Which three main sections comprise a gas turbine engine?

A gas turbine engine fundamentally consists of three integral sections: the compressor, combustion chamber, and turbine.

The compressor is responsible for drawing in air and compressing it to a high pressure. This compressed air is critical for efficient combustion, as it allows for a more powerful reaction when mixed with fuel. The combustion chamber is where the actual burning of fuel occurs, significantly raising the temperature and pressure of the air-fuel mixture. This high-energy gas is then directed into the turbine section.

The turbine is where energy extraction happens; the high-energy gases expand through the turbine's blades, causing them to spin. This spinning motion, in turn, drives the compressor, creating a continuous cycle. The design and function of these three sections work together seamlessly to produce thrust in gas turbine engines, making them highly efficient for aviation and other applications.

The other options listed do not encapsulate the essential sections of a gas turbine engine. For example, while air intake and exhaust are relevant to the overall operation, they do not constitute the main sections that define the engine's cycle and functionality. Fuel control, fuel pump, and ignition components, while crucial to engine operation, are not categorized as the primary sections of the engine structure itself.