ANNA UNIVERSITY-CHENNAI
REGULATION 2013
DEPARTMENT OF MECHANICAL ENGINEERING
ME6604-GAS DYNAMICS AND JET PROPULSION
Unit II – Flow Through Ducts
Part
A (2 Marks)
1.
What are the consumption made for fanno flow?
2.
Differentiate Fanno flow and Rayleigh flow?
3.
Explain chocking in Fanno flow?
4.
Explain the difference between Fanno flow and Isothermal flow?
5.
Write down the ratio of velocities between any two sections in terms of their
Mach
number
in a fanno flow ?
6.
Write down the ratio of density between any two section in terms of their Mach
number
in a fanno flow?
7.
What are the three equation governing Fanno flow?
8.
Give the expression to find increase in entropy for Fanno flow?
9.
Give two practical examples where the Fanno flow occurs?
10.
What is Rayleigh line and Fanno line?
Click ME6602 Automobile Engg Anna University Question April May 2014
Part
B (16 Marks)
1.Air
having mach number 3 with total temperature 295 C and static pressure 0.5 bar
flows through a constant are duct adiabatically to another section where
the mach number is 1.5. Determine the amount of heat transfer and the
change in stagnation pressure
(AU:
May 2004)
2.Air
flow through a constant area duct with inlet temperature of 20 C and
inlet Mach number of 0.5. what is the possible exit stagnation
temperature? It is desired to transfer heat such that
at
exit of the duct the stagnation temperature is 1180 K. For this condition what
must be the limiting inlet Mach number? Neglect friction. (AU: Dec
2004)
3.Air
enters a combustion chamber with certain Mach number. Sufficient heat is added
to obtain a stagnation temperature ratio of 3 and a final Mach number of
0.8. Determine the Mach number at entry and the percentage loss in static
pressure. Take γ = 1.4 and Cp = 1.005 Kj/KgK. (AU: Dec 2005)
4.A
circular duct passes 8.25 kg/s of air at an exit Mach number of 0.5. The entry
pressure and temperature are 3.45 bar and 38 C respectively and the
coefficient of friction is 0.005. If the Mach number at entry is 0.15,
determine the diameter of the duct, length of the duct, pressure and
temperature at the exit, and stagnation pressure loss.
(AU:
May 2012, May 2010, May 2009, Dec 2007)
5.The
mach number at inlet and exit for a Rayleigh flow are 3 and 1.5 respectively.
At inlet static pressure is 50 kPa and stagnation temperature is 295 K.
Consider the fluid is air. Find i) the static pressure, temperature and velocity
at exit, ii) stagnation pressure at inlet and exit, iii) heat transferred,
iv) maximum possible heat transfer, v) change in entropy between the two
sections, vi) is it a cooling or heating process?
(AU:
May 2012)
6.Air
at Po = 10 bar, To = 400 K is supplied to a 50 mm diameter pipe. The friction
factor for the pipe surface is 0.002. If the Mach number changes from 3.0
at the entry to 1.0 at the exit determine i) the length of the pipe and
ii) the mass flow rate.
(AU:
May 2011)
7.A
combustion chamber in a gas turbine plant receives air at 350 k, 0.55 bar and
75m/s. The air fuel ratio is 29 and the calorific value of the fuel is
41.87MJ/Kg. Taking γ = 1.4 and R= 0.287 KJ/Kg K for the gas determine: I)
the initial and final mach numbers ii) final pressure, temperature and
velocity of the gas. Iii) percent stagnation pressure loss in the
combustion chamber and iv) the maximum stagnation temperature attainable.
(AU:
May 2011, Dec 2007)
8.The
stagnation temperature of air in a combustion chamber is increased to 3.5 times
its initial value. If the air at entry is at 5 bar, 105 C and a mach
number of 0.25 determine: i) the Mach number, pressure and temperature at
exit. ii) Stagnation pressure loss and iii) the heat supplied per kg of
air.
(AU:
May 2010, May 2008)
9.Air
enters a constant area duct at M1 = 3, P1 = 1 atm and T1 = 300 K. inside the
duct the heat added per unit mass is q = 3 × 105 J/Kg. Calculate the flow
properties M2, P2, T2, ρ2, To2 and Po2 at the exit. (AU: Dec 2009)
10.Air
at an inlet temperature of 60 C flows with subsonic velocity through an
insulated pipe having inside diameter of 50 mm and a length of 5 m. The
pressure at the exit of the pipe is 101 kPa and the flow is choked at the
end of the pipe. If the friction factor 4f = 0.005. determine the inlet
Mach number, the mass flow rate and the exit temperature.
(AU:
Dec 2009)
11.Air
flows with negligible friction in a constant are duct. At section one, the flow
properties are T1 = 60.4 C, P1 = 135 kPa absolute and velocity 732 m/s.
Heat is added to the flow between section one and section two, where the
mach number is 1.2. Determine the flow
properties
at section two, the heat transfer per unit mass and the entropy
change. (AU: May 2009)
12.A
long pipe of 0.0254 m diameter has a mean coefficient of friction of 0.003. Air
enters the pipe at a mach number of 2.5, stagnation temperature 310 K and
static pressure 0.507 bar. Determine for a section at which the mach
number reaches 1.2: i) Static pressure and temperature, ii) Stagnation
pressure and temperature, iii) Velocity of air, iv) Distance of
this section from the inlet and v) mass flow rate of air.
(AU:
Dec 2008, May 2008)
13.The
mach number at the exit of a combustion chamber is 0.9. the ratio of stagnation temperatures
at exit and entry is 3.74. If the pressure and temperature of the gas at exit
are 2.5 bar and 1273 K respectively, determine: i) Mach number, pressure
and temperature of the gas at entry ii) the heat supplied per Kg of the
gas and iii) the maximum heat that can be supplied.
(AU:
Dec 2008)
See right side of this page,For more Mechanical Engineering subjects Study materials like Lecture notes, PDF,PPT,Question bank,University questions were uploaded in annaunivstudymaterials.blogspot.com
See right side of this page,For more Mechanical Engineering subjects Study materials like Lecture notes, PDF,PPT,Question bank,University questions were uploaded in annaunivstudymaterials.blogspot.com
The question bank
for unit 1,2,3,4,5 were uploaded from the following link or copy paste the
following link
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Unit 5 Question bank-Click the link
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Unit 1 Question bank-Click the link
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