ASTB-12 Jet Engine
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ASTB-12 Jet Engine Axial Gas Turbine
The ASTB-12 Jet Engine Lab Equipment is an axial flow gas turbine system designed for practical educational purpose. The system consists of a Micro Gas Turbine Engine (MGTE) integrated with sensors and Data Acquisition System (DAQ). An Electronic Engine Controller continuously monitors the engine to ensure safe operating limits of the engine. A computer based software is used to manage the engine for real time data acquisition.
ASTB-12 Jet Engine SPECIFICATION
- Thrust: 150N
- Exhaust Gas Temperature (EGT): 550 – 750°C
- Starting: Automatic Starting Sequence
- Compressor Type: Single Stage Radial
- Typical Fuel: Kerosene, Jet A-1, JP-4, JP-5, JP-8, Sustainable aviation fuel
- RPM: 33000 @ Idle, 110,000 @ Max
- Compressor Pressure Ratio: 2.2 @ Max RPM
- Turbine Type: Single stage Axial
- Lubrication: 5% Turbine Oil Mixed with Fuel
- Mass flow: 0.35 kg/s
- Engine Diameter: 110 mm
- Length: 245 mm
- Engine Weight: 1.7 kg
- Maintenance interval: 25 H
- Ignition System: Glow plug
- Ignition Type: Propane / Kerosene
KEY FEATURES OF LAB EQUIPMENT
- Complete aeronautical axial gas turbine engine
- Real time thrust measurement
- software controllable throttle setting with safety limits
- Real time fuel metering system
- Transparent safety housing for protection while engine is visible to students
- Standard graph plotting, display parameters and data logging features for analysis
- Microprocessor based fully automatic ECU (Engine Control Unit)
PHYSICAL SPECIFICATIONS OF LAB EQUIPMENT
- Length: 0.9m
- Width: 0.5m
- Height: 0.4m
- Trolley Height: 0.8m
- Overall Height: 1.2m
ELECTRICAL SPECIFICATIONS OF LAB EQUIPMENT
- AC Supply : 110/220 VAC 60/50 Hz
- Power Consumption: 200 W
- DC Supply: 12V 10AH / 11.1V 3S LIPO
OPERATING SYSTEM REQUIREMENT
- Windows 10 Or Above
- 10 GB of HD
- 4 GB RAM
- LAN port
- USB Port
INSTRUMENTS INCLUDED (FOR DATA READING)
The Jet Engine to enhance your Lab
Nozzle Area
- Exit Total Temperature
- Fuel Flow
- Shaft Speed (RPM)
- Thrust
Compressor Stage
- Exit Total pressure
- Exit pressure
- Exit total temperature
Inlet Duct (Air Intake) Stage
- Inlet Pressure
- Inlet temperature
Turbine Stage
- Intel total temperature
- Inlet total pressure
- Exit total temperature
- Exit total pressure
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