Compressors Gas Turbines and Jet Engines Pdf Free Download

1. The following property is most important for material used for gas turbine blade

A. Toughness

B. Fatigue

C. Creep

D. Corrosion resistance

Answer: Option C

Solution:

The following property is most important for material used for gas turbine blade creep

2. The main purpose of reheating in gas turbine is to

A. Increase temperature

B. Reduce turbine size

C. Increase power output

D. Increase speed

Answer: Option C

Solution:

The main purpose of reheating is to avoid excess moisture and to increase the quality of steam at the end section of turbine.

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3. In the cross compounding of the gas turbine plant

A. H.P. compressor is connected to H.P. turbine and L.P. compressor to L.P. turbine

B. H.P. compressor is connected to L.P. turbine and L.P. compressor is connected to H.P. turbine

C. Both the arrangements can be employed

D. All are connected in series

Answer: Option B

Solution:

In the cross compounding of the gas turbine plant H.P. compressor is connected to L.P. turbine and L.P. compressor is connected to H.P. turbine

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4. The advantage of multistage compression over single stage compression is

A. Lower power consumption per unit of air delivered

B. Higher volumetric efficiency

C. Decreased discharge temperature

D. All of the above

Answer: Option D

Solution:

Advantages of multi-stage compressor over single stage compressor. -The fluid can be compressed to very high

pressure. - The intercooler is more efficient than the cylinder wall cooling in a single stage compressor. -

Pressure ratio per each stage is lowered and it reduces the leakage loss.

5. 1 m of air at atmospheric condition weighs approximately

A. 0.5 kg

B. 1.0 kg

C. 1.3 kg

D. 2.2 kg

Answer: Option C

Solution:

1 m of air at atmospheric condition weighs approximately 1.3 kg

Compressors Gas Turbines and Jet Engines Pdf Free Download

6. A simple turbojet engine is basically

A. A propeller system

B. Gas turbine engine equipped with a propulsive nozzle and diffuse

C. Chemical rocket engine

D. Ramjet engine

Answer: Option B

Solution:

A simple turbojet engine is basically Gas turbine engine equipped with a propulsive nozzle and diffuse

7. The efficiency of a jet engine is higher at

A. Low speeds

B. High speeds

C. Low altitudes

D. High altitudes

Answer: Option D

Solution:

The efficiency of a jet engine is higher at high altitudes

Answer & Solution

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8. The degree of reaction in an axial flow compressor is defined as the ratio of static enthalpy rise in the

A. Rotor to static enthalpy rise in the stator

B. Stator to static enthalpy rise in the rotor

C. Rotor to static enthalpy rise in the stage

D. Stator to static enthalpy rise in the stage

Answer: Option C

Solution:

The degree of reaction in an axial flow compressor is defined as the ratio of static enthalpy rise in the Rotor to

static enthalpy rise in the stage

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9. The performance of air compressor at high altitudes will be ________ as compared to that at sea level.

A. Same

B. Lower

C. Higher

D. None of these

Answer: Option B

Solution:

The performance of air compressor at high altitudes will be lower as compared to that at sea level.

Answer & Solution

10. Maximum work is done in compressing air when the compression is

A. Isothermal

B. Adiabatic

C. Polytropic

D. None of the above

Answer: Option B

Solution:

Maximum work is done in compressing air when the compression is adiabatic

Compressors Gas Turbines and Jet Engines Pdf Free Download

11. The volumetric efficiency of a compressor falls roughly as follows for every 5°C increase in atmospheric temperature

A. 0.1%

B. 0.5%

C. 1%

D. 5%

Answer: Option C

Solution:

The volumetric efficiency of a compressor falls roughly as follows for every 5°C increase in atmospheric temperature 1%

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12. The area of actual indicator diagram on an air compressor as compared to area of ideal indicator diagram is

A. Less

B. More

C. Same

D. More/less depending on compressor capacity

Answer: Option B

Solution:

The area of actual indicator diagram on an air compressor as compared to area of ideal indicator diagram is

