冷却空气的进料通道 将进料通道和进料室相互连接的孔。 叶片的旋转对进料室内的空气施加离心泵送作用，以最大化冷却空气的冷却效果。 尖端处的空气冷却叶片的尖端并提供尖端空气动力学密封，并且前缘和后缘类似地送入冷却空气。
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公开(公告)号：US5700131A
公开(公告)日：1997-12-23
申请号：US236093
申请日：1988-08-24
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2260/201 , F05D2260/2212 , Y02T50/671 , Y02T50/676
摘要： An internally cooled turbine blade for a gas turbine engine is modified at the leading and trailing edges to include a dynamic cool air flowing radial passageway with an inlet at the root and a discharge at the tip feeding a plurality of radially spaced film cooling holes in the airfoil surface. Replenishment holes communicating with the serpentine passages radially spaced in the inner wall of the radial passage replenish the cooling air lost to the film cooling holes. The discharge orifice is sized to match the backflow margin to achieve a constant film hole coverage throughout the radial length. Trip strips may be employed to augment the pressure drop distribution
摘要翻译： 用于燃气涡轮发动机的内部冷却的涡轮机叶片在前缘和后缘处被改变，以包括具有在根部处的入口的动态冷空气流动的径向通道，并且在末端处的排放物将多个径向间隔开的薄膜冷却孔 机翼表面。 与在径向通道的内壁中径向隔开的蛇形通道相通的补充孔补充了损失到膜冷却孔的冷却空气。 排气孔的尺寸设计成匹配回流边缘，以在整个径向长度上实现恒定的膜孔覆盖。 可以使用跳闸条来增加压降分布
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公开(公告)号：US5375973A
公开(公告)日：1994-12-27
申请号：US993862
申请日：1992-12-23
CPC分类号： F01D25/12 , F01D11/08 , Y02T50/67 , Y02T50/675
摘要： This disclosure describes a cooling and manufacturing enhancement for gas turbine engine outer air seals. The invention provides convective cooling in a counter-flow array, internal heat transfer augmentation through the use of boundary layer trip-strips, coolant Mach number control through the use of tapered convective channels, inter-segment purge without additional secondary cooling air, and is castable.
摘要翻译： 本公开描述了用于燃气涡轮发动机外部空气密封件的冷却和制造增强。 本发明提供逆流阵列中的对流冷却，通过使用边界层跳闸条的内部热传递增强，通过使用锥形对流通道的冷却剂马赫数控制，不具有另外的二次冷却空气的段间吹扫，并且 浇注料
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公开(公告)号：US5129231A
公开(公告)日：1992-07-14
申请号：US492188
申请日：1990-03-12
申请人： James T. Becker , Thomas A. Auxier
发明人： James T. Becker , Thomas A. Auxier
CPC分类号： F23R3/10 , F23R3/14 , F23D2214/00
摘要： The heatshield for the fuel nozzles mounted at the dome of an annular combustor for a gas turbine engine is cooled by discretely locating cool air film cooling holes in the heatshield oriented to inject the cooling air with the recirculation zone to be compatible with the direction of the swirling air in the recirculated zone.
摘要翻译： 用于安装在用于燃气涡轮发动机的环形燃烧器的圆顶处的燃料喷嘴的挡风玻璃通过离散地定位在挡风玻璃中的冷空气膜冷却孔而被冷却，所述冷却空气膜定向成将再循环区域注入冷却空气以与 在再循环区域内旋转空气。
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公开(公告)号：US4820122A
公开(公告)日：1989-04-11
申请号：US185227
申请日：1988-04-25
CPC分类号： F01D25/32 , F01D5/187 , F05D2260/607 , Y02T50/676
摘要： Dirt removal means for an internally air cooled blade for a gas turbine engine of the type that includes multi passes some of which are serpentine as made in situ by casting the ribs so as to be angularly disposed at the root of the blade and a straight through passageway with an opening at the tip. The velocity of the airstream in the straight through passageway being sufficiently high to carry the dirt through the opening and the angularly disposed ribs overlying the entrance to the other passageway so as to divert the dirt entrained airstream into the straight through passageway while allowing relatively dirt-free air to turn the angle of the rib to enter the serpentine passes.
摘要翻译： 用于燃气涡轮发动机的内部空气冷却叶片的除尘装置，其包括多次通过，其中一些是通过浇铸肋原位制造的蛇形，以便成角度地设置在叶片的根部处，并且直线穿过 在尖端具有开口的通道。 直通通道中的气流的速度足够高以将污物通过开口和角度布置的肋覆盖在另一通道的入口上，以将污物夹带的气流转移到直通通道中，同时允许相对污垢 - 自由空气转动肋骨的角度进入蛇纹通道。
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公开(公告)号：US4767268A
公开(公告)日：1988-08-30
申请号：US82403
申请日：1987-08-06
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A hollow, cooled airfoil has a pair of nested, coolant channels therein which carry separate coolant flows back and forth across the span of the airfoil in adjacent parallel paths. The coolant in both channels flows from a rearward to forward location within the airfoil allowing the coolant to be ejected from the airfoil near the leading edge through film coolant holes.
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