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AERO-440 Project Due: 28 November 2024 The Boeing 757 is a mid-size, narrow-body commercial passenger airliner, propelled by twin, non-mixing, turbofan engines. The specifications of the engine and the gas properties, respectively, are listed below in Tables 1 & 2. Form a team of not more than 4 students to analyze the on-design operation of this engine. Table 1: Engine specifications PW-2037 Table 2: Gas properties Diffuser adiabatic efficiency 97% Yeold 1.40 Nozzle adiabatic efficiency 99% Cp.cold 10051/(kg-K) Fan polytropic efficiency [er] 0.90 Yhot 1.25 Compressor polytropic efficiency (et.P:) 0.94 phot 14001/(kg-K) Compressor polytropic efficiency (HPC) 0.93 Mechanical efficiency (banc) 0.96 Mechanical efficiency (bc) 0.93 Turbine polytropic efficiency (er) 0.97 0.96 Turbine polytropic efficiency (er) Maximum allowed temperature (TET) Fuel Lower Heating Value (QHV) Combustor pressure loss 1400 K 45 MJ/kg 2% 'https://www.prattwhitney.com/en/products/commercial-engines/pw/2000 1|Page: Develop a computer program for the analysis of the engine. Allow the variation of the bypass ratio B, compressor pressure ratio . Mach number M. Altitude h, and investigate the following: a. Assume a turbojet configuration (B=0). Vary the compressor pressure ratio and plot. 3/mo vs. and TSFC vs. π at various Mach numbers, at an altitude of h = 35000 ft. Find the optimum pressure ratio with respect to 3/mo- b. Use the optimum compressor pressure ratio and investigate the effect of the bypass ratio of the turbofan on [TSFC, 3/mo] at various Mach numbers and at an altitude of h 35000 ft. Find the best bypass ratio with respect to 3/mo. c. Fix all the variables in the program, use the optimum values from sections a & b, plot the net thrust developed by the turbofan engine at various altitudes. d. Write a report that include but not limited to the following items: i. Equations, formulas and assumptions. ii. Computer program. iii. Graphs with proper labels, titles and units. iv. Proper interpretation of each graph. V. Results and conclusions. Grading scheme: 1) Submitting on time: 2) Formatting and neatness: 3) Accuracy: 4) Results, figures, and tables: . 5) Discussion of the results: 6) Assumptions and justifications: 7) Conclusions:

AERO-440 Project Due: 28 November 2024 The Boeing 757 is a mid-size, narrow-body commercial passenger airliner, propelled by twin, non-mixing, turbofan engines. The specifications of the engine and the gas properties, respectively, are listed below in Tables 1 & 2. Form a team of not more than 4 students to analyze the on-design operation of this engine. Table 1: Engine specifications PW-2037 Table 2: Gas properties Diffuser adiabatic efficiency 97% Yeold 1.40 Nozzle adiabatic efficiency 99% Cp.cold 10051/(kg-K) Fan polytropic efficiency [er] 0.90 Yhot 1.25 Compressor polytropic efficiency (et.P:) 0.94 phot 14001/(kg-K) Compressor polytropic efficiency (HPC) 0.93 Mechanical efficiency (banc) 0.96 Mechanical efficiency (bc) 0.93 Turbine polytropic efficiency (er) 0.97 0.96 Turbine polytropic efficiency (er) Maximum allowed temperature (TET) Fuel Lower Heating Value (QHV) Combustor pressure loss 1400 K 45 MJ/kg 2% 'https://www.prattwhitney.com/en/products/commercial-engines/pw/2000 1|Page: Develop a computer program for the analysis of the engine. Allow the variation of the bypass ratio B, compressor pressure ratio . Mach number M. Altitude h, and investigate the following: a. Assume a turbojet configuration (B=0). Vary the compressor pressure ratio and plot. 3/mo vs. and TSFC vs. π at various Mach numbers, at an altitude of h = 35000 ft. Find the optimum pressure ratio with respect to 3/mo- b. Use the optimum compressor pressure ratio and investigate the effect of the bypass ratio of the turbofan on [TSFC, 3/mo] at various Mach numbers and at an altitude of h 35000 ft. Find the best bypass ratio with respect to 3/mo. c. Fix all the variables in the program, use the optimum values from sections a & b, plot the net thrust developed by the turbofan engine at various altitudes. d. Write a report that include but not limited to the following items: i. Equations, formulas and assumptions. ii. Computer program. iii. Graphs with proper labels, titles and units. iv. Proper interpretation of each graph. V. Results and conclusions. Grading scheme: 1) Submitting on time: 2) Formatting and neatness: 3) Accuracy: 4) Results, figures, and tables: . 5) Discussion of the results: 6) Assumptions and justifications: 7) Conclusions:

