Turbine Engine Types

Turboshaft, Turboprop, Turbojet and Turbofan

Turboprop and Turbofan

Turboprop, Turbojet and Turbofan

Turboshaft, Turboprop, Ramjet and Turbofan

The ratio of the mass of air bypassing the engine core, to the mass of the air passing through the engine core.

The ratio of the mass of air bypassing the engine core, to the mass of the air passing into the engine core.

The ratio of the mass of air bypassing the engine case, to the mass of the air passing through the engine core.

The ratio of the pressure of air bypassing the engine core, to the pressure of the air passing through the engine core.

Both the turbine and reciprocating engine are internal combustion

Both the turbine and reciprocating engine are external combustion

Both the turbine and reciprocating engine are continuous cycle

Both the turbine and reciprocating engine produce similar thrust

A turbine engine combustion takes place at a near constant pressure, while in a reciprocating engine combustion takes place at near constant volume.

A turbine engine combustion takes place at a near constant volume, while in a reciprocating engine combustion takes place at near constant pressure.

A turbine engine combustion takes place at a near constant pressure, while in a reciprocating engine combustion takes place at near constant temperature.

A turbine engine combustion takes place at a near constant pressure, while in a reciprocating engine combustion takes place at near constant pressure.

A turboprop engine has an output shaft which drives a gearbox for a propeller while a turboshaft engine has an output shaft which drives a gearbox for something other than a propeller

A turboshaft engine has an output shaft which drives a gearbox for a propeller while a turbprop engine has an output shaft which drives a gearbox for something other than a propeller

It is mechanically completely independent of the other spools in the engine

It is mechanically completely dependent of the other spools in the engine

It is mechanically partially independent of the other spools in the engine

It is mechanically partially dependent of the other spools in the engine

The design flexibility of the layout, easier to start, the spools can run at their optimum speeds independent of each other and the ability to stop the propeller while the engine is still running

Easier to start, the spools can run at their optimum speeds independent of each other and the ability to stop the propeller while the engine is still running

The design flexibility of the layout, easier to start and the ability to stop the propeller while the engine is still running

The design flexibility of the layout, the spools can run at their optimum speeds independent of each other and the ability to stop the propeller while the engine is still running

Because only the high pressure turbine and compressor need to be rotated on start

Because only the low pressure turbine and compressor need to be rotated on start

Because only the low pressure turbine and ignitor need to be rotated on start

Because only the high pressure turbine and ignitor need to be rotated on start

The high pressure compressor (N2) section.

The high pressure compressor (N1) section.

The low pressure compressor (N1) section.

The low pressure compressor (N2) section.

The low pressure turbine(s)

The high pressure turbine(s)

An independent compressor, shaft, turbine combination

An dependent compressor, shaft, turbine combination

An dependent compressor and turbine combination

An independent compressor and turbine combination

A free turbine

A spool

A continuous cycle

A geared turbine

So that each can operate closer to their design rpm

So that each can operate closer to their design egt

So that each can operate closer to their design limits

So that each can operate closer to their design features

The first stage(s) of the compressor and the last stage(s) of the turbine are low pressure, while the last stage(s) of the compressor and the first stages of the turbine are high pressure

The first stage(s) of the compressor and the last stage(s) of the turbine are high pressure, while the last stage(s) of the compressor and the first stages of the turbine are low pressure

The intermediate pressure turbine

The low pressure turbine

The high pressure turbine

The low pressure turbine

The high pressure turbine

The intermediate pressure turbine

The compressor, combustion chamber, turbine and exhaust sections

Intake, the compressor, the combustion chamber, turbine and the exhaust nozzle

The compressor, combustion chamber, turbine and exhaust nozzle

4:1

2:1

3:1

5:1

A pure turbojet has no bypass air

A pure turbofan has no bypass air

0%

40%

80%

22%

Lower cost, easier maintenance

Shorter and lighter, better range/fuel consumption

Shorter and lighter, lower cost, easier maintenance

Lower cost, easier maintenance, better range/fuel consumption

Shorter and lighter, better range/fuel consumption

Lower cost, better range/fuel consumption

Shorter and lighter, easier maintenance

Lower cost, easier maintenance

AC electrical power and bleed air

DC electrical power

AC electrical power

DC electrical power and bleed air

To provide AC electrical power and pneumatic bleed on the ground, and in flight in the event of a main engine failure.

To provide DC electrical power and pneumatic bleed on the ground, and in flight in the event of a main engine failure.

To provide DC electrical power and pneumatic bleed on the ground, and in flight in the event of a main battery/generator failure.

To provide AC electrical power and pneumatic bleed on the ground, and in flight in the event of a battery/generator failure.

The driveshaft

The turbine

The compressor

The spools