Description
A self-contained, fully instrumented, educational single shaft gas turbine with reheat. Powered by kerosene, the experimental abilities of this high-quality apparatus enable comprehensive practical investigations into the principles, and performance of single-shaft gas turbines with reheat. This product helps students to understand the use of this ‘engine’ with additional exhaust nozzle control, on practical applications such as jet aircraft. A steel frame holds a gas generator, combustion chamber, oil and fuel tanks, pumps, ancillaries and guards. Above these is an instrumentation and control panel with schematic diagram. The clearly labelled control panel with mimic diagram includes the instrument displays, controls and warning lights. Air passes into an air box, through a calibrated nozzle into a compressor, then into the combustion chamber. A pump transfers fuel from the fuel tank to spray through a special nozzle into the combustion chamber. A high-energy spark ignites the air and fuel mixture, that flows to a radial fl ow turbine, then to the reheat section. This increases the temperature and velocity of the gas. It then passes through a variable area propelling nozzle. The exhaust gases then discharge to a suitable exhaust system. The combustion chamber gives excellent combustion, low pressure loss and good flame stability over a wide range of conditions. A fuel flow control valve on the instrumentation and control panel regulates the turbine speed. This design reduces the possibility of overspeed. A separate control adjusts the fuel fl ow to the reheat section. A second high-energy spark in the reheat section ignites the reheat fuel. This creates a secondary burn (or afterburn), using some of the remaining oxygen in the hot exhaust gases leaving the turbine. The equipment has an oiling system including filters and water-cooled oil. A PLC (programmable logic controller) controls the turbine start up and shut down. For protection of the equipment and user, it shuts down the turbines if the user makes an error. It also switches on cooling fans after running. Digital and analogue indicators show all the important readings from the sensors around the equipment, such as pressures, temperatures, fuel fl ow and level. This equipment connects to your computer (computer not supplied) and includes dedicated, user-friendly data acquisition software. This allows students to display, graph and analyse all relevant variables, and save their results for later analysis. The data acquisition system includes adaptors and leads, and the software is supplied on CDROM. Supplied with the equipment is a detailed textbook that covers the theory and use of gas turbines.
Learning Outcomes
- Turbine, reheat and nozzle tests to find key performance information such as:
- Specific thrust and fuel consumption
- Pressure losses and ratios
- Thermal, propulsive, isentropic and mechanical efficiencies
- Work and power
- Thrust with and without reheat
- How the variable area nozzle affects thrust
Specifications
- Nett Dimensions and weight: 1385 mm (wide) x 1200 mm (depth) x 1721 mm (height) and 260 kg (with no fuel or oil)
- Approximate packed dimensions and weight: 3.8 m3 and 450 kg
- Fuel: High-quality aviation kerosene: ASTM D 1655 Jet A or similar
- Lubricating oil: SAE 10W-40 multigrade turbo diesel oil
- Gas generator turbine:
- Maximum continuous speed:
- Approximately 100000 rev.min–1
- Approximate Maximum Thrust: 50 N
- Note: Local operating conditions, such as air and fuel quality will affect maximum thrust.
Instruments:
- Shaft speed
- Pressures
- Temperatures
- Thrust
- Fuel flow, level and pressure
- Oil temperature and pressure
- Nozzle area
- Total hours run
Automatic shut down conditions:
- Ignition failure
- Incorrect turbine speed
- Oil pressure failure
- Water supply failure
- Incorrect temperatures
Exhaust emissions (typical):
- Carbon dioxide (CO2): 1.8 – 2.9%
- Carbon monoxide, (CO): 240 – 900 ppm*
- Nitric oxide, (NO): 11 – 26 ppm
- Nitrogen dioxide, (NO2): 0 – 1 ppm
- Combination of NO and NO2, (NOX): 12 – 26 ppm
- Sulphur dioxide, (SO2): 5 – 6 ppm
- *Note: with reheat on, the CO levels can increase to
- 1700 ppm at a low engine speed.
Operating Conditions
Operating Enviroment:
- Dry and well-ventilated engine test laboratories
Storage Temprature Range :
- –25°C to +55°C (when packed for transport)
Operating Temprature range:
- +5°C to +35vC
- Note: The fl ash point of kerosene can be as low as 37°C, so keep your working environment below 35°C.
- Operating relative humidity range:
- 30% to 95% (non-condensing)
