Project Title

Performance Improvement of High Bypass Turbofan Engine Through Optimization of High-Pressure Compressor Blade - A Case Study

Presenters

Vlad MandzyukFollow

Academic department under which the project should be listed

SPCEET - Mechanical Engineering

Faculty Sponsor Name

Adeel Khalid

Disciplines

Propulsion and Power

Abstract (300 words maximum)

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 engine's performance is observed. The objective is to determine key parameters that could maximize the performance of a gas turbine engine for a given mission. The metrics used to compare engine performance include thrust, thrust specific fuel consumption, and overall efficiency. Parametric cycle analysis (PCA), computational fluid dynamics (CFD), and wind-tunnel testing are performed to compare and validate findings. PCA is a physics-based method performed mathematically to serve as the benchmark for data obtained through the other methods. The CFD method replicated wind-tunnel testing within a computer setting. In this experiment, the first stage of the high-pressure compressor was designed and simulated. Upon the completion of these experiments, wind-tunnel testing will be conducted to confirm results. Data will be compared in the form of graphs relating the stage pressure ratio of the HPC to the corresponding blade design variable. The goal 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, answers to the following questions will be determined. 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?

Project Type

Oral Presentation (15-min time slots)

How will this be presented?

Yes, synchronously via Teams

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Performance Improvement of High Bypass Turbofan Engine Through Optimization of High-Pressure Compressor Blade - A Case Study

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 engine's performance is observed. The objective is to determine key parameters that could maximize the performance of a gas turbine engine for a given mission. The metrics used to compare engine performance include thrust, thrust specific fuel consumption, and overall efficiency. Parametric cycle analysis (PCA), computational fluid dynamics (CFD), and wind-tunnel testing are performed to compare and validate findings. PCA is a physics-based method performed mathematically to serve as the benchmark for data obtained through the other methods. The CFD method replicated wind-tunnel testing within a computer setting. In this experiment, the first stage of the high-pressure compressor was designed and simulated. Upon the completion of these experiments, wind-tunnel testing will be conducted to confirm results. Data will be compared in the form of graphs relating the stage pressure ratio of the HPC to the corresponding blade design variable. The goal 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, answers to the following questions will be determined. 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?

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