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Shkiper50 [21]
4 years ago
14

A two-stroke CI. engine delivers 5000 kWwhile using 1000 kW to overcome friction losses. It consumes 2300 kg of fuel per hour at

an air-fuel ratio of 20 to 1. The heating value of fuel is 42000 kJkg Find the (a) indicated power (b) mechanical efïiciency, (c) air consumption per hr, (d) indicated themal efficiency, and (e) brake thermal efficiency.
Engineering
1 answer:
Lady_Fox [76]4 years ago
5 0

Answer:

(a) Indicating power(IP)=6000 KW

(b)   \eta_{mech}=0.833

(c) Consumption of air per hour =46000 kg/hr

(d) \eta_{BPth}=0.1865

Explanation:

Break power(BP) =5000 KW

Friction power(FP)=1000 KW

Consumption of fuel per hour=2300 kg/hr

CV=42000 KJ/kg

We know that

Indicating power(IP)=Break power(BP)+Friction power(FP)

⇒IP=5000+1000 KW

  IP=6000 KW

(a)

Indicating power(IP)=6000 KW

(b)

Mechanical efficiency  \eta_{mech}=\dfrac{BP}{IP}

 \eta_{mech}=\dfrac{5000}{6000}      

  \eta_{mech}=0.833

(c)

Air fuel ratio=\dfrac{mass \ of \ air}{mass \ of \ fuel}

consumption of air per hour=20\times2300 kg/hr

So consumption of air per hour =46000 kg/hr

(d)

Break thermal efficiency  \eta_{BPth}=\dfrac{IP}{\dot{m_f}\times CV}

\dot{m_f}=\dfrac{2300}{3600}  

                      =0.638 kg/s

\eta_{BPth}=\dfrac{5000}{{0.638}\times 42000}

\eta_{BPth}=0.1865

 

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Thin film deposition is a process where: a)-elemental, alloy, or compound thin films are deposited onto a bulk substrate! b)-Pho
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Answer:

(A) elemental, alloy, or compound thin films are deposited on to a bulk substrate

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8 0
3 years ago
A medium-sized jet has a 3.8-mm-diameter fuselage and a loaded mass of 85,000 kg. The drag on an airplane is primarily due to th
SCORPION-xisa [38]

Answer:

F_{thrust} ≅ 111 KN

Explanation:

Given that;

A medium-sized jet has a 3.8-mm-diameter i.e diameter (d) = 3.8

mass = 85,000 kg

drag co-efficient (C) = 0.37

(velocity (v)= 230 m/s

density (ρ) = 1.0 kg/m³

To calculate the thrust; we need to determine the relation of the drag force; which is given as:

F_{drag} = \frac{1}{2} × CρAv²

where;

ρ = density of air wind.

C = drag co-efficient

A = Area of the jet

v = velocity of the jet

From the question, we can deduce that the jet is in motion with a constant speed; as such: the net force acting on the jet in the air = 0

SO, F_{drag}-F_{thrust} = 0

We can as well say:

F_{drag}= F_{thrust}

We can now replace F_{thrust} with F_{drag} in the above equation.

Therefore, F_{thrust} = \frac{1}{2} × CρAv²

The A which stands as the area of the jet is given by the formula:

A=\frac{\pi d^2}{4}

We can now have a new equation after substituting our A into the previous equation as:

F_{thrust} = \frac{1}{2} × Cρ (\frac{\pi d^2}{4})v^2

Substituting our data from above; we have:

F_{thrust} = \frac{1}{2} × (0.37)(1.0kg/m^3)(\frac{\pi(3.8m)^2 }{4})(230m/s)^2

F_{thrust} = \frac{1}{8}   (0.37)(1.0kg/m^3)({\pi(3.8m)^2 })(230m/s)^2

F_{thrust} = 110,990N

F_{thrust}  in N (newton) to KN (kilo-newton) will be:

F_{thrust} = (110,990N)*\frac{1KN}{1,000N}

F_{thrust} = 110.990 KN

F_{thrust} ≅ 111 KN

In conclusion, the jet engine needed to provide 111 KN thrust in order to cruise at 230 m/s at an altitude where the air density is 1.0 kg/m³.

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Answer:

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