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Monday, December 22, 2014

MiniLab™ Gas Turbine Lab

The Mini Gas Turbine Power System is a self-contained jet engine laboratory featuring the purpose built SR-30 Turbojet engine. All aspects of gas turbine theory, fluids and thermodynamics are easily demonstrated and readily explored.

All engine systems are fully integrated in the MiniLab™ cabinetry. The MiniLab™ educational gas turbine lab is easily rolled to any convenient location. No dedicated test cell or facilities modifications are required. The time between uncrating and first run is measured in minutes. The included data acquisition system makes real-time engine data display and recording effortless.

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 safely stop the engine and alert the operator to the problem. No specialized jet engine training is required to operate the MiniLab™.

CAD models & material properties are available.  No other system offers actual electronic models for such activities like CFD/ FEA analysis, or velocity vector calculations.  

On-Board Jet Engine Data Acquisition  (Click to Enlarge)

Mini Lab Data Screen

Jet engines create a tremendous sound when operating. The SR-30™ engine powering the Mini-Lab™ is no exception! However, you can’t look into it to see what’s happening. Enter the included MiniLab™ Interactive Virtual Instrument (VI) Panel. This LabVIEWTM generated VI offers a real-time graphical perspective of the engine operation which offers a new dimension in the operators’ total experience. All engine operating parameters are displayed as they occur, with system locations clearly indicated 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 jet 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 in computer for later retrieval and analysis and the VI code is even open for manipulation!

As the original engine manufacturer, Turbine Technologies, LTD offers unparalleled end-user support. In use at over 200 colleges, technical training and military installations worldwide.  MiniLab™ is the proven leader in Gas Turbine Education. 

Mini Lab Gas Turbine Lab teaching toolTurbine Technologies' MiniLab™ is a world-class educational gas turbine lab. Designed to provide a rare educational experience, MiniLab™ offers students an extremely exciting opportunity- operation of a real jet engine!   

MiniLab's™ true "stand-alone" design enables operation within 10 minutes of uncrating . As the original engine manufacturer, Turbine Technologies does not rely on the availability of surplus parts, or engines and is therefore able to offer first class customer support.         

MiniLab's™ cabinet houses TTL's SR-30 engine and all necessary accessories- including fuel and oil tanks, pumps, motors, operator instrumentation, sensors, transducers and data acquisition hardware. On-screen data display and replay capability enable a new world of computational opportunities- ranging from high school basics to graduate level thermodynamics theory.         

MiniLab ™ - turnkey, portable and affordable. In operation at schools worldwide for well over two decades.

Turbine Technologies, Ltd. has recently announced the addition of a new software piece that will enhance the educational experience offered by our ful...

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Wisconsin’s 75th District Representative, Roger Rivard, recently took time out of his busy schedule to visit Turbine Technologies, Ltd. (TT...

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Mr. Thanesvorn Siri-achawawath, Innovative Instruments Company’s sales manager, from Bangkok, Thailand recently completed turbojet engine operat...

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Professor Lasse Rosendahl, Ph.D., of Aalborg University in Denmark, recently acquired Turbine Technologies’ (TTL) new software offering to facilitate Computational Fluid Dynamics (CFD) and bio-fuels combustion studies.

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TTL released a story through various media outlets which focused on its’ MiniLab™ Gas Turbine Power System being utilized for Bio-Fuels Research.

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While developing the TurboGen™ Gas Turbine Electrical Generation System, Turbine Technologies, Ltd. determined their most ambitious educational lab system design to date should feature the latest onboard data acquisition and virtual instrument panel systems. 

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Magazine article about the Gas Turbine Lab published in Aero International Download the complete Article Here (PDF Format)
Turbine Technologies, Ltd. (TTL) has announced the shipment of its very first commercially configured TurboGen™ Gas Turbine Electrical Generation System to Perm State Technological University in Moscow, Russia.

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Sometimes, it pays to know your neighbors. Sun Power Bio-Diesel of Cumberland, WI is a producer of cold-flow canola-based bio-diesel fuel.

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Turbine Technologies, Ltd. (TTL) is on track for April delivery of its new TurboGen™ gas turbine electrical power generating station.

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MiniLabTM Product Summary

  • Complete Educational Jet Propulsion Power System
  • Suitable for Secondary, University, Technical and Military Education and Training
  • Purpose Built Gas Turbine Engine Designed and Manufactured to Aerospace Standards
  • Integrated Test Cell ~ Requires No Facilities Modification
  • All Key Engine Stations Fully Instrumented for Temperature and Pressure Measurement
  • Most Stable and Reliable Operation of any Engine in Size and Thrust Class
  • Fully Instrumented Operator Control Panel Featuring OneTouchTM Automatic Start
  • DigiDAQTM 
  • Data Acquisition System Utilizing USB Technology
  • User Configurable Real Time Computer Data Display
  • Designed to Meet ABET Criterion 4 and 6 Objectives
  • Supplied with a Comprehensive Operator’s Manual, Checklists and Safety Instructions
  • Industry Leading Warranty with Unsurpassed End-User Support
  • Designed and Manufactured in the USA

Click on the PDF's below to learn more about MiniLabTM Specifications:

CAD Models 




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
  United States Naval Academy
EA 429 Propulsion Course
  Fuel-Thrust Dynamics of a Gas Turbo Engine
Universidad Autonoma de Nuevo Leon, Mexico
  University of Minnesota Undergraduate Student Laboratory Procedure
  "Design, Implementation, and Evaluation of a Passive Thrust Augmentation Device for the SR-30 Turbojet" 
University of Stuttgart, Germany
  University of California, Chico Undergraduate Lab Procedure
University of California, Chico
  Boston University Undergraduate Student Laboratory Procedure
Boston University

Recycled Fuel Performance in the SR-30 Gas Turbine
John Brown University

2000 Annual Technical Report
Stanford University

Research on Small Turbojet Engines
Royal Military Academy of Belgium

Characterizing the Performance of the SR-30 Turbojet Engine
University of Minnesota

On-Line Validation of Measurements on Jet Engines Using Automatic Learning Methods
University of Liege

Engine Mapping and Water Ingestion in the SR-30 Turbojet
Royal Military Academy, Belgium

Brayton Power Cycle Experiment – Jet Engine
University of Toledo

Gas Turbine Experiment and Instrumentation Design
University California Davis

AME 40431: Gas Turbine Propulsion
Notre Dame Lab

Design of a Comprehensive Condition Monitoring System for Gas Turbine Engines
Ryerson University  

Development of a Jet Engine Experiment for the Energy Systems Laboratory
ASME IMECE 2003 Paper

Soft Computing Applications on SR-30 Turbojet Engine