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公开(公告)号：US20080130708A1
公开(公告)日：2008-06-05
申请号：US11979324
申请日：2007-11-01
IPC分类号： G01K1/00
CPC分类号： G01K1/14 , C09D5/26 , F01D21/003 , F05D2260/80 , G01K11/06 , G01K11/12 , G01K13/02 , G01K2013/024
摘要： A temperature measuring arrangement measures the temperature of a fluid passing a component. The arrangement comprises a temperature measuring device having a substrate of low thermal capacity that has applied thereto two or more temperature recording media. The device is attached to and spaced apart from the component and is in the fluid flow.
摘要翻译： 温度测量装置测量通过部件的流体的温度。 该装置包括具有低热容量基板的温度测量装置，其已经施加到两个或多个温度记录介质上。 该装置附接到部件并与该部件间隔开并处于流体流中。
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公开(公告)号：US07819578B2
公开(公告)日：2010-10-26
申请号：US11979324
申请日：2007-11-01
CPC分类号： G01K1/14 , C09D5/26 , F01D21/003 , F05D2260/80 , G01K11/06 , G01K11/12 , G01K13/02 , G01K2013/024
摘要： A temperature measuring arrangement measures the temperature of a fluid passing a component. The arrangement includes a temperature measuring device having a substrate of low thermal capacity that has applied thereto two or more temperature recording media. The device is attached to and spaced apart from the component and is in the fluid flow.
摘要翻译： 温度测量装置测量通过部件的流体的温度。 该装置包括具有低热容量的基板的温度测量装置，其已经施加到两个或多个温度记录介质上。 该装置附接到部件并与该部件间隔开并处于流体流中。
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公开(公告)号：US08052377B2
公开(公告)日：2011-11-08
申请号：US11976989
申请日：2007-10-30
IPC分类号： F01D25/12
CPC分类号： F02K1/386 , F02K1/827 , Y02T50/671
摘要： A gas turbine engine including a bypass duct defined by radially outer and inner walls, the radially inner wall defined by acoustic panels. The acoustic panels define the outer wall of a heated fire zone. In conventional engines an insulating blanket is attached to the panels, however, this is heavy and costly. Cooling film means are configured to pass bypass air through and over an internal surface of the panel.
摘要翻译： 一种燃气涡轮发动机，其包括由径向外壁和内壁限定的旁路管，所述径向内壁由隔音板限定。 声学板限定加热的防火区的外壁。 在传统的发动机中，绝缘毯被附着到面板上，然而，这是重且昂贵的。 冷却膜装置构造成使旁路空气通过面板内表面。
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公开(公告)号：US20080223961A1
公开(公告)日：2008-09-18
申请号：US12076076
申请日：2008-03-13
摘要： A pipe for carrying a fluid, having a longitudinal axis and defining a radial aperture for release of a jet of fluid having a radial direction component α, the aperture having an aspect ratio greater than 2 and arranged with its elongate axis within 30 degrees of the longitudinal axis and having area greater than 0.2 the cross-sectional area of the pipe, the fluid jet having an angle α between 30 and 80 degrees from the longitudinal axis.
摘要翻译： 用于承载流体的管道，其具有纵向轴线并且限定用于释放具有径向方向分量α的流体射流的径向孔，所述孔具有大于2的纵横比并且其细长轴线布置在其中的30度内 纵向轴线并且具有大于0.2的管的横截面积的面积，流体射流与纵向轴线的角度α在30和80度之间。
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公开(公告)号：US20080112796A1
公开(公告)日：2008-05-15
申请号：US11976989
申请日：2007-10-30
IPC分类号： F04D29/04
CPC分类号： F02K1/386 , F02K1/827 , Y02T50/671
摘要： A gas turbine engine (10) comprising a bypass duct (22) defined by radially outer and inner walls (27, 30), the radially inner wall (30) defined by acoustic panels (30). The acoustic panels (30) define the outer wall of a heated fire zone. In conventional engines an insulating blanket is attached to the panels, however, this is heavy and costly. The present invention comprises cooling film means (50) to pass bypass air through and over an internal surface (39) of the panel (30).
摘要翻译： 一种燃气涡轮发动机（10），包括由径向外壁和内壁（27,30）限定的旁通管道（22），所述径向内壁（30）由隔音板（30）限定。 声学板（30）限定加热的防火区的外壁。 在传统的发动机中，绝缘毯被附着到面板上，然而，这是重且昂贵的。 本发明包括使旁路空气通过面板（30）的内表面（39）的冷却膜装置（50）。
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公开(公告)号：US20080110593A1
公开(公告)日：2008-05-15
申请号：US11978621
申请日：2007-10-30
IPC分类号： F28F7/00
CPC分类号： F01D25/12 , F02C7/16 , F02C7/224 , Y02T50/675
摘要： An aircraft electrical component cooling arrangement comprises at least one electrical component (40) housed in a body (38), for example an engine's electronic controller, characterised in that fuel is passed through the body (38) and directly over the component (40). Advantageously, this maintains a uniform temperature of the electronic components, protection against internal and external fire, ability to further miniaturise electrical components and/or combine units due to enhanced cooling effectiveness over convention air cooled systems.
