System Capacity means the available operational capacity of the System at any applicable point in time, as such amount may vary from time to time pursuant to any contractual arrangements entered into by Carrier.
<h3>What is capacity of a production system?</h3>
Production capacity is the maximum possible output of a manufacturing business, measured in units of output per period. Knowing your production capacity gives you the chance to better plan and schedule production, give more accurate lead times, and forecast your cash flow.
<h3>What is an example of capacity?</h3>
The definition of capacity is the ability of someone or something to hold something. An example of capacity is how many people can fit in a room. An example of capacity is the amount of water a cup can hold.
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Answer:
Pitch circle diameter = 5,66 inch
Explanation:
<u>According to the pitch circle diameter formula</u>
<em>Dc= Dp - 2b</em> ; where Dp= primitive diameter, b= dedendum of the tooth and also the dedendum formula is b= 1,25 Pc/π.
The definition of primitive diameter is equal to (Pc*Z)/π ; Pc= circular pitch and Z= number of teeths.
<u>Replacing in the formula </u>
⇒ Dc= (Pc*Z)/π - 2* 1,25 Pc/π, Pc= 0,375 ; Z=50
In conclusion the pitch circle diameter is equal to:
Dc= 5,66 inch.
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Answer:
The thrust of the engine calculated using the cold air is 34227.35 N
Explanation:
For the turbofan engine, firstly the overall mass flow rate is considered. The mass flow rate is given as
Here
- ρ is the density which is given as
- P is the pressure of air at 5500 m from the ISA whose value is 50506.80 Pa
- R is the gas constant whose value is 286.9 J/kg.K
- T is the temperature of the inlet which is given as 253 K
- A is the cross-sectional area of the inlet which is given by using the diameter of 2.0 m
- V_a is the velocity of the aircraft which is given as 250 m/s
So the equation becomes
Now in order to find the flow from the fan, the Bypass ratio is used.
Here BPR is given as 8 so the equation becomes
Now the exit velocity is calculated using the total energy balance which is given as below:
Here
- h_4 and h_5 are the enthalpies at point 4 and 5 which could be rewritten as and respectively.
- The value of T_4 is the inlet temperature which is 253 K
- The value of T_5 is the outlet temperature which is 233K
- The value of c_p is constant which is 1005 J/kgK
- V_a is the inlet velocity which is 250 m/s
- V_e is the outlet velocity that is to be calculated.
So the equation becomes
Rearranging the equation gives
Now using the cold air approach, the thrust is given as follows
So the thrust of the engine calculated using the cold air is 34227.35 N