Two Shaft Gas Turbine Power Plant (SMT-HT-48)

availability: in stock

Specifications:
Touch LCD with GUI Interface for better monitoring and accurate measurement of Plant variables.
Experiments relating to the function and behaviour during operating of a gas turbine in a two-shaft
arrangement.
Operation with power turbine and generator.
Asynchronous motor with frequency converter as generator.
Start-up fan to start the high-pressure turbine.
Conversion of generated electrical energy into heat using four 600W braking resistors.
Effective silencing at intake and exhaust for laboratory operation.
Sensors record all relevant data visualised on displays in the process schematic.
Uses industrial parts, powered by kerosene for realistic tests and results
ESOLS DAQ Software for monitoring and control.
Technical Specifications:

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Description

The SMT-HT-48 trainer helps to study the behaviour of Two shaft Gas Turbine Power Plan. In
this system one turbine (the high-pressure turbine) drives the compressor and the other
turbine (the power turbine) supplies the effective power. The trainer includes the following
components: compressor, tubular combustion chamber and high-pressure turbine; fuel
system; starter and ignition system; lubrication system; power turbine; generator; and
measuring and control equipment. The complete unit is called gas turbine.
The gas turbine works as an open cyclic process, with the ambient air being drawn out and
fed back in. The high-pressure turbine together with the compressor and the combustion
chamber are called gas generator as they produce the required gas for the power turbine. To
do so, the ambient air drawn in is brought to a higher pressure in the single-stage radial
compressor. When the air enters the combustion chamber, only part of it is used for
combustion. This air is decelerated with the aid of a turbulence generator such that the added
fuel is able to burn with a stable flame. The greater portion of the air is used to cool the
combustion chamber components, and is mixed into the combustion gases at the end of the
combustion chamber. This reduces the gas temperature to the permissible inlet temperature
of the high-pressure turbine.