13. In a centrifugal compressor, the highest Mach number leading to shock wave in the fluid flow occurs at

A. Diffuser inlet radius

B. Diffuser outlet radius

C. Impeller inlet radius

D. Impeller outlet radius

Answer: Option B

Solution:

In a centrifugal compressor, the highest Mach number leading to shock wave in the fluid flow occurs at diffuser outlet radius

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15. Axial flow compressor has the following advantage over centrifugal compressor

A. Larger air handling ability per unit frontal area

B. Higher pressure ratio per stage

C. Aerofoil blades are used

D. Higher average velocities

Answer: Option A

Solution:

Axial flow compressor has the following advantage over centrifugal compressor Larger air handling ability per unit frontal area

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Compressors Gas Turbines and Jet Engines Pdf Free Download

16. The pressure ratio of an ideal vaned compressor with increase in mass flow rate

A. Increases

B. Decreases

C. Remain constant

D. First decreases and then increases

Answer: Option C

Solution:

The pressure ratio of an ideal vaned compressor with increase in mass flow rate remain constant

17. The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio

A. Increases

B. Decreases

C. First increases and then decreases

D. First decreases and then increases

Answer: Option A

Solution:

The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio Increases

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18. A closed cycle gas turbine consists of a

A. Compressor

B. Heating chamber

C. Cooling chamber

D. All of these

Answer: Option D

Solution:

A closed cycle gas turbine consists of a -Compressor - Heating chamber -Cooling chamber

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19. During base load operation, the best method of controlling compressor is

A. Start-stop motor

B. Constant speed unloader

C. Relief valve

D. Variable speed

Answer: Option A

Solution:

During base load operation, the best method of controlling compressor is Start-stop motor

20. The effective power of gas turbines is increased by adding the following in compressor

A. Ammonia and water vapour

B. Carbon dioxide

C. Nitrogen

D. Hydrogen

Answer: Option A

Compressors Gas Turbines and Jet Engines Pdf Free Download

21. For an irreversible gas turbine cycle, the efficiency and work ratio both depend on

A. Pressure ratio alone

B. Maximum cycle temperature alone

C. Minimum cycle temperature alone

D. Both pressure ratio and maximum cycle temperature

Answer: Option D

Solution:

For an irreversible gas turbine cycle, the efficiency and work ratio both depend on Both pressure ratio and maximum cycle temperature

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22. For minimum work in multistage compression, assuming same index of compression in all stages

A. Work done in first stage should be more

B. Work done in subsequent stages should increase

C. Work done in subsequent stages should decrease

D. Work done in all stages should be equal

Answer: Option D

Solution:

For minimum work in multistage compression, assuming same index of compression in all stages Work done in all stages should be equal

23. In a single acting reciprocating air compressor, without clearance, the compression of air may be

A. Isothermal

B. Polytropic

C. Isentropic

D. Any one of these

Answer: Option D

Solution:

In a single acting reciprocating air compressor, without clearance, the compression of air may be

- Isothermal

- Polytropic

- Isentropic

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25. Euler's equation is applicable for

A. Centrifugal compressor

B. Axial compressor

C. Pumps

D. All of the above

Answer: Option D

Solution:

Euler's equation is applicable for -Centrifugal compressor -Axial compressor -Pumps

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Compressors Gas Turbines and Jet Engines Pdf Free Download

26. The compressor capacity is defined as the

A. Actual volume of the air delivered by the compressor when reduced to normal temperature and pressure conditions

B. Volume of air delivered by the compressor

C. Volume of air sucked by the compressor during its suction stroke

D. None of the above

Answer: Option B

Solution:

The compressor capacity is defined as the Volume of air delivered by the compressor

27. In a single stage, single acting reciprocating air compressor without clearance volume, the work-done is maximum during

A. Isothermal compression

B. Isentropic compression

C. Polytropic compression

D. None of these

Answer: Option B

Solution:

In a single stage, single acting reciprocating air compressor without clearance volume, the work-done is maximum during isentropic compression

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28. In a single stage, single acting reciprocating air compressor, without clearance volume, the work-done is minimum during

A. Isothermal compression

B. Isentropic compression

C. Polytropic compression

D. None of these

Answer: Option A

Solution:

In a single stage, single acting reciprocating air compressor, without clearance volume, the work-done is minimum during Isothermal compression

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29. In a centrifugal compressor, the flow of air is ________ to the axis of compressor.

