|The typical cruising altitude of a commercial jet airliner is 10,700 m above sea level where the local atmospheric temperature is 219 K, and the pressure is 0.25 bar. The aircraft utilizes a cold air-standard Brayton cycle as shown with a volume flow rate of 1450 m³/s. The compressor pressure ratio is 50, and the maximum cycle temperature is 1700 K. The compressor and turbine isentropic efficiencies are 90%. Neglect kinetic and potential energy effects in this problem. Assume constant specific heats with k=1.4, Ra=0.287 kJ/kg- K, Cp=1.0045 kJ/kg-K, and cv = 0.7175 kJ/kg-K. a) Draw a T-s diagram for this cycle on the diagram provided. b) Fill in the table below with the missing information. T[K] Heat exchanger Heat exchanger State P [bar] 1 0.25 2s 2 3 4s 4 Turbine c) (5pts) Determine the inlet air density in [kg/m³] (at state 1), and the system mass flowrate in [kg/s]. d) (10pts) Determine the net power developed in [MW]. Be sure to draw each component you are analyzing, define the system, and apply conservation of energy in the space below. e) (10pts) Determine the rate of heat addition (Qi) in [MW]. Be sure to draw the component you are analyzing, define the system, and apply conservation of energy in the space below. f) (5pts) Determine the thermal efficiency of the cycle. g) (10pts) Assuming the source of the heat transfer in the combustor is a jet fuel flame at a constant 2500 K, determine the entropy generated in the combustor (heat exchanger) in [kW/K].
|The typical cruising altitude of a commercial jet airliner is 10,700 m above sea level where the local atmospheric temperature is 219 K, and the pressure is 0.25 bar. The aircraft utilizes a cold air-standard Brayton cycle as shown with a volume flow rate of 1450 m³/s. The compressor pressure ratio is 50, and the maximum cycle temperature is 1700 K. The compressor and turbine isentropic efficiencies are 90%. Neglect kinetic and potential energy effects in this problem. Assume constant specific heats with k=1.4, Ra=0.287 kJ/kg- K, Cp=1.0045 kJ/kg-K, and cv = 0.7175 kJ/kg-K. a) Draw a T-s diagram for this cycle on the diagram provided. b) Fill in the table below with the missing information. T[K] Heat exchanger Heat exchanger State P [bar] 1 0.25 2s 2 3 4s 4 Turbine c) (5pts) Determine the inlet air density in [kg/m³] (at state 1), and the system mass flowrate in [kg/s]. d) (10pts) Determine the net power developed in [MW]. Be sure to draw each component you are analyzing, define the system, and apply conservation of energy in the space below. e) (10pts) Determine the rate of heat addition (Qi) in [MW]. Be sure to draw the component you are analyzing, define the system, and apply conservation of energy in the space below. f) (5pts) Determine the thermal efficiency of the cycle. g) (10pts) Assuming the source of the heat transfer in the combustor is a jet fuel flame at a constant 2500 K, determine the entropy generated in the combustor (heat exchanger) in [kW/K].
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
![|The typical cruising altitude of a commercial jet airliner is 10,700 m above
sea level where the local atmospheric temperature is 219 K, and the pressure
is 0.25 bar. The aircraft utilizes a cold air-standard Brayton cycle as shown
with a volume flow rate of 1450 m³/s. The compressor pressure ratio is 50,
and the maximum cycle temperature is 1700 K. The compressor and turbine
isentropic efficiencies are 90%. Neglect kinetic and potential energy effects
in this problem. Assume constant specific heats with k=1.4, Ra=0.287 kJ/kg-
K, Cp=1.0045 kJ/kg-K, and cv = 0.7175 kJ/kg-K.
a) Draw a T-s diagram for this cycle on the diagram provided.
b) Fill in the table below with the missing information.
T[K]
Heat exchanger
Heat exchanger
State
P [bar]
1
0.25
2s
2
3
4s
4
Turbine
c) (5pts) Determine the inlet air density in [kg/m³] (at state 1), and the system mass flowrate
in [kg/s].
d) (10pts) Determine the net power developed in [MW]. Be sure to draw each component you
are analyzing, define the system, and apply conservation of energy in the space below.
e) (10pts) Determine the rate of heat addition (Qi) in [MW]. Be sure to draw the component
you are analyzing, define the system, and apply conservation of energy in the space below.
f) (5pts) Determine the thermal efficiency of the cycle.
g) (10pts) Assuming the source of the heat transfer in the combustor is a jet fuel flame at a
constant 2500 K, determine the entropy generated in the combustor (heat exchanger) in
[kW/K].](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F8713ba7c-61e3-40e0-afc1-3cb140fa24f1%2F2ba5c9cd-4f6a-4d45-88bb-e85a5face3b3%2Fxbjti28l_processed.jpeg&w=3840&q=75)
Transcribed Image Text:|The typical cruising altitude of a commercial jet airliner is 10,700 m above
sea level where the local atmospheric temperature is 219 K, and the pressure
is 0.25 bar. The aircraft utilizes a cold air-standard Brayton cycle as shown
with a volume flow rate of 1450 m³/s. The compressor pressure ratio is 50,
and the maximum cycle temperature is 1700 K. The compressor and turbine
isentropic efficiencies are 90%. Neglect kinetic and potential energy effects
in this problem. Assume constant specific heats with k=1.4, Ra=0.287 kJ/kg-
K, Cp=1.0045 kJ/kg-K, and cv = 0.7175 kJ/kg-K.
a) Draw a T-s diagram for this cycle on the diagram provided.
b) Fill in the table below with the missing information.
T[K]
Heat exchanger
Heat exchanger
State
P [bar]
1
0.25
2s
2
3
4s
4
Turbine
c) (5pts) Determine the inlet air density in [kg/m³] (at state 1), and the system mass flowrate
in [kg/s].
d) (10pts) Determine the net power developed in [MW]. Be sure to draw each component you
are analyzing, define the system, and apply conservation of energy in the space below.
e) (10pts) Determine the rate of heat addition (Qi) in [MW]. Be sure to draw the component
you are analyzing, define the system, and apply conservation of energy in the space below.
f) (5pts) Determine the thermal efficiency of the cycle.
g) (10pts) Assuming the source of the heat transfer in the combustor is a jet fuel flame at a
constant 2500 K, determine the entropy generated in the combustor (heat exchanger) in
[kW/K].
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