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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AERO-440 Project Due: 28 November 2024 The Boeing 757 is a mid-size, narrow-body commercial passenger airliner, propelled by twin, non-mixing, turbofan engines. The specifications of the engine and the gas properties, respectively, are listed below in Tables 1 & 2. Form a team of not more than 4 students to analyze the on-design operation of this engine. Table 1: Engine specifications PW-2037 Table 2: Gas properties Diffuser adiabatic efficiency 97% Yeold 1.40 Nozzle adiabatic efficiency 99% Cp.cold 10051/(kg-K) Fan polytropic efficiency [er] 0.90 Yhot 1.25 Compressor polytropic efficiency (et.P:) 0.94 phot 14001/(kg-K) Compressor polytropic efficiency (HPC) 0.93 Mechanical efficiency (banc) 0.96 Mechanical efficiency (bc) 0.93 Turbine polytropic efficiency (er) 0.97 0.96 Turbine polytropic efficiency (er) Maximum allowed temperature (TET) Fuel Lower Heating Value (QHV) Combustor pressure loss 1400 K 45 MJ/kg 2% 'https://www.prattwhitney.com/en/products/commercial-engines/pw/2000 1|Page: Develop a computer program for the analysis of the engine. Allow the variation of the bypass ratio B, compressor pressure ratio . Mach number M. Altitude h, and investigate the following: a. Assume a turbojet configuration (B=0). Vary the compressor pressure ratio and plot. 3/mo vs. and TSFC vs. π at various Mach numbers, at an altitude of h = 35000 ft. Find the optimum pressure ratio with respect to 3/mo- b. Use the optimum compressor pressure ratio and investigate the effect of the bypass ratio of the turbofan on [TSFC, 3/mo] at various Mach numbers and at an altitude of h 35000 ft. Find the best bypass ratio with respect to 3/mo. c. Fix all the variables in the program, use the optimum values from sections a & b, plot the net thrust developed by the turbofan engine at various altitudes. d. Write a report that include but not limited to the following items: i. Equations, formulas and assumptions. ii. Computer program. iii. Graphs with proper labels, titles and units. iv. Proper interpretation of each graph. V. Results and conclusions. Grading scheme: 1) Submitting on time: 2) Formatting and neatness: 3) Accuracy: 4) Results, figures, and tables: . 5) Discussion of the results: 6) Assumptions and justifications: 7) Conclusions:
Transcribed Image Text:AERO-440 Project Due: 28 November 2024 The Boeing 757 is a mid-size, narrow-body commercial passenger airliner, propelled by twin, non-mixing, turbofan engines. The specifications of the engine and the gas properties, respectively, are listed below in Tables 1 & 2. Form a team of not more than 4 students to analyze the on-design operation of this engine. Table 1: Engine specifications PW-2037 Table 2: Gas properties Diffuser adiabatic efficiency 97% Yeold 1.40 Nozzle adiabatic efficiency 99% Cp.cold 10051/(kg-K) Fan polytropic efficiency [er] 0.90 Yhot 1.25 Compressor polytropic efficiency (et.P:) 0.94 phot 14001/(kg-K) Compressor polytropic efficiency (HPC) 0.93 Mechanical efficiency (banc) 0.96 Mechanical efficiency (bc) 0.93 Turbine polytropic efficiency (er) 0.97 0.96 Turbine polytropic efficiency (er) Maximum allowed temperature (TET) Fuel Lower Heating Value (QHV) Combustor pressure loss 1400 K 45 MJ/kg 2% 'https://www.prattwhitney.com/en/products/commercial-engines/pw/2000 1|Page: Develop a computer program for the analysis of the engine. Allow the variation of the bypass ratio B, compressor pressure ratio . Mach number M. Altitude h, and investigate the following: a. Assume a turbojet configuration (B=0). Vary the compressor pressure ratio and plot. 3/mo vs. and TSFC vs. π at various Mach numbers, at an altitude of h = 35000 ft. Find the optimum pressure ratio with respect to 3/mo- b. Use the optimum compressor pressure ratio and investigate the effect of the bypass ratio of the turbofan on [TSFC, 3/mo] at various Mach numbers and at an altitude of h 35000 ft. Find the best bypass ratio with respect to 3/mo. c. Fix all the variables in the program, use the optimum values from sections a & b, plot the net thrust developed by the turbofan engine at various altitudes. d. Write a report that include but not limited to the following items: i. Equations, formulas and assumptions. ii. Computer program. iii. Graphs with proper labels, titles and units. iv. Proper interpretation of each graph. V. Results and conclusions. Grading scheme: 1) Submitting on time: 2) Formatting and neatness: 3) Accuracy: 4) Results, figures, and tables: . 5) Discussion of the results: 6) Assumptions and justifications: 7) Conclusions:
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