Gas Turbine Engine Concepts
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A collection of key concepts and terminologies related to gas turbine engines, focusing on their functions, specifications, and operational processes.
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22 Terms
Intakes
Designed to accelerate the free air stream flow.
Electrical ice protection system
Utilizes heating elements that operate either continuously, intermittently, or part continuous-part intermittent.
Pressure ratio
The ratio between compressor discharge pressure and compressor inlet pressure.
Constant pressure combustion
Occurs in a turbo jet engine where combustion happens at a constant pressure.
Turbine efficiency range
Normal range of turbine efficiency is 70% - 85%.
Labyrinth seals
Fitted to gas turbine engines to form a gas-tight seal and retain oil in the bearing housing.
Low pressure fuel pump
Used in a gas turbine engine to maintain a vapour-free pressure from aircraft fuel tanks to the high-pressure fuel pump.
Air starter system
Provides a safer operation with no fire risk.
Gas turbine lubricating oils
Usually mineral-based.
Modular construction
Facilitates easy component change and rapid rebalancing.
Ram Ratio
The relationship between ambient pressure and compressor inlet pressure.
Energy in convergent type propelling nozzle
Gained due to high exit velocity.
Convergent-divergent intake
Most efficient engine intake for subsonic or low supersonic aircraft.
Combustion chamber flame temperature
Typically around 2000 °C.
Cooling air jacket
Used to insulate the jet pipe to protect the airframe.
Fuel pump plungers
Lubricated by the fuel.
Pressure regulating valve
In a hot air de-icing system, it protects against excessive depression.
Air starter supply
Usually comes from storage bottles carried in the aircraft.
Blade tip shrouding
Minimizes vibration and enhances efficiency.
Compressor surge
Occurs when all stages have stalled.
Ambient temperature
Considered when evaluating the efficiency of an engine's air intake.
Pressure-filter in lubrication systems
Incorporated to protect the pressure pump.
Note 
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