The equations of an inviscid blade force component for modeling the flow turning through real blade rows are analytically combined with Euler equations in the meanline annulus of a complete compressor. This combination gives rise to a modified set of unsteady 2D flow equations with specific convective flux and source terms that explicitly depend on the geometry of the blade camberline. At the leading and trailing edges of each bladed region, the new set of equations is coupled to standard Euler equations in unbladed regions by means of boundary conditions that allow modeling of a leading edge shock. The numerical flux difference splitting scheme for time integration of the governing equations includes a consistent, upwind formulation of the delay model for correction of empirical input on loss and deviation at each (either stalled or unstalled) circumferential grid station. The steady 1D solution of the new equations provides the numerical compressor map in normal operation. Several stall configurations can then be obtained by artificially perturbing a near-stall solution assumed as unstable with respect to some well-known stall criteria. The method predicts experimental stalled performance of a transonic rotor with accuracy higher than 4%. The predicted stall inception transients and stall propagation speed are also in line with previous experience.

用于模拟通过实际叶片行的流动的无粘性叶片力分量的方程与完整压缩机的平均线环中的Euler方程解析地组合。这种组合产生了一组经过修改的非定常二维流动方程组，这些方程组具有特定的对流通量和源项，这些方程明确地取决于叶片外倾角的几何形状。在每个叶片区域的前缘和后缘，通过允许对前缘冲击建模的边界条件，新的方程组与未叶片区域中的标准Euler方程耦合。用于控制方程时间积分的数值通量差分裂方案包括一致的，延迟模型的逆风公式，用于校正每个（停顿或未停顿）周向网格站的损耗和偏差的经验输入。新方程的稳定一维解在正常操作中提供了数值压缩器图。然后，可以通过人为地干扰相对于一些众所周知的失速标准被认为是不稳定的近失速解来获得几种失速配置。该方法可预测跨音速转子的实验失速性能，其准确度高于4％。预测的失速开始瞬变和失速传播速度也与以前的经验一致。然后，可以通过人为地干扰相对于一些众所周知的失速标准被认为是不稳定的近失速解来获得几种失速配置。该方法可预测跨音速转子的实验失速性能，其准确度高于4％。预测的失速开始瞬变和失速传播速度也与以前的经验一致。然后，可以通过人为地干扰相对于一些众所周知的失速标准被认为是不稳定的近失速解来获得几种失速配置。该方法可预测跨音速转子的实验失速性能，其准确度高于4％。预测的失速开始瞬变和失速传播速度也与以前的经验一致。