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Effect of aging and manufacturing tolerances on multi-stage transonic axial compressor performance

机译：老化和制造公差对多级跨音速轴向压缩机性能的影响

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The Axial compressor is an integrated part of a gas turbine. The central part of compressors is its blades. Blade aerodynamic has a significant effect on compressor performance. Because of the adverse pressure gradient in the compressor, any deviation in the blade profile has a significant influence on the flow field as well as the compressor performance. During the manufacturing and operation of a compressor, the blade profile may deviate from the nominal design. This deviation may happen within the manufacturing process, e.g., changing in stagger angle of the blade, changing in the maximum thickness of the blade profile or may occur in an operation process, e.g., increasing the blade surface roughness. By the way, these deviations affect the compressor performance. In this research, a numerical investigation is carried out to understand better the effects of geometry variability of the blades, including maximum thickness, blade surface roughness, and rotor blades stagger angle on the Transonic Axial compressor performance parameters, including the efficiency and pressure ratio. A CFD code, which solves the Reynolds-averaged Navier–Stokes equations, is employed to simulate the complicated 3D flow field of the axial compressor. The code is validated against experimental data for the axial compressor. The numerical result is in good agreement with the test dataand error at the design point for the efficiency was computed to be 0.3%, which shows high accuracy of the numerical method. Then, the effect of geometry variability on the axial compressor blade performance parameters is studied. Results show that increase in the surface roughness, blade thickness, and the rotor blades twist lowers the efficiency, pressure ratio and mass flow significantly in the compressor. Results show with a 10% increase of the blade installation angle at the design point, the mass flow rate decreases 1.93%, and the efficiency and pressure ratio decreases 0.35% and 1.8%, respectively. The blade surface roughness reduces the mass flow rate, total pressure ratio and efficiency of the compressor. The results show that imposing the roughness at the design point of the compressor, mass flow rate and efficiency is reduced 1.8% and 2.75 %, respectively. Meridional view of this compressor is shown in figure 1 in which the blade profiles for the first to fourth stages are DCA type [1].
机译：轴向压缩机是燃气轮机的组成部分。压缩机的中心部分是叶片。叶片的空气动力学性能对压缩机性能有重要影响。由于压缩机中不利的压力梯度，叶片轮廓的任何偏差都会对流场以及压缩机性能产生重大影响。在压缩机的制造和运行期间，叶片轮廓可能会偏离标称设计。该偏差可能在制造过程中发生，例如，叶片的交错角改变，叶片轮廓的最大厚度的改变，或者可能在操作过程中发生，例如，增加叶片的表面粗糙度。顺便说一下，这些偏差会影响压缩机的性能。在这项研究中，进行了数值研究，以更好地理解叶片的几何可变性（包括最大厚度，叶片表面粗糙度和转子叶片错位角）对跨音速轴向压缩机性能参数（包括效率和压力比）的影响。使用CFD代码求解雷诺平均Navier-Stokes方程，以模拟轴向压缩机的复杂3D流场。该代码已针对轴向压缩机的实验数据进行了验证。数值结果与试验数据吻合良好，设计时的误差为0.3％，表明该方法具有较高的精度。然后，研究了几何可变性对轴向压缩机叶片性能参数的影响。结果表明，表面粗糙度，叶片厚度增加以及转子叶片扭曲会明显降低压缩机的效率，压力比和质量流量。结果表明，在设计点叶片安装角度增加10％时，质量流率降低1.93％，效率和压力比分别降低0.35％和1.8％。叶片表面粗糙度会降低质量流量，总压比和压缩机效率。结果表明，在压缩机的设计点施加粗糙度，质量流量和效率分别降低了1.8％和2.75％。该压缩机的子午线视图如图1所示，其中第一至第四级的叶片轮廓为DCA类型[1]。

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