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PilotLPTM [1.2K]
3 years ago
6

The Boeing 787 Dreamliner is billed to be 20% more fuel efficient than the comparable Boeing 767 and will fly at Mach 0.85. The

midsize Boeing 767 has a range of 12,000 km, a fuel capacity of 90,000 L, and flies at Mach 0.80. For Boeing 787, assume the speed of sound is 700 mph and calculate the projected volumetric flow rate of fuel for each of the two Dreamliner engines in m3/s.
Engineering
1 answer:
evablogger [386]3 years ago
8 0

Answer:

the projected volumetric flow rate of fuel for each of the two Dreamliner engines is 0.005 m³/s

Explanation:

Given the data in the question;

First we determine the fuel economy of Boeing 767

Range = 12,000 km

fuel capacity = 90,000 L

so,  fuel economy of Boeing 767 will be

η_f = Range / fuel capacity

η_f = ( 12,000 km / 90000 L ) ( 1000m / 1 km) ( 3.7854 L/gal × 264.2 gal/m² )

η_f  = 133,347.024 m/m³

Now, Boeing 787 is 20% more fuel efficient than Boeing 767

so fuel economy of Boeing 787 will be;

⇒ (1 - 20%) × fuel economy of Boeing 767

⇒ (1 - 0.2) × 133,347.024 m/m³

⇒ 0.8 × 133,347.024 m/m³

⇒ 106,677.6 m/m³

Hence, fuel economy of Boeing 787 dream line engine is

⇒ 106,677.6 m/m³ / 2 = 53,338.8 m/m³

Next, we find the velocity of Boeing 787

V_{787 = Mach number of 787 × speed of sound

given that; Mach number is 0.85 and speed of sound is 700 mph

we substitute

V_{787 = (0.85 × 700 mph) × ( 1 hr / 3600 s ) × ( 1609 m / 1 mile )

V_{787 = 265.9319 m/s

Now, to get the Volume flow rate for each dream liner engine { Boeing 787 };

Volumetric flow rate = velocity of flight / fuel economy

we substitute

= 265.9319 m/s / 53,338.8 m/m³

= 0.0049857 ≈ 0.005 m³/s

Therefore,  the projected volumetric flow rate of fuel for each of the two Dreamliner engines is 0.005 m³/s

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Convert 250 lb·ft to N.m. Express your answer using three significant figures.
vfiekz [6]

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It will be equivalent to 338.95 N-m

Explanation:

We have to convert 250 lb-ft to N-m

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So 250 lb = 250×4.45 =125 N

And we know that 1 feet = 0.3048 meter

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Air modeled as an ideal gas enters a turbine operating at steady state at 1040 K, 278 kPa and exits at 120 kPa. The mass flow ra
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Answer:

a) T_{2}=837.2K

b) e=91.3 %

Explanation:

A) First, let's write the energy balance:

W=m*(h_{2}-h_{1})\\W=m*Cp*(T_{2}-T_{1})  (The enthalpy of an ideal gas is just function of the temperature, not the pressure).

The Cp of air is: 1.004 \frac{kJ}{kgK} And its specific R constant is 0.287 \frac{kJ}{kgK}.

The only unknown from the energy balance is T_{2}, so it is possible to calculate it. The power must be negative because the work is done by the fluid, so the energy is going out from it.

T_{2}=T_{1}+\frac{W}{mCp}=1040K-\frac{1120kW}{5.5\frac{kg}{s}*1.004\frac{kJ}{kgk}} \\T_{2}=837.2K

B) The isentropic efficiency (e) is defined as:

e=\frac{h_{2}-h_{1}}{h_{2s}-h_{1}}

Where {h_{2s} is the isentropic enthalpy at the exit of the turbine for the isentropic process. The only missing in the last equation is that variable, because h_{2}-h_{1} can be obtained from the energy balance  \frac{W}{m}=h_{2}-h_{1}

h_{2}-h_{1}=\frac{-1120kW}{5.5\frac{kg}{s}}=-203.64\frac{kJ}{kg}

An entropy change for an ideal gas with  constant Cp is given by:

s_{2}-s_{1}=Cpln(\frac{T_{2}}{T_{1}})-Rln(\frac{P_{2}}{P_{1}})

You can review its deduction on van Wylen 6 Edition, section 8.10.

For the isentropic process the equation is:

0=Cpln(\frac{T_{2}}{T_{1}})-Rln(\frac{P_{2}}{P_{1}})\\Rln(\frac{P_{2}}{P_{1}})=Cpln(\frac{T_{2}}{T_{1}})

Applying logarithm properties:

ln((\frac{P_{2}}{P_{1}})^{R} )=ln((\frac{T_{2}}{T_{1}})^{Cp} )\\(\frac{P_{2}}{P_{1}})^{R}=(\frac{T_{2}}{T_{1}})^{Cp}\\(\frac{P_{2}}{P_{1}})^{R/Cp}=(\frac{T_{2}}{T_{1}})\\T_{2}=T_{1}(\frac{P_{2}}{P_{1}})^{R/Cp}

Then,

T_{2}=1040K(\frac{120kPa}{278kPa})^{0.287/1.004}=817.96K

So, now it is possible to calculate h_{2s}-h_{1}:

h_{2s}-h_{1}}=Cp(T_{2s}-T_{1}})=1.004\frac{kJ}{kgK}*(817.96K-1040K)=-222.92\frac{kJ}{kg}

Finally, the efficiency can be calculated:

e=\frac{h_{2}-h_{1}}{h_{2s}-h_{1}}=\frac{-203.64\frac{kJ}{kg}}{-222.92\frac{kJ}{kg}}\\e=0.913=91.3 %

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