solve by using Matlab ON-DESIGN ANALYSIS OF A TURBOFAN 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 engines¹. 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% Ycoid 1.40 Nozzle adiabatic efficiency 99% Cp.cold 1005 J/(kg-K) 1.25 Fan polytropic efficiency (er) 0.90 Yhot Compressor polytropic efficiency (e.Pc) 0.94 Cphot 1400 J/(kg-K) Compressor polytropic efficiency (ePC) 0.931 Mechanical efficiency (h) 0.96 Mechanical efficiency (haic) 0.93 Turbine polytropic efficiency (err) 0.97 Turbine polytropic efficiency (err) Maximum allowed temperature (TET) Fuel Lower Heating Value (Qav) Combustor pressure loss 45 MJ/kg 2% 0.96 1400 K https://www.prattwhitney.com/en/products/commercial-engines/pw/2000 11Page Develop a computer program for the analysis of the engine. Allow the variation of the bypass ratio B, compressor pressure ratio л, 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., 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/m] 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 3 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.
solve by using Matlab ON-DESIGN ANALYSIS OF A TURBOFAN 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 engines¹. 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% Ycoid 1.40 Nozzle adiabatic efficiency 99% Cp.cold 1005 J/(kg-K) 1.25 Fan polytropic efficiency (er) 0.90 Yhot Compressor polytropic efficiency (e.Pc) 0.94 Cphot 1400 J/(kg-K) Compressor polytropic efficiency (ePC) 0.931 Mechanical efficiency (h) 0.96 Mechanical efficiency (haic) 0.93 Turbine polytropic efficiency (err) 0.97 Turbine polytropic efficiency (err) Maximum allowed temperature (TET) Fuel Lower Heating Value (Qav) Combustor pressure loss 45 MJ/kg 2% 0.96 1400 K https://www.prattwhitney.com/en/products/commercial-engines/pw/2000 11Page Develop a computer program for the analysis of the engine. Allow the variation of the bypass ratio B, compressor pressure ratio л, 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., 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/m] 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 3 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.
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter5: Analysis Of Convection Heat Transfer
Section: Chapter Questions
Problem 5.12P
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![solve by using Matlab
ON-DESIGN ANALYSIS OF A TURBOFAN
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 engines¹. 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%
Ycoid
1.40
Nozzle adiabatic efficiency
99%
Cp.cold
1005 J/(kg-K)
1.25
Fan polytropic efficiency (er)
0.90
Yhot
Compressor polytropic efficiency (e.Pc)
0.94
Cphot
1400 J/(kg-K)
Compressor polytropic efficiency (ePC) 0.931
Mechanical efficiency (h)
0.96
Mechanical efficiency (haic)
0.93
Turbine polytropic efficiency (err)
0.97
Turbine polytropic efficiency (err)
Maximum allowed temperature (TET)
Fuel Lower Heating Value (Qav)
Combustor pressure loss
45 MJ/kg
2%
0.96
1400 K
https://www.prattwhitney.com/en/products/commercial-engines/pw/2000
11Page
Develop a computer program for the analysis of the engine. Allow the variation of the
bypass ratio B, compressor pressure ratio л, 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., 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/m] 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 3 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.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F0a1ca4e0-f96f-41dc-a595-8acd1f0c0ac4%2Fdf93cb68-8c15-48f2-bf89-fc75b4fa9c6e%2Fhwaxge_processed.jpeg&w=3840&q=75)
Transcribed Image Text:solve by using Matlab
ON-DESIGN ANALYSIS OF A TURBOFAN
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 engines¹. 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%
Ycoid
1.40
Nozzle adiabatic efficiency
99%
Cp.cold
1005 J/(kg-K)
1.25
Fan polytropic efficiency (er)
0.90
Yhot
Compressor polytropic efficiency (e.Pc)
0.94
Cphot
1400 J/(kg-K)
Compressor polytropic efficiency (ePC) 0.931
Mechanical efficiency (h)
0.96
Mechanical efficiency (haic)
0.93
Turbine polytropic efficiency (err)
0.97
Turbine polytropic efficiency (err)
Maximum allowed temperature (TET)
Fuel Lower Heating Value (Qav)
Combustor pressure loss
45 MJ/kg
2%
0.96
1400 K
https://www.prattwhitney.com/en/products/commercial-engines/pw/2000
11Page
Develop a computer program for the analysis of the engine. Allow the variation of the
bypass ratio B, compressor pressure ratio л, 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., 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/m] 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 3 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.
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