Abstract: Based on the parameter matching technology, a gas turbine performance estimation method is developed which has the advantage that no component characteristic maps are required. Influence coefficient matrix for gas turbine engines by using gas path measurements is introduced and the performance parameters which cannot be directly measured is optimized by using the genetic algorithm and sequential unconstrained minimization technique. The developed method is applied to the performance estimation of a gas turbine running at different altitudes and Mach numbers with and without degradation by using simulated gas path measurements to test the effectiveness of the method. Taking the high bypass ratio turbofan engine as an example, the results of the investigation indicate that the model proposed in the paper are in good agreements with the simulated data, and the relative error is less than 4.5%, which shows that the performance estimation model is correct, and the method can be applied to the performance estimation of different types of gas turbine engines.