Multirow film cooing is an advanced cooling method to provide large surface cooling for gas turbine components exposed to high temperature. In this paper, the efficiency of multirow film cooling under different configurations is investigated numerically. The geometrical parameters including the hole arrangement, hole orientation and trenched hole are considered. The numerical setup is validated before the cooling performance of different configurations is predicted and analysed. The results showed that the staggered arrangement is not always beneficial to the cooling efficiency. For standard hole, the inline arrangement with opposite compound angles provides the best cooling efficiency. The trenches contribute a lot to the multirow film cooling. For all the configurations investigated, the cooling efficiency of multirow trenched holes is higher than the largest cooling efficiency obtained by standard holes. The configuration of inline compound angle holes with opposite orientation embedded in trenches is the best design throughout all the investigated configurations.