1 Many small airplanes are powered by the turboprop engine (pictured). A simplistic view of aturboprop engine consists of the following 3 processes: compression of incoming air to anelevated pressure in a compressor, heating of the compressed air in a combustion chamber, andexpansion of the hot compressed air to extract shaft work in a turbine. The shaft work is used todrive the compressor and the rotating blades of the propeller.PropGearboxCompressorTurbineExhaustCombustionchamberShaftData:Incoming air temperature = 235 KAmbient air pressure at the cruise altitude of the airplane = 70 kPaConstant-pressure heat capacity of air = 30 J mol·1 K-1Molar flow rate of air through the engine = 100 mol s-1Heat transfer rate in the combustion chamber = 1.1 MWPressure ratio (Pout/Pin) of compressor = 12.0In an idealized turboprop engine, the air goes through what is called a Brayton cycle. Thecompressor and the turbine operates isentropically, and there is no pressure loss in thecombustion chamber.Calculate the difference in molar exergy between the incoming air and the exhaust, assumingthe combustion chamber acts as our infinite heat source at 1000 K. Hence, determine theSecond Law efficiency of the idealized turboprop engine. Why is your answer not 100% evenfor this idealized turboprop engine?

Calculate the difference in molar exergy between the incoming air and the exhaust, assuming the combustion chamber acts as our infinite heat source at 1000 K. Hence, determine the Second Law efficiency of the idealized turboprop engine. Why is your answer not 100% even for this idealized turboprop engine?

Calculate the difference in molar exergy between the incoming air and the exhaust, assuming the combustion chamber acts as our infinite heat source at 1000 K. Hence, determine the Second Law efficiency of the idealized turboprop engine. Why is your answer not 100% even for this idealized turboprop engine?

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

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Concept explainers

Moment of Inertia

Inertia can be termed as a resistance offered by a body to change its state. A rigid body initially at rest will apply resistance when acted by an external force that tends to change its state of rest or velocity, or a body initially at motion will provide resistance in changing its state of velocity or motion for coming to a state of rest. In other words, Newton's first law of motion describes the law of inertia of a rigid body.

Question

Many small airplanes are powered by the turboprop engine (pictured). A simplistic view of a
turboprop engine consists of the following 3 processes: compression of incoming air to an
elevated pressure in a compressor, heating of the compressed air in a combustion chamber, and
expansion of the hot compressed air to extract shaft work in a turbine. The shaft work is used to
drive the compressor and the rotating blades of the propeller.
Prop
Gearbox
Compressor
Turbine
Exhaust
Combustion
chamber
Shaft
Data:
Incoming air temperature = 235 K
Ambient air pressure at the cruise altitude of the airplane = 70 kPa
Constant-pressure heat capacity of air = 30 J mol·1 K-1
Molar flow rate of air through the engine = 100 mol s-1
Heat transfer rate in the combustion chamber = 1.1 MW
Pressure ratio (Pout/Pin) of compressor = 12.0
In an idealized turboprop engine, the air goes through what is called a Brayton cycle. The
compressor and the turbine operates isentropically, and there is no pressure loss in the
combustion chamber.
Calculate the difference in molar exergy between the incoming air and the exhaust, assuming
the combustion chamber acts as our infinite heat source at 1000 K. Hence, determine the
Second Law efficiency of the idealized turboprop engine. Why is your answer not 100% even
for this idealized turboprop engine?

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