Throughflow model for design and analysis integrated in a three-dimensional Navier-Stokes solver

Throughflow model for design and analysis integrated in a three-dimensional Navier-Stokes solver
复制标题

DOI:
10.1243/0957650991537608
复制
发表时间:
1999-06
期刊:
Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy
影响因子:
--
通讯作者:
A. Sturmayr;C. Hirsch
A. Sturmayr;C. Hirsch
中科院分区:
其他
文献类型:
--
作者:
A. Sturmayr;C. Hirsch

文献摘要

被引文献

相似文献

摘要本文将多块多重网格Navier-Stokes方程的求解方法扩展到包括通流模型,用于涡轮机的设计和分析。无粘轴对称流中叶片的存在以经典方式建模,通过分布式叶片力产生所需的转向,阻塞因子,占由于叶片厚度而减少的面积,以及分布式摩擦力表示由于粘性应力和热传导而导致的熵增加。不需要精确的刀片几何形状。通流模块可使用三维代码的所有功能,包括物理流体模型、边界条件、空间和时间离散化、收敛加速技术和数据可视化。这包括处理相关马赫数的整个范围的能力,从严格不可压缩(通过预处理技术)到超音速,以及在任何配置中的任何数量的叶片排,包括,例如,旁路发动机。选定的元素,包括通流模型进行了讨论,特别强调的叶片力及其离散化。分析和设计模式的冲击和相关的损失的属性进行了研究。该方法在跨音速压气机转子和四级低速涡轮机上进行了验证。
Abstract A multiblock multigrid Navier-Stokes solver has been extended to include a throughflow model for the design and analysis of turbomachines. The presence of the blades in the inviscid axisymmetric flow is modelled in the classical way through a distributed blade force to produce the desired turning, a blockage factor that accounts for the reduced area due to blade thickness, and a distributed frictional force representing the entropy increase due to viscous stresses and heat conduction. The exact blade geometry is not required. All features of the three-dimensional code concerning the physical fluid model, boundary conditions, spatial and time discretization, convergence acceleration techniques and data visualization are available to the throughflow module. This includes the capability to treat the entire range of relevant Mach numbers, from strictly incompressible (through a preconditioning technique) to supersonic, as well as any number of blade rows in any configuration, including, for example, bypass engines. Selected elements comprising the throughflow model are discussed, with special emphasis on the blade force and its discretization. The properties of analysis and design mode with respect to shocks and the associated losses are investigated. The methodology is demonstrated on a transonic compressor rotor and a four-stage low-speed turbine.