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1.发明申请Turbine Nozzle Segment, Turbine Nozzle, Turbine, and Gas Turbine Engine 审中-公开涡轮喷嘴段，涡轮喷嘴，涡轮机和燃气轮机发动机公开(公告)号：US20070231122A1
公开(公告)日：2007-10-04
申请号：US11587578
申请日：2005-04-13
IPC分类号： F02C7/04
CPC分类号： F01D9/02 , F05D2260/80 , Y02T50/671
摘要： A turbine nozzle segment, a turbine nozzle, a turbine, and a gas turbine engine. The turbine nozzle segment is provided with an outer band 39 of an arc shape, an inner band 41 of an arc shape, a thick stator vane 43 in which an insertion hole 49 to which a probe 47 is insertable from a side of the outer band 39 is formed and on the pressure surface 43b of which an inlet hole 51 communicating with the insertion hole 49 is formed, and a thin stator vane 45 having a suction surface 45a having an identical shape to a suction surface 43a of the thick stator vane 43 and a smooth pressure surface 45b approximating to a pressure surface 43b of the thick stator vane 43 configured to be thinner than the thick stator vane.
摘要翻译： 涡轮喷嘴段，涡轮喷嘴，涡轮机和燃气涡轮发动机。 涡轮喷嘴段设置有弧形外带39，弧形内带41，厚定子叶片43，其中探针47可从外带的一侧插入到其中的插入孔49 39形成，并且在压力表面43b上形成有与插入孔49连通的入口孔51，以及具有吸力表面45a的薄定子叶片45，其具有与厚度的吸入表面43a相同的形状 定子叶片43和平滑的压力表面45b，其接近构造成比厚定子叶片薄的厚定子叶片43的压力表面43b。
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公开(公告)号：US20070258810A1
公开(公告)日：2007-11-08
申请号：US11570325
申请日：2005-09-22
IPC分类号： F02C7/04
CPC分类号： F01D5/143 , F05D2250/70 , F05D2250/71 , F05D2270/17 , Y02T50/671 , Y02T50/673
摘要： A wall configuration of an axial-flow machine which can reduce the secondary flow loss is provided. A trough is formed between a blade and another blade in the blade row and extends in at least an axial direction of the blade row. The region where the trough is formed is axially between a leading edge and a trailing edge of the blade. A center line of the trough has a curvature in the same direction as a camber line of the blade. A maximum amplitude of the trough is located adjacent to an axial center of the blade or located axially between the axial center and the leading edge of the blade.
摘要翻译： 提供了可以减少二次流动损失的轴流式机器的壁结构。 叶片与刀片列中的另一个叶片之间形成槽，并在叶片排的至少一个轴向方向上延伸。 槽形成的区域轴向位于叶片的前缘和后缘之间。 槽的中心线具有与叶片的弧线相同方向的曲率。 槽的最大幅度位于叶片的轴向中心附近，或者位于叶片的轴向中心和前缘之间的轴向。
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公开(公告)号：US08235661B2
公开(公告)日：2012-08-07
申请号：US12520562
申请日：2007-12-19
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/145 , F01D7/00 , F01D9/041 , F04D29/023 , F04D29/324 , F05D2300/50212 , F05D2300/505 , Y02T50/67 , Y02T50/673 , Y10S415/914
摘要： The present invention provides a turbine blade that is exposed to a high temperature atmosphere at relatively high temperatures and to a low temperature atmosphere at relatively low temperatures, including: a concave-curve-like pressure surface that is concaved along a flow direction of fluid; a convex-curve-like suction surface that is convexed along the flow direction of the fluid; and a concave and convex formation device which causes a concave and convex portion along the flow of the fluid to appear on the suction surface when the turbine blade is exposed to the low temperature atmosphere, and which turns the suction surface into a smooth surface along a convex curve surface of the suction surface when the turbine blade is exposed to the high temperature atmosphere. With this construction, it is possible to reduce a pressure loss of the turbine blade at high Reynolds numbers in the low temperature atmosphere without increasing a pressure loss of the turbine blade at low Reynolds numbers in the high temperature atmosphere.
摘要翻译： 本发明提供一种涡轮叶片，其在比较高的温度下暴露在高温气氛中，在相对较低的温度下暴露于低温气氛，包括：沿流体流动方向凹陷的凹曲面状的压力表面; 沿着流体的流动方向凸起的凸曲线状吸引表面; 以及凹凸形成装置，当涡轮叶片暴露于低温气氛时，使得沿着流体流动的凹凸部分出现在吸入表面上，并且将吸入表面沿着 当涡轮叶片暴露于高温气氛时，吸力表面的凸曲面。 利用这种结构，可以在高温大气中以较低的雷诺数增加涡轮叶片的压力损失，从而在低温大气中降低涡轮叶片的高的雷诺数的压力损失。
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公开(公告)号：US07690890B2
公开(公告)日：2010-04-06
申请号：US11570325
申请日：2005-09-22
IPC分类号： F01D9/02
CPC分类号： F01D5/143 , F05D2250/70 , F05D2250/71 , F05D2270/17 , Y02T50/671 , Y02T50/673
摘要： A wall configuration of an axial-flow machine which can reduce the secondary flow loss is provided. A trough is formed between a blade and another blade in the blade row and extends in at least an axial direction of the blade row. The region where the trough is formed is axially between a leading edge and a trailing edge of the blade. A center line of the trough has a curvature in the same direction as a camber line of the blade. A maximum amplitude of the trough is located adjacent to an axial center of the blade or located axially between the axial center and the leading edge of the blade.
