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Turbine Engines TURBOJET The turbojet engine, developed for aircraft in the years prior to World War II, was a departure in think- ing from the standard piston engine. Instead of burning fuel in a confined space that is dependent upon pre- cise timing of ignition, the turbojet engine is essentially an open tube that burns fuel continuously. According to Newton’s Third Law (see “Newton’s Laws” in chap- ter 4, “Physics and Math”), as hot gases expand out from the rear of the engine, the engine is accelerated At the BURNER stage fuel is injected and ignited, raising the energy of the gas by raising it’s temperature. A typical engine will add about 2 lb fuel/second (s) for every 100 lb air/s. The energy of the gas increases dra- matically and is accelerated toward the turbine(s) due to the high pressure created by the compressor. Since these engines can produce temperatures well over the melting points of the materials used to make the tur- bine, only 12 to 25 percent of the air from the compres- sor is combusted while the rest cools the combusted gases down to temperatures just below that which would damage the turbine. The larger the difference between the temperature of gas at the turbine face and that of the outside air, the more thrust is created and the more efficient the engine. The next stage is the TURBINE. Here the heated gas passes over the turbine blades causing them to rotate and, in turn, to rotate a shaft that is connect- ed to the compressor. The turbine removes some energy from the flow to drive the compressor, but there remains sufficient energy in the gas to do work as it exits the nozzle. The purpose of the NOZZLE is to convert energy into velocity thus producing thrust. The nozzle allows the flow of hot gases to exit the rear of the engine until they reach free-stream pressure, which creates the thrust of the engine. Most nozzles restrict the flow somewhat before allowing it to expand. This creates additional pressure and thus, additional thrust. It also controls the mass flow through the engine, which along with the velocity, determines the amount of energy the engine produces. Overall, turbine engines have a much higher power- to-weight ratio than piston engines. They can operate at much higher temperatures and can produce much more thrust than propeller engines. However, they are less efficient at low speeds and low altitudes. Cutaway view of turbojet engine. in the opposite direction. The engine consists of three main parts, the compressor, the burner, and the tur- bine, along with the inlet, shaft, and nozzle, as shown above. A large mass of air enters the engine through the INLET and is drawn into a rotating COMPRESSOR. There are two types of compressors, centrifugal and axial. The axial type is shown above. The compressor raises the pressure of the air entering the engine by passing it through a series of rotating and stationary blades. As the gas is forced into smaller and smaller volumes, the pressure of the gas is increased. The gas also heats up as its volume is decreased by the com- pressor. Today’s compressors can have a compression ratio of over 40:1, much higher than a piston engine. Also, in order to maximize the engine’s performance, turbojets will have two different compressors operat- ing on different shafts: a low-pressure compressor fol- lowed by a high-pressure compressor. 16PDF Image | NASA Guide to Engines
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