مراد جبار فرحانIn a gas turbine engine (A, = 2.85 A2, p1 = 1.14 p2,p1 = 100.5 kPa, T, = 11 °C, v1 = 107 m-s1, V2 = 785m-s", A, = 2.4 m?), calculate the thrust force.%3D%3D===

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Answered: In a gas turbine engine (A, = 2.85 A2,…

In a gas turbine engine (A, = 2.85 A2, pi = 1.14 p2, p1 = 100.5 kPa, T1 = 11 °C, V1 = 107 m-s1, v2 = 785 m-s1, A, = 2.4 m?), calculate the thrust force. %3D %3D

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

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Question

مراد جبار فرحان
In a gas turbine engine (A, = 2.85 A2, p1 = 1.14 p2,
p1 = 100.5 kPa, T, = 11 °C, v1 = 107 m-s1, V2 = 785
m-s", A, = 2.4 m?), calculate the thrust force.
%3D
%3D
===

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We give: AB: adiabatic trigger such as VB = 2 VA AC: isothermal compression PA =1bar=105 Pa , VA = 10^-2 m3 Gas temperature at point A: TA= 300 Kelvin Perfect gas constant: R = 8,31 J.mol-1.K-1 Molar thermal capacity at constant pressure:Cp = 29 J.mol-1.K-1 Calorific capacity ratio of this gas: Cp/Cv = 1,40 4 – Calculate the amount of QBC heat and WBC work received by the system for the transformation that changes the system from state B to state C.5 – a – Why is the UCA internal energy variation of the gas zero during the CA transformation? b – Apply the first principle to the ABCA cycle and deduce the WAB work received by the gas during theadiabatic relaxation AB.c – Interpret the WAB sign.
71. Find the inlet cross-sectional-area for an airplane engine (p, = 1.31 p2, P2 = 99.8 kPa, T2 = 232 °C, v, = 109 m-s1, v2 = 811 m-s1, A2 = 0.7 m?, Fth = 33 kN). png càug yảào %3D %3D %3D == ===
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Question B3 The engine of an aeroplane is equipped with an ideal convergent nozzle with an area ratio Ainlet 2.035 ( -A-2.035), as in Figure Q-B3. The aeroplane is flying at an altitude of 11 Aexit km where the atmospheric pressure and temperature are 0.23 bar and 216K respectively. You may assume the combustion gases entering the nozzle have the same property as air (i.e. y=1.40, R=287 J/kgK and Cp-1004.5J/kgK). Page 6 Question B3 continued inlet exit Amles/Aexit -AVAJ-2.035 Figure Q-B3 a) If the nozzle operates at its critical condition, calculate: the inlet Mach number M;. nozzle's exit velocity V, the inlet stagnation pressure Por- the inlet static pressure FG The stagnation Aj P, and the nozzle's gross thrust per unit exit area temperature of the gases entering the nozzle is To 1200 K. b) If the stagnation pressure at the inlet of the nozzle is reduced to 80% of its value in part (a), determine the exit static temperature 7;, the nozzle's gross thrust per unit exit area FG. The…