i-Use the first law of thermodynamics to determine an algebraic equation for the combustorexit temperature (T 04 ) in terms of equivalence ratio (phi) if the fuel in Problem 2 is used. Hint:find the equation for f in terms of T04 and T03 in the canvas handout, our class notes, or in thetextbook in Chpt 5. Then solve that equation for T04 .Assume that the compressor exit temperature T 03 is 650 K. The heating value (Q R ) of thenew fuel in problem 2 is 39,000 kJ/kg fuel. The effective heat capacity cp of the mixture is constant and is 1.2 kJ/(kg-K). Insert these values into your equation for (T 04 ) in terms ofequivalence ratio (phi) ii-Now consider values of fuel-air equivalence ratios (phi) of 0.1, 0.2, 0.3, 0.4, 0.5. Use Matlab,Excel or some other program to use your equation from problem 2 to plot a graph of T04versus f. You have just computed the “adiabatic flame temperature”; the turbojet / turbofan engine designer can decide what fuel-air ratio to use to achieve the desired combustor exit temperature. iii - What is the value for T04 for phi = 0.2? Please show all work!!
i-Use the first law of thermodynamics to determine an algebraic equation for the combustorexit temperature (T 04 ) in terms of equivalence ratio (phi) if the fuel in Problem 2 is used. Hint:find the equation for f in terms of T04 and T03 in the canvas handout, our class notes, or in thetextbook in Chpt 5. Then solve that equation for T04 .Assume that the compressor exit temperature T 03 is 650 K. The heating value (Q R ) of thenew fuel in problem 2 is 39,000 kJ/kg fuel. The effective heat capacity cp of the mixture is constant and is 1.2 kJ/(kg-K). Insert these values into your equation for (T 04 ) in terms ofequivalence ratio (phi) ii-Now consider values of fuel-air equivalence ratios (phi) of 0.1, 0.2, 0.3, 0.4, 0.5. Use Matlab,Excel or some other program to use your equation from problem 2 to plot a graph of T04versus f. You have just computed the “adiabatic flame temperature”; the turbojet / turbofan engine designer can decide what fuel-air ratio to use to achieve the desired combustor exit temperature. iii - What is the value for T04 for phi = 0.2? Please show all work!!
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
Related questions
Question
i-Use the first law of thermodynamics to determine an algebraic equation for the combustor
exit temperature (T 04 ) in terms of equivalence ratio (phi) if the fuel in Problem 2 is used. Hint:
find the equation for f in terms of T04 and T03 in the canvas handout, our class notes, or in the
textbook in Chpt 5. Then solve that equation for T04 .
Assume that the compressor exit temperature T 03 is 650 K. The heating value (Q R ) of the
new fuel in problem 2 is 39,000 kJ/kg fuel. The effective heat capacity cp of the mixture is constant and is 1.2 kJ/(kg-K). Insert these values into your equation for (T 04 ) in terms of
equivalence ratio (phi)
exit temperature (T 04 ) in terms of equivalence ratio (phi) if the fuel in Problem 2 is used. Hint:
find the equation for f in terms of T04 and T03 in the canvas handout, our class notes, or in the
textbook in Chpt 5. Then solve that equation for T04 .
Assume that the compressor exit temperature T 03 is 650 K. The heating value (Q R ) of the
new fuel in problem 2 is 39,000 kJ/kg fuel. The effective heat capacity cp of the mixture is constant and is 1.2 kJ/(kg-K). Insert these values into your equation for (T 04 ) in terms of
equivalence ratio (phi)
ii-Now consider values of fuel-air equivalence ratios (phi) of 0.1, 0.2, 0.3, 0.4, 0.5. Use Matlab,
Excel or some other program to use your equation from problem 2 to plot a graph of T04
versus f. You have just computed the “adiabatic flame temperature”; the turbojet / turbofan engine designer can decide what fuel-air ratio to use to achieve the desired combustor exit temperature.
Excel or some other program to use your equation from problem 2 to plot a graph of T04
versus f. You have just computed the “adiabatic flame temperature”; the turbojet / turbofan engine designer can decide what fuel-air ratio to use to achieve the desired combustor exit temperature.
iii - What is the value for T04 for phi = 0.2?
Please show all work!!
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