Abstract: A method has been developed for calculation of three-dimensional flows in aeroengine combustor including diffuser and flametube,inner and outer annuluses.The 3D body-fitting grid has been generated to deal with the complex geometry of the combustor.The non-staged grid scheme and k-ε turbulence model has been adopted.The mass flowing thought primary holes,dilution holes and film cooling holes has been calculated.The calculated results are consistent reasonably with the experimental measurements.