Creating Innovative Laboratory Systems For Engineering & Technical Education

MiniLab™ Gas Turbine Engine Lab

MiniLab™ is a self-contained turbojet engine test cell for small jet engine technology. Utilized by hundreds of leading educational institutions, the included SR30 turbojet engine offers exciting teaching opportunities in applied thermodynamics and jet propulsion.

A National Instruments™ based data acquisition system displays and records compressor inlet temperature and pressure, turbine inlet temperature and pressure, turbine exit temperature and pressure, thrust and fuel flow and makes possible studies of:

  • Brayton Cycle
  • Compressor Performance
  • Turbine Performance - work & power, expansion ratio, turbine efficiency
  • Combustion/Emissions Analysis

Contact us to learn more or request pricing below. 

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Turbine Technologies' SR30 Turbojet Engine

All engine support systems are fully integrated. The system is easily rolled to any convenient location. No dedicated test cell or facilities modifications are required. The time between delivery and first run is measured in minutes. The included data acquisition system makes real-time engine data display and recording effortless. CAD model of all primary turbojet engine components are also available, along with their flow-cavity negatives, to support CFD, FEA, or other turbomachinery related analysis

Equipped with the OneTouch™ Auto Start System, virtually anyone can operate the MiniLab™. Start sequencing is completely automatic with all critical engine parameters monitored during operation. In the unlikely event of an engine fault, the OneTouch™ system will stop the turbojet engine and alert the operator to the problem.

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On-Board Small Jet Engine Data Acquisition

The pre-installed MiniLab™ Interactive Virtual Instrument (VI) Panel displays and records pertinent turbojet engine data for follow-on study. This LabVIEW™ generated VI offers a real-time graphical perspective of engine performance. All engine operating parameters are displayed clearly on the engine cutaway graphic.

Engine pressures, temperatures and fuel flow are displayed in digital data windows. Engine RPM and thrust are displayed on analog-style round meters for a neat visual cue (the readings are also displayed digitally below each meter).

The real-time plotting feature lets the operator plot any parameter on screen as it occurs to provide a clear sense of how the data is reacting to the actual system operating conditions. Operators can toggle between all the parameters to watch them graphically. Data logging functionality is conveniently controlled from the VI screen. All the turbojet engine power data can be observed and tracked through its full throttle range. System units can be changed with a simple click of the mouse. Feeding this interactive VI is data from the on-board National Instruments 6218 Data Acquisition System. That same data is also stored for later retrieval and analysis and the VI code is even open for user programming and customization!

A turbojet engine cut-away model is also available.

As the original engine manufacturer, Turbine Technologies, LTD offers unparalleled end-user support. In use at hundreds of colleges, technical training and military installations worldwide. MiniLab™ is the proven leader in Gas Turbine Education.

Technical Papers


Purchase Specifications
  • A complete gas-turbine power system to consist of an engine designed and manufactured for engineering education.
  • Engine must utilize a centrifugal flow compressor, reverse flow annular combustor and an axial flow turbine stage.
  • Engine to be of current manufacture and consisting of all new components.
  • All engine components either vacuum investment cast or precision CNC machined.
  • All high-heat components manufactured from 17-4 ph stainless steel, Inconel® 718 or CMR 247 Super Alloy.
  • Traceable and verifiable material to be used throughout engine.
  • All elements comprising the system to be contained in a rigid steel chassis mounted on rolling castors.
  • All system metal surfaces to be stainless steel, anodized or powder coated to promote durability and wear resistance.
  • Complete system not to require any permanent facility modifications or additions.
  • Engine situated behind transparent protective shields allowing clear view during operation.
  • Operator capable of manual control throughout entire range of operation.
  • Operator panel to consist of digital TIT, EGT, and RPM indicators, analog oil pressure, engine pressure ratio, fuel pressure and air pressure gauges, keyed master, green start, red stop and T-handled power control lever.
  • System to be equipped with calibrated transducers and thermocouples capable of measuring compressor inlet, compressor exit, turbine stage inlet, turbine stage exit and thrust nozzle exit temperature and pressures, fuel flow, thrust and engine compressor / turbine rotational speed.
  • Engine thrust to be measured by a load cell permitting direct indication of thrust value.
  • To be supplied with a USB based digital data acquisition system complete with computer and user configurable data acquisition software capable of measuring and recording analog, digital and frequency signals.
  • Fully automatic engine start and operational health monitoring system provided with LCD status readout and cumulative runtime and cycle count.
  • Representative engine components and technical data optionally available for teaching use and training aids.
  • Manufacturer to guarantee spares availability and provide technical support services for core engine and power system.
  • Provided with a comprehensive Operator’s Manual. Provided with summary operating checklist for all operating conditions.
  • Provided with safety instruction to address all operating conditions.
  • To be covered by a free two year warranty