Generation of the grid for blade passages with packaging using universal grid generators usually takes much time. The paper is devoted to grid generation in turbo machine blade passages with packaging in automatic mode. The main requirement to the approach is to obtain the grid with minimum engineer participant. In the developed procedure engineer must specify only general input data: number of nodes, cell size near solid bodies and geometrical data. Multiblock structured grids are considered. All grid blocks have node-to-node attachment between each other; periodicity is also specified from node to node. The grid in blade passage consists of two blocks: “O” grid around blade and “H” grid in blade passage. Additional blocks are used to describe different ZR-effects such us tip clearances, leakage seals and bleed air systems. A variational method of constructing three dimensional grids composed of hexahedral cells is applied. The combination of the energy density functional and cell size functional is used. The first functional lets us control the shapes and the second functional lets us control the sizes of grid cells. Grid untangling procedure is also developed. Developed approach was tested using the blades of axial and centrifugal compressors and axial turbines. Results of grid generation are presented.

The paper is pointed to the problem of numerical simulation of unsteady flow around an oscillating blade in jet engine compressor. Single compressor rotor blade row is considered. It is assumed that mode shape and frequency of blade oscillation is not influenced by airflow. The system of governing equations is transformed to a moving coordinate system to describe blade oscillations. Multi-block structured “H-O” grid is used for spatial discretization. Inner boundary of “O”-grid (representing blade airfoil surface) is moved to describe blade airfoil oscillation. To minimize discretization error, special morphing procedure was developed for “O”-grid to accommodate blade airfoil surface motion. Other grid blocks remain steady. Nonlinear harmonic method is applied to integrate Euler equations on time variable. For spatial derivation Dispersion-Relation-Preserving methodology is applied. To maintain solution accuracy nonreflecting boundary conditions are implemented on artificial boundaries (inlet and outlet). Resulting system of nonlinear algebraic equations is resolved numerically. As an alternative, time-marching method is realized in ANSYS CFX by means of user routines. Numerical and experimental cascade results are compared.

No abstract

The study of processes occurring in gas turbine combustor is an important part of engine design for achieving the required technical, operational, and environmental characteristics of the engine. During engine design process, both experimental and computational methods are used. The progress in numerical methods of modeling fourdimensional (space and time) physical phenomena and increasing of computation capacity allow application of complex computational fluid dynamics (CFD) methods for simulating such technical devices as the gas turbine combustor.

No abstract