多级轴流压气机全工况性能计算

Calculation of the Overall Aerodynamic Performance ofMultl-Stage Axial-Flow Compressor

运用三维粘性流动计算软件Fine/Numeca对某重型燃气轮机多级轴流压气机的前5排叶列进行了全工况下的数值联算,重点分析了设计转速下可调导叶角度的变化,以及可调导叶处于设计角度时转速的变化对压气机特性的影响。计算中采用Jameson的中心差分格式使用全局时间推进方法求解N S方程和Spalart Allmaras一方程湍流模型。结果表明,这套方法能比较准确地反映压气机在各种工况下的性能,同样适用于后续阶段的整机联算。

The internal flow field of a heavy gas turbine's multi-stage axial-flow compressor was simulated with Fine/Numeca, a 3-D viscous flow commercial software. As a prior study of the project, only five blade rows were calculated, including inlet guide vane and first two stages. Analysis of the relationship between the compressor performance and the changes of the adjustable guide vane's angle and the rotational speed has been done. In order to resolve the Navier-Stokes equations and Spalart-Allmaras one-equation turbulence model, the central difference scheme by Jameson and local time stepping method were employed. This set of method works well to simulate the compressor performance in the overall working conditions and is feasible as well for the subsequent multi-stage computation of the whole compressor.