Problem 4: Consider the following schematic of a simple turbojet engine model that uses air as its working fluid. With the data given determine (A) the pressure and temperature of all five states, (B) the amount of heat added in the burner, (C) the necessary air-to-fuel ratio of the engine, (D) the amount of power required by the compressor, and (E) the velocity of the exhaust stream at the exit of the system. Note: The variable rp is the compressor ratio defined to be the pressure of the compressor exit to the pressure of the compressor inlet. Assume that the compressor, turbine, and nozzle are all adiabatic and reversible. The Turbo jet Engine 2 R = P; : 100 kfa %3D 3 Burner T,: 300 k 6: 12 5: 1200 K Kefpo 4/3 %3D FHV = 43 KJ/g-fred
Problem 4: Consider the following schematic of a simple turbojet engine model that uses air as its working fluid. With the data given determine (A) the pressure and temperature of all five states, (B) the amount of heat added in the burner, (C) the necessary air-to-fuel ratio of the engine, (D) the amount of power required by the compressor, and (E) the velocity of the exhaust stream at the exit of the system. Note: The variable rp is the compressor ratio defined to be the pressure of the compressor exit to the pressure of the compressor inlet. Assume that the compressor, turbine, and nozzle are all adiabatic and reversible. The Turbo jet Engine 2 R = P; : 100 kfa %3D 3 Burner T,: 300 k 6: 12 5: 1200 K Kefpo 4/3 %3D FHV = 43 KJ/g-fred
Introduction to Chemical Engineering Thermodynamics
8th Edition
ISBN:9781259696527
Author:J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Publisher:J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Chapter1: Introduction
Section: Chapter Questions
Problem 1.1P
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Transcribed Image Text:Problem 4: Consider the following schematic of a simple turbojet engine model that uses air as its working
fluid. With the data given determine (A) the pressure and temperature of all five states, (B) the amount of heat
added in the burner, (C) the necessary air-to-fuel ratio of the engine, (D) the amount of power required by the
compressor, and (E) the velocity of the exhaust stream at the exit of the system.
Note: The variable rp is the compressor ratio defined to be the pressure of the compressor exit to the pressure of
the compressor inlet. Assume that the compressor, turbine, and nozzle are all adiabatic and reversible.
The Turbojet Engine
2
P = Pj
: 100 kPa
Burner
T,: 300 k
6: 12
5= 1200 K
FHV = 43 KJ/g- frel
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