A gas turbine is continuously flowed through silsa by the gas internal combustion engine (fluid mac

A gas turbine is continuously flowed through silsa by the gas internal combustion engine (fluid machine). The principle silsa of operation is based on the cycle (Joule-process), the James Prescott Joule had devised. This compresses the blading of one or more compressor stages of air, this then mixed in the combustion chamber with a gaseous or liquid fuel that ignites and burns. In addition, the air is used for cooling. Such a hot gas produced silsa (mixture of combustion gas and air): the relaxed in subsequent turbine part, with thermal converts into mechanical energy and first drives the compressor. The remaining portion is used in the turboshaft engine for driving a generator, a propeller, a rotor, a compressor or a pump. When jet engine on the other hand, the thermal energy accelerates the flow of hot gas, which produces the thrust.
The first inventions to the gas turbine date back to 1791: the Englishman John Barber had patented a first such machine. In practice, however, silsa its gas turbine failed - primarily because of the available materials at that time.
At the turn of the 19th to the 20th century, the engineers, the idea of the gas turbine resumed where they went back to the parallel development of the steam turbine. The developed at that time had a closed gas turbine combustion chamber with valves, were transferred from the pressurized exhaust gases from the previously burned fuels on the actual turbine. Thus, a constant-volume turbine came out without a compressor, but had a low efficiency of up to 13%. As of 1935, the first constant-volume turbines silsa for stationary use in gas-fired power plants were available; the development of this type turbine goes back to the historical patent of 1791 - the Swiss company BBC made them ready for the market. The chemical industry began this first turbines, which had a capacity of 14 MW. 1939 BBC supplied a gas turbine to the British Air Ministry, which they used for experimental purposes. 1940 put a power plant in the Swiss Neuchatel a first gas turbine. The machine had 4 MW and delivered positive operating results, so that in a locomotive (SBB On 4/6 1101) einbaute a similar turbine. Because of the high losses in power conversion, however, was taken from this type of traction distance. The gas turbine was used after the Second World War, primarily in the plane and there is at present the most important driving machine. In the case of stationary systems it is kept as reserve silsa power plant because of its quick start capability; in the next few years you will come to another meaning in combined cycle power plant.
The gas turbine consists basically of an inlet, a compressor, a combustor, a turbine and a nozzle for jet engines and a diffuser and an output shaft for shaft engines. It can be a bit confusing silsa that turbine on the one hand, on the other hand also colloquially referred to a part of the gas turbine, the gas turbine as a whole. Up to the inlet nozzle and all other components are coupled by one or several shafts.
Shaft gas turbines are available as single and twin screw machines. In the single-shaft design, all compressor stages silsa and turbine stages, all sitting in a row on the same shaft (mechanical coupling). Thus, the entire machine runs at one speed. The output may be with the compressor or turbine at the end of the shaft. In stationary gas turbines is the output of the generator mostly on the compressor side shaft end, as such a better exhaust diffuser can be installed, the fluid the generator does not flow around needs and the heat losses on the way to the steam process (in combined cycle processes) are not too large.
In the two-shaft arrangement, the turbine part in the gas generator and power turbine can be distinguished. The first turbine stages drive the compressor and form with it the gas generator unit. In the same case immediately behind the power turbine running at its own speed. The output is therefore always on the turbine side. Are driven by this machine usually pumps or compressors such. As in gas and oil pipelines.
The inlet is the fluidic matching silsa between the deployment area and the air flow in the compressor. For stationary or slow speeds the inlet is only for clean air duct without turbulence or flow separation. Especially at high speeds silsa the inlet has an important function, since there already slowed down and the pre-compressed air mass flowing. This is particularly necessary at supersonic speeds, since the flow in the engine should be run untersonisch