Numerical analysis of 3D temperature field of an impingement-effusion cooled flame tube floating tile;

Numerical simulations of flame tube cooling structure with multi-jet holes;

A computational procedure is developed for numerical simulation of three-dimensional two-phase reacting flow fields on a gas turbine annular combustor including the diffuser,dual-stage swirler,flame tube,and cooling passages.

For crack failure occurred in the combustor liner of an aeroengine,several aspects are investigated,including statistical and sample analysis for full-scale combustor liner,and microstructure observation and crack analysis by use of optical and electron microscope.

The velocity field inside the combustor liner is measured with two-dimensional particle image velocimetry.

In this paper, the body-fitted grids of the combustor with the swirl cup are generated by an elliptical grid generation technique.

The combustor of gas turbine engine operates under inhomogeneous high temperature, which causes very complicated mechanical behavior of combustor s material, and makes combustor failure.

In accordance with some failures of an aeroengine machining liner in operation such as cracks and loss,the analysis and research are completed from structure, materials and argon arc welding repairing process,and the cold and hot fatigue,stress and hot stretch tests are also conducted.