A. Parallel

B. Perpendicular

C. Inclined

D. None of these

Answer: Option B

Solution:

In a centrifugal compressor, the flow of air is perpendicular to the axis of compressor.

30. The most efficient method of compressing air is to compress it

A. Isothermally

B. Adiabatically

C. Isentropically

D. Isochronically

Answer: Option A

Solution:

The most efficient method of compressing air is to compress it Isothermall

Compressors Gas Turbines and Jet Engines Pdf Free Download

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Which compressor is used in jet engine?

Jet engines typically use axial compressors to compress incoming air before it enters the combustion chamber. An axial compressor is a type of compressor that uses a series of rotating airfoils, or blades, to compress the air in a continuous flow. As the air moves through the compressor, the blades increase the pressure and decrease the volume of the air, which makes it more suitable for combustion in the engine's combustion chamber. Axial compressors are preferred for their high efficiency and high airflow capacity, which are necessary for the high power and high speeds of jet engines.

What compressor is used in gas turbines?

Gas turbines use axial compressors to compress the incoming air before it enters the combustion chamber. Axial compressors are a type of dynamic compressor that use a series of rotating blades to compress the air. The blades in an axial compressor are arranged in a series of stages, each with a row of stationary blades called stator vanes and a row of rotating blades called rotor blades. As the rotor blades rotate, they draw in air and compress it as it passes through the smaller spaces between the rotor and stator blades. The compressed air is then directed into the combustion chamber, where it is mixed with fuel and ignited to create the high-temperature, high-pressure gases that drive the turbine blades.

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What does the compressor do in a jet engine?

In a jet engine, the compressor is responsible for compressing incoming air to increase its pressure and temperature before it is mixed with fuel and ignited in the combustion chamber.

The compressor is typically made up of multiple stages, each of which consists of rotating blades and stationary vanes. The blades on the rotor of each stage spin at a high speed, drawing air into the engine and accelerating it towards the next stage. As the air moves through the compressor stages, its pressure and temperature increase, preparing it for combustion.

The compressed air is then mixed with fuel in the combustion chamber, where it is ignited and burns, generating a high-temperature and high-pressure stream of exhaust gases. These exhaust gases then expand through the turbine, which powers the compressor and other accessories in the engine before being expelled from the rear of the engine as thrust.

Overall, the compressor plays a crucial role in the functioning of a jet engine by compressing incoming air to prepare it for combustion and creating the high-pressure stream of exhaust gases that produces the engine's thrust.

What is gas turbine and jet propulsion?

Gas turbines and jet propulsion are two related technologies that involve the use of high-velocity gases to produce thrust for various applications.

A gas turbine is a type of internal combustion engine that converts the energy of burning fuel into mechanical energy, which is then used to turn a turbine and generate electricity or propel a vehicle. In a gas turbine, air is compressed and mixed with fuel, which is then ignited in a combustion chamber. The hot gases produced by the combustion expand rapidly, passing through the turbine blades and driving them to rotate. The turbine is connected to a shaft, which can be used to generate electricity or provide mechanical power to drive a vehicle or machinery.

Jet propulsion, on the other hand, is a type of propulsion system used in aircraft and other vehicles that rely on high-velocity gases to generate thrust. In a jet engine, air is drawn into the engine and compressed, then mixed with fuel and ignited to produce a high-velocity stream of hot gases that exits the back of the engine, creating forward thrust. The basic principle of jet propulsion is Newton's Third Law of Motion, which states that for every action, there is an equal and opposite reaction. By expelling hot gases at high speed in one direction, the aircraft is propelled in the opposite direction.

