论文部分内容阅读
根据选定的船用设计点参数(G、n、Pa、T_a)和顶切尺寸F/F_I值,我们可以按照下述步骤求出顶切风扇级通流部分尺寸[9]: 1.根据航空风扇级(照例还应包括外函道喷口及低压其余级的影响)各叶列沿径向的详细的气动计算或实验结果,求出在航空设计点参数下,风扇级内外函分界面流线位置(图13),并计算出以各列叶栅进口动压头为权函数的风扇级内函部分加权平均的通流面积F_o值。 2.修正叶顶端部壁面影响,估计顶切尺寸(面积)F_I。这里可以采取两种方法:一是按文献[4],[5]推荐的估计端部壁面附面层位移厚度δ的方法,修正轴向位置不同的影响,就可以求出沿通流部分各叶列的附面层厚度δ,从而得出顶切尺寸I[3]。另一种方法,如图14所示,是
According to the selected design parameters of the ship (G, n, Pa, T_a) and the top cut size F / F_I, we can get the size of the through-flow section of the top cut fan stage according to the following steps: Fan-level (as a rule, should also include the outer channel spout and the impact of the rest of the low-pressure) each leaf column radial detailed aerodynamic calculations or experimental results obtained at the aviation design point parameters, the fan-level internal and external communication flow lines (Figure 13), and calculate the value of the flow area F_o, which is weighted average of the fan-like internal part of the cascade inlet with the dynamic pressure head of each cascade inlet. 2. Corrected the effect of the tip of the tip of the wall, estimated top cut size (area) F_I. There are two ways to do this: First, according to the method of estimating the thickness δ of the boundary wall displacement as recommended in [4], [5], by correcting the influence of different axial positions, Leaf column surface thickness of δ, resulting in top cut size I [3]. Another method, shown in Figure 14, is