In a rocket engine, the fuel and the oxidiser are stored in the propelling body. The rocket can function in a vacuum and is the only device capable of space flight.
Rockets may be of the single-stage or multi-stage type, consisting of one or more rocket motors. They may be solid propellant or liquid propellant rockets.
Figure 17.6 shows the line diagram of a liquid propellant rocket engine using liquid oxygen and refined petrol. It consists of a fuel tank, oxidiser tank, gas turbine, pumps, combustion chamber, and nozzle. Pumps are used to supply propellants to the nozzle at high pressure to obtain higher thrust. These pumps are operated by a gas turbine where the high pressure and high temperature gases formed by the fuel and oxidiser are delivered to the gas turbine.
The properties for an ideal propellant are high calorific value, high density, high stability, ease of handling and storing, non-corrosive, and high boiling point at low pressure.
Rockets find important applications in the field of long range artillery, lethal weapons, signalling and fireworks, jet assisted take-off, satellites, space ships, and research. They are suitable for pilotless operation.
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