While gas turbines and jet propulsion both use the same basic principle of converting the energy of burning fuel into high-velocity gases to produce thrust, they are typically used for different applications. Gas turbines are often used to generate electricity or provide mechanical power for machinery, while jet propulsion is used primarily in aircraft and other vehicles that require high speed and maneuverability.

What is the difference between jet propulsion and rocket propulsion?

Jet propulsion and rocket propulsion are both methods of propelling objects through the air or in space, but there are some key differences between them.

Jet propulsion is a type of engine that works by taking in air from the surrounding environment, compressing it, and then mixing it with fuel to create a high-velocity exhaust stream. This exhaust stream creates a reaction force that propels the vehicle forward. The most common example of jet propulsion is the turbojet engine used in airplanes.

Rocket propulsion, on the other hand, is a type of engine that carries both fuel and oxidizer on board and does not rely on the surrounding air to generate thrust. The fuel and oxidizer are mixed and burned in the rocket engine, and the exhaust gases are expelled out of the back of the rocket at a high velocity, creating a reaction force that propels the rocket forward. Rockets are commonly used to propel spacecraft and missiles.

One key advantage of rocket propulsion over jet propulsion is that rockets can operate in the vacuum of space, where there is no air for a jet engine to compress and use for propulsion. However, rockets generally require more fuel to achieve the same amount of thrust as a jet engine, making them less efficient for use within the Earth's atmosphere.

What is the difference between rocket engine and gas turbine engine?

Rocket engines and gas turbine engines are two different types of propulsion systems with unique features and applications. The main differences between them are as follows:

Working principle: A rocket engine generates thrust by expelling hot gases at high velocities through a nozzle, whereas a gas turbine engine produces thrust by using a compressor to compress air, mixing it with fuel, igniting the mixture, and expelling the hot gases through a turbine.

Fuel: Rocket engines typically use liquid or solid propellants, whereas gas turbine engines typically burn liquid or gaseous fuels, such as jet fuel or natural gas.

Efficiency: Gas turbine engines are generally more efficient than rocket engines, as they can extract energy from the combustion gases to power the compressor, generator, or other devices.

Altitude: Rocket engines are better suited for high-altitude or space applications, where the thin atmosphere limits the effectiveness of air-breathing engines. Gas turbine engines are used primarily in aircraft, ships, power plants, and other terrestrial applications.

Thrust-to-weight ratio: Rocket engines can generate very high thrust-to-weight ratios, which are essential for launching spacecraft or missiles. Gas turbine engines have lower thrust-to-weight ratios, but they are more reliable and easier to maintain.

In summary, rocket engines and gas turbine engines have different working principles, fuel types, efficiencies, altitudes, and thrust-to-weight ratios. Each type of engine is optimized for a specific set of applications, and their relative strengths and weaknesses depend on the specific requirements of the mission or operation.

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Is gas turbine and jet engine the same?

Gas turbine engines and jet engines are similar in many ways, but they are not exactly the same.

A gas turbine engine is a type of internal combustion engine that converts the energy from the combustion of fuel into mechanical energy through a turbine. The turbine drives a compressor, which compresses the air that enters the combustion chamber where fuel is burned to produce high-temperature, high-pressure gases. These gases then expand through the turbine, producing mechanical work that can be used to power generators, pumps, or other equipment.

A jet engine, on the other hand, is a type of gas turbine engine that is specifically designed to provide thrust for an aircraft. It works by taking in air at the front of the engine, compressing it, mixing it with fuel, and igniting it in the combustion chamber. The resulting hot gases then flow through a series of turbine blades, which extract energy from the flow and use it to drive the compressor and the fan (in the case of a turbofan engine). The exhaust gases then exit the engine at high speed, providing the thrust that propels the aircraft forward.

So, while a jet engine is a type of gas turbine engine, it is specifically designed to produce thrust for aircraft, whereas a gas turbine engine can be used for a variety of applications, including power generation and marine propulsion.

Compressors Gas Turbines and Jet Engines Pdf Free Download

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