Optimization of High-Bypass Turbofan High-Pressure Compressor Blade – A Case Study

Authors

Adeel Khalid, Kennesaw State UniversityFollow
Vlad Mandzyuk, Kennesaw State UniversityFollow

Name of Faculty Sponsor

Adeel Khalid

Faculty Sponsor Email

akhalid2@kennesaw.edu

Author Bio(s)

Vlad Mandzyuk was a Mechanical Engineering student at Kennesaw State University where he also studied aerospace engineering. Vlad was a part of many clubs and organizations at Kennesaw. The most notable included being a member of the aerial robotics competition team where he helped the team design aircraft for competitions. In addition, he was a member of the AIAA and ASME professional organizations. Vlad also conducted research on optimizing high-pressure compressor blades of a gas turbine engine. Both of his senior-design capstones involved company sponsored projects where he successfully met each company's requirements. He is currently pursuing a career in aerospace.

Publication Date

2024

Abstract

This research determines the relationship between the High-Pressure Compressor (HPC) rotor blade design variables and compressor pressure ratio of a high bypass turbofan engine. Alterations in the HPC blades span, chord, taper, twist, number, and angle of incidence are performed and their effect on the HPC pressure ratio is observed. The objective is to determine key parameters that could maximize the performance of a high-pressure compressor for a given mission. Physics-based modeling, Computational Fluid Dynamics (CFD), and wind-tunnel testing are performed to compare and validate findings. Physics-based modeling is performed to serve as the benchmark for data obtained through other methods. CFD analysis replicates wind-tunnel testing within a computer setting. In this experiment, the first stage of the high-pressure compressor is designed and simulated. Upon the completion of these experiments, wind-tunnel testing is conducted to validate results. Data is compared in the form of graphs relating the stage pressure ratio of the HPC to the corresponding blade design variable. The objective of this study is to optimize the design of the HPC using the discovered design variables related to the maximum pressure ratios to maximize the engine performance. This will result in lower operating costs, longer range, and lower emissions. When implemented, the engine optimized for the specific mission could save the aircraft manufacturer and operators the initial and operating expenses. Additionally, solutions to the following questions are explored. Do the use of CAD (Computer Aided Design) and CFD models provide a feasible solution for gas turbine engine optimization? Do the results obtained from CFD analyses show the same level of improvement in engine performance as obtained by physics-based models? This study is a comparative analysis between the different blade design variables and will compare the level of accuracy between each experiment.