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    • 41. 发明申请
    • COOLED AIRFOIL IN A TURBINE ENGINE
    • 涡轮发动机冷却空气
    • US20120269647A1
    • 2012-10-25
    • US13090294
    • 2011-04-20
    • Paul H. VittDavid A. KempChing-Pang LeeJohn J. Marra
    • Paul H. VittDavid A. KempChing-Pang LeeJohn J. Marra
    • F01D5/18
    • F01D5/186F01D5/188F05D2250/30F05D2260/221F05D2260/941
    • An airfoil in a gas turbine engine includes an outer wall and an inner wall. The outer wall includes a leading edge, a trailing edge opposed from the leading edge in a chordal direction, a pressure side, and a suction side. The inner wall is coupled to the outer wall at a single chordal location and includes portions spaced from the pressure and suction sides of the outer wall so as to form first and second gaps between the inner wall and the respective pressure and suction sides. The inner wall defines a chamber therein and includes openings that provide fluid communication between the respective gaps and the chamber. The gaps receive cooling fluid that provides cooling to the outer wall as it flows through the gaps. The cooling fluid, after traversing at least substantial portions of the gaps, passes into the chamber through the openings in the inner wall.
    • 燃气涡轮发动机中的翼型件包括外壁和内壁。 外壁包括前缘,从前缘朝向方向相对的后缘,压力侧和吸力侧。 内壁在单个弦位置处联接到外壁,并且包括与外壁的压力和吸力侧隔开的部分,以便在内壁和相应的压力和吸力侧之间形成第一和第二间隙。 内壁在其中限定一个室,并且包括在相应间隙和室之间提供流体连通的开口。 间隙接收冷却流体,当其流过间隙时,向外壁提供冷却。 冷却流体在穿过至少大部分间隙之后通过内壁中的开口进入腔室。
    • 43. 发明申请
    • NEAR-WALL SERPENTINE COOLED TURBINE AIRFOIL
    • 近壁式冷却涡轮机
    • US20120014808A1
    • 2012-01-19
    • US12836060
    • 2010-07-14
    • Ching-Pang Lee
    • Ching-Pang Lee
    • F01D5/18
    • F01D25/12F01D5/187F05D2250/185F05D2260/202F05D2260/22141
    • A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.
    • 由涡轮机翼(20A)的压力侧和吸力侧壁(22,24)之间的空腔(49)中的内壁(50,52)形成的蛇形冷却剂流动路径(54A-54G)。 冷却剂流(58)进入(56)翼型件的端部,流入跨度通道(54A),然后在压力侧壁的内表面上向前(54B)流动,然后在前缘 26),并且沿吸力侧壁的前部流回,然后围绕内壁(52)向前和向后循环(54E),然后沿着吸力侧壁的中间部分流动,然后流入 在压力侧和吸力侧壁之间的后通道(54G),然后离开后缘(28)。 这提供了与翼型件的加热形状相匹配的冷却,最小化差异热膨胀,恢复冷却剂,并最小化所需的流量。
    • 47. 发明申请
    • Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall
    • 翼型端壁边界层等离子体诱导流量控制
    • US20110150653A1
    • 2011-06-23
    • US12640242
    • 2009-12-17
    • Matthew D. MontgomeryChing-Pang LeeChander Prakash
    • Matthew D. MontgomeryChing-Pang LeeChander Prakash
    • F01D5/14F01D9/02
    • F01D5/145F05D2270/172Y02T50/67Y02T50/673
    • Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.
    • 翼型件(22)的端壁(25)中的等离子体发生器(48,49,70,71)在方向(50)上引起空气动力学流动,所述方向(50)将端壁边界层的流线(47)改变为流线几何形状(46) 翼型的跨跨区域。 这减少了由边界层的动量缺失产生的旋涡(42),从而提高了空气动力学效率。 等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件(22)之间排列,并且可以位于由端壁的表面轮廓(66)引起的流线中的校正点(68)处。 等离子体发生器可以被定向以产生与边界层流向量(72)组合的流向量(74),以在减少湍流的方向上产生合成流向量(76)。