摘要翻译： 提供了可以减少二次流动损失的轴流式机器的壁结构。 叶片与刀片列中的另一个叶片之间形成槽，并在叶片排的至少一个轴向方向上延伸。 槽形成的区域轴向位于叶片的前缘和后缘之间。 槽的中心线具有与叶片的弧线相同方向的曲率。 槽的最大幅度位于叶片的轴向中心附近，或者位于叶片的轴向中心和前缘之间的轴向。
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公开(公告)号：US20100014983A1
公开(公告)日：2010-01-21
申请号：US12520562
申请日：2007-12-19
CPC分类号： F01D5/147 , F01D5/145 , F01D7/00 , F01D9/041 , F04D29/023 , F04D29/324 , F05D2300/50212 , F05D2300/505 , Y02T50/67 , Y02T50/673 , Y10S415/914
摘要： The present invention provides a turbine blade that is exposed to a high temperature atmosphere at relatively high temperatures and to a low temperature atmosphere at relatively low temperatures, including: a concave-curve-like pressure surface that is concaved along a flow direction of fluid; a convex-curve-like suction surface that is convexed along the flow direction of the fluid; and a concave and convex formation device which causes a concave and convex portion along the flow of the fluid to appear on the suction surface when the turbine blade is exposed to the low temperature atmosphere, and which turns the suction surface into a smooth surface along a convex curve surface of the suction surface when the turbine blade is exposed to the high temperature atmosphere. With this construction, it is possible to reduce a pressure loss of the turbine blade at high Reynolds numbers in the low temperature atmosphere without increasing a pressure loss of the turbine blade at low Reynolds numbers in the high temperature atmosphere.
摘要翻译： 本发明提供一种涡轮叶片，其在比较高的温度下暴露在高温气氛中，在相对较低的温度下暴露于低温气氛，包括：沿流体流动方向凹陷的凹曲面状的压力表面; 沿着流体的流动方向凸起的凸曲线状吸引表面; 以及凹凸形成装置，当涡轮叶片暴露于低温气氛时，使得沿着流体流动的凹凸部分出现在吸入表面上，并且将吸入表面沿着 当涡轮叶片暴露于高温气氛时，吸力表面的凸曲面。 利用这种结构，可以在高温大气中以较低的雷诺数增加涡轮叶片的压力损失，从而在低温大气中降低涡轮叶片的高的雷诺数的压力损失。
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公开(公告)号：US20090136354A1
公开(公告)日：2009-05-28
申请号：US12297256
申请日：2007-04-06
IPC分类号： B64C27/46
CPC分类号： F04D29/324 , F01D5/145 , F04D29/681 , F05D2240/121 , F05D2240/127 , F05D2240/303 , Y02T50/673 , Y10S415/914
摘要： A blade surrounded by: a leading edge portion, which is where fluid flows in; a pressure surface which is a concave curve shape concaved along a direction the fluid flows; a suction surface which is a convex curve shape convexed along a direction the fluid flows; and a trailing edge portion, which is where the fluid flows out, in which a disturbance addition portion is provided on the suction surface closer to the leading edge portion than a maximum velocity point, where the flow velocity of the fluid is maximized on the suction surface, for disturbing a laminar flow on the suction surface and for transitioning to a turbulent flow.
摘要翻译： 叶片包围：流体流入的前缘部分; 沿着流体流动方向凹陷的凹曲面形状的压力面; 沿着流体流动方向凸出的凸曲线形状的吸附面; 以及流体流出的后缘部，其中在比最大速度点更靠近前缘部分的吸入面上设置有扰动加法部，其中流体的流速在吸力上最大化 表面，用于扰动吸入表面上的层流并转变成湍流。
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公开(公告)号：US08118560B2
公开(公告)日：2012-02-21
申请号：US12297256
申请日：2007-04-06
CPC分类号： F04D29/324 , F01D5/145 , F04D29/681 , F05D2240/121 , F05D2240/127 , F05D2240/303 , Y02T50/673 , Y10S415/914
摘要： A blade surrounded by: a leading edge portion, which is where fluid flows in; a pressure surface which is a concave curve shape concaved along a direction the fluid flows; a suction surface which is a convex curve shape convexed along a direction the fluid flows; and a trailing edge portion, which is where the fluid flows out, in which a disturbance addition portion is provided on the suction surface closer to the leading edge portion than a maximum velocity point, where the flow velocity of the fluid is maximized on the suction surface, for disturbing a laminar flow on the suction surface and for transitioning to a turbulent flow.
摘要翻译： 叶片包围：流体流入的前缘部分; 沿着流体流动方向凹陷的凹曲面形状的压力面; 沿着流体流动方向凸出的凸曲线形状的吸附面; 以及流体流出的后缘部，其中在比最大速度点更靠近前缘部分的吸入面上设置有扰动加法部，其中流体的流速在吸力上最大化 表面，用于扰动吸入表面上的层流并转变成湍流。
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