This article is an open access article distributed under the terms and conditions of the Creative... more This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY
This article is an open access article distributed under the terms and conditions of the Creative... more This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY
/ International Journal of Research Publications (IJRP.ORG), 2018
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1....
International Journal of Advance Engineering and Research Development, 2018
This paper present the optimum operation of the Micro Gas Turbine Engine that is minimum specific... more This paper present the optimum operation of the Micro Gas Turbine Engine that is minimum specific fuel consumption and maximum specific thrust. In the turbojet engine, the main operating variables are: compressor pressure ratio and turbine inlet temperature. These variables affect the specific thrust and specific fuel consumption (SFC), which represent the main performance parameters. The analytical results show that the specific thrust and specific fuel consumption strongly depend on TIT and compressor pressure ratio (Pr). From the variation of TIT and Pr, the results show that the optimum running line (ORL) give while the engine is running at optimum (TIT) and (Pr) for higher performance.
/ International Journal of Research Publications (IJRP.ORG), 2018
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1.2-1.9 and 5-8. After that optimum line was investigated that connects the points of maximum Fs and optimum SFC in these ranges that shows optimum engine performance.
IJAAA (Interantional Jouranl of Aviation, Aeronautics and Aerospace), 2018
This paper presents a reliable and robust optimization for minimum drag of an aircraft at the con... more This paper presents a reliable and robust optimization for minimum drag of an aircraft at the conceptual design phase. Firstly, the conceptual design code was developed and existing Single Seat Aerobatic (SSA) aircraft was chosen to validate the reliability of developed code. The resulted data from the developed code showed good agreement with the existing data. Secondly, Sequential Quadratic Programming (SQP) optimizer was created and employed as a tool to explore possible aircraft configurations that are more efficient and less costly than an existing design. The optimized results gave lower Drag and better performance.
This article is an open access article distributed under the terms and conditions of the Creative... more This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY
This article is an open access article distributed under the terms and conditions of the Creative... more This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY
/ International Journal of Research Publications (IJRP.ORG), 2018
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1....
International Journal of Advance Engineering and Research Development, 2018
This paper present the optimum operation of the Micro Gas Turbine Engine that is minimum specific... more This paper present the optimum operation of the Micro Gas Turbine Engine that is minimum specific fuel consumption and maximum specific thrust. In the turbojet engine, the main operating variables are: compressor pressure ratio and turbine inlet temperature. These variables affect the specific thrust and specific fuel consumption (SFC), which represent the main performance parameters. The analytical results show that the specific thrust and specific fuel consumption strongly depend on TIT and compressor pressure ratio (Pr). From the variation of TIT and Pr, the results show that the optimum running line (ORL) give while the engine is running at optimum (TIT) and (Pr) for higher performance.
/ International Journal of Research Publications (IJRP.ORG), 2018
Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1.2-1.9 and 5-8. After that optimum line was investigated that connects the points of maximum Fs and optimum SFC in these ranges that shows optimum engine performance.
IJAAA (Interantional Jouranl of Aviation, Aeronautics and Aerospace), 2018
This paper presents a reliable and robust optimization for minimum drag of an aircraft at the con... more This paper presents a reliable and robust optimization for minimum drag of an aircraft at the conceptual design phase. Firstly, the conceptual design code was developed and existing Single Seat Aerobatic (SSA) aircraft was chosen to validate the reliability of developed code. The resulted data from the developed code showed good agreement with the existing data. Secondly, Sequential Quadratic Programming (SQP) optimizer was created and employed as a tool to explore possible aircraft configurations that are more efficient and less costly than an existing design. The optimized results gave lower Drag and better performance.
Uploads
Papers by Zin Win Thu