In order to study on cycle design projects with different cycle parameters of turboshaft engine, the engine/components integration design model which includes performance calculation, gas-flow-path size estimation, preliminary aerodynamic design of components and weight estimation is set up. The engine/components coupling design method which combines the engine/components integration design model, coupling design maps of components efficiencies and aerodynamic loadings and turbine cooling flow estimation model is set up. The results show that firstly, low pressure ratio design project, high turbine inlet temperature design project and combined design project with low pressure ratio and high turbine inlet temperature have their own advantages in actual technology level. Secondly, high cycle design projects base on the advancement of technology level. Finally, the engine integration design directions of advanced turboshaft engine will develop towards high cycle design projects and low cycle design projects in the future.