摘要翻译： 飞机电气部件冷却装置包括容纳在主体（38）中的至少一个电气部件（40），例如发动机的电子控制器，其特征在于，燃料通过所述主体（38）并直接在所述部件（40）上方， 。 有利地，这保持电子部件的均匀温度，防止内部和外部火灾，由于通过常规空气冷却系统的增强的冷却效果，进一步使电气部件和/或组合单元小型化的能力。
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公开(公告)号：US4604031A
公开(公告)日：1986-08-05
申请号：US769702
申请日：1985-08-27
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , Y02T50/673 , Y02T50/676
摘要： Hollow fluid cooled turbine blades of the multi-pass type used in gas turbine engines have suffered from separation of cooling fluid from longitudinally extending walls defining longitudinally extending passages as the cooling fluid is turned through a turning passage from one longitudinally extending passage to an adjacent one. The invention provides an aerodynamically shaped end portion arranged at an angle with respect to the remainder of the wall to increase the turning radius, and a turning vane is positioned in turning passage to form a convergent passage with the end portion of wall. The turning vane has a large turning radius and a large surface area for retention of a boundary layer of cooling fluid thereon. The turning vane directs the cooling fluid flowing through the convergent passage and over the turning vane substantially parallel to the wall to reduce separation in order to reduce pressure losses. The turning vane may be provided with a tail and bleed holes may be provided in the suction sidewall to reduce separation.
摘要翻译： 用于燃气涡轮发动机中的多通式空心流体冷却涡轮机叶片由于冷却流体从限定纵向延伸通道的纵向延伸的壁分离而冷却流体从一个纵向延伸的通道转向相邻的一个转向通道 。 本发明提供了一种空气动力学形状的端部，其相对于壁的其余部分以一定角度布置以增加转弯半径，并且转动叶片定位在转动通道中以与壁的端部部分形成会聚通道。 转动叶片具有大的转弯半径和大的表面积，用于保持其上的冷却流体的边界层。 转向叶片引导冷却流体流过会聚通道并在转动叶片上大致平行于壁，以减少分离，以减少压力损失。 转向叶片可以设置有尾部，并且排出孔可以设置在吸力侧壁中以减少分离。
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公开(公告)号：US4497610A
公开(公告)日：1985-02-05
申请号：US467078
申请日：1983-02-16
摘要： A shroud assembly for a gas turbine engine consists of a housing having a boundary wall and a gas contacting skin, the wall and skin being in segmented form. The skin consists of a thin metal sheet attached to the boundary wall, and a ceramic gas contacting coating. The skin is impingement cooled by cooling air flowing through apertures in the boundary wall, and the cooling air exhausts into the gas flow through passages.The use of a thin metal sheet with a ceramic coating promotes favorable temperature gradients in the skin enabling the coating to run at optimum conditions for maximum cooling effect.
摘要翻译： 用于燃气涡轮发动机的护罩组件由具有边界壁和气体接触皮肤的壳体组成，壁和皮肤处于分段形式。 皮肤由附着在边界壁上的薄金属片和陶瓷气体接触涂层组成。 皮肤被流经边界壁上的孔的冷却空气冲击冷却，冷却空气通过通道排入气体流中。 使用具有陶瓷涂层的薄金属片促进皮肤中有利的温度梯度，使得涂层能够在最佳条件下运行以实现最大的冷却效果。
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公开(公告)号：US4473336A
公开(公告)日：1984-09-25
申请号：US418022
申请日：1982-09-14
CPC分类号： F01D5/14 , B23P15/04 , F01D5/187 , F05D2260/201
摘要： The present invention relates to turbine blades and in particular to turbine blades for use in gas turbine engines. Tensile stresses are introduced into turbine blades when they rotate at high speeds on a turbine rotor. In order to minimize the stresses in an outer skin of an aerofoil of the turbine blade, the outer skin is secured to a platform and an inner core, and in operation a temperature difference is set up between the outer skin and the inner core. The temperature difference produces a thermal compressive stress in the outer skin which opposes the tensile stress produced due to the rotation of the turbine blade. The extremities of the outer skin may be secured to the platform with either a tensile or compressive prestress depending upon the temperature difference between the outer skin and inner core at normal operating conditions. If the operating speed of the gas turbine engine changes, the temperature difference between the outer skin and the inner core may be varied in order to adjust the thermal compressive stress in the outer skin, so that the tensile stress in the outer skin may be opposed, to ensure the stresses in the outer skin are maintained at a minimum during operation of the engine.
摘要翻译： 涡轮叶片技术领域本发明涉及涡轮叶片，特别涉及用于燃气涡轮发动机的涡轮叶片。 当涡轮机转子高速旋转时，拉力应力被引入涡轮叶片。 为了使涡轮机叶片的机翼的外皮中的应力最小化，外皮被固定到平台和内芯，并且在操作中，在外皮和内芯之间建立温度差。 温度差在外表面产生热压缩应力，其与由于涡轮机叶片的旋转产生的拉伸应力相反。 根据外表皮和内芯在正常工作条件下的温差，外皮的四肢可以用拉伸或压缩预应力固定到平台上。 如果燃气涡轮发动机的运转速度发生变化，则为了调整外皮中的热压缩应力，可以改变外皮与内芯之间的温差，使得外皮中的拉伸应力可以相对 ，以确保在发动机操作期间外皮中的应力保持在最小。
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