Aero Elastic Analysis of a Transonic Fan Blade with Different Mach Numbers

Abstract

In aircraft engine design (and in other applications), small improvements in turbine efficiency may be significant. Since analytical tools for predicting transonic turbine losses are still being developed, experimental efforts are required to evaluate various designs, calibrate design methods, and validate CFD analysis tools. However, these experimental efforts must be very accurate to measure the performance differences to the levels required by the highly competitive aircraft engine market. Due to the sensitivity of transonic and supersonic flow fields, it is often difficult to obtain the desired level of accuracy.

In this thesis, the development of high-performance turbine airfoils is investigated under the supersonic condition. Transonic turbine airfoil is designed and modeled in 3D modeling software Catia. CFD analysis is done by considering k-ε turbulence model at different velocities of air to verify the aerodynamic performance of turbine airfoil. The velocities of air are varied by changing the Mach number 0.8, 0.9, 1, 1.1 and 1.2. Analysis is done in Ansys.