Turbo-Jet Trainer with Reheat Manufacturer,Supplier and Exporter in India
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Product Code : SCL-CELE-13935
The trainer is built on a thick sheet steel frame and uses a
single-shaft gas generator, simulating a common design for jet propulsion.
1. Gas Generator Cycle
- Intake: Air
enters an air box, passes through a calibrated nozzle, and into a radial
flow compressor.
- Combustion: The
compressed air moves into the combustion chamber where high-quality
aviation kerosene is pumped and sprayed. A high-energy spark
initiates combustion.
- Turbine: Hot
gases flow through a radial flow turbine (driving the compressor),
then to the reheat section.
- Performance:
Maximum continuous speed is approximately 100,000 revolutions per
minute, and approximate maximum thrust is 50 Newtons.
2. Reheat (Afterburning) System
- Mechanism: After
leaving the main turbine, the hot exhaust gases still contain some
residual oxygen. A separate fuel flow control valve and a second
high-energy spark ignite additional fuel sprayed into the reheat
section.
- Effect: This
process (afterburning) creates a secondary burn, which
significantly increases the temperature and velocity of the gas,
thereby increasing thrust.
3. Exhaust and Control
- Nozzle: The
reheated gas passes through a variable area propelling nozzle,
allowing students to study its direct effect on thrust.
- Control:
Engine speed is regulated by a fuel flow control valve on the panel.
Reheat fuel flow is controlled separately.
- Safety: A PLC
module manages automatic startup and shutdown, and includes safety
interlocks that shut down the turbine upon errors like incorrect speed,
ignition failure, or oil pressure failure.
Instrumentation and
Data Analysis
The trainer is fully instrumented for accurate data logging
and analysis, with both digital and analogue indicators on the control panel.
|
Measured Parameter |
Instrumentation Detail |
|
Performance |
Shaft speed, Thrust, Fuel flow, Nozzle area, Total hours
run |
|
Process Variables |
Pressures and Temperatures at key
points (inlet, compressor, combustion, reheat) |
|
Ancillary System |
Oil temperature and pressure, Fuel level and pressure |
|
Data System |
Connects to a computer (via USB, includes software) for
display, graphing, and analysis of all relevant variables. |
|
Emissions |
Typical readings for Carbon Dioxide (1.8 – 2.9 percent),
Carbon Monoxide (240 – 900 ppm without reheat; up to 1700 ppm with reheat),
and Nitrogen Oxides (NOx). |
Experiments and Educational Capabilities
The equipment is designed for advanced practical
investigations into gas turbine thermodynamics, performance, and propulsion:
- Propulsion
Analysis: Measuring thrust with and without reheat and
analyzing how the variable area nozzle affects thrust.
- Efficiency:
Determining specific thrust and fuel consumption (key metrics) and
calculating thermal, propulsive, isentropic, and mechanical
efficiencies.
- Cycle
Analysis: Investigating pressure losses and ratios across
the compressor and turbine, and calculating work and power
delivered by the engine.
The system requires significant services, including a 220-230
V single-phase electrical supply, cold water supply (at least 18 liters per
minute), and a heat-resistant exhaust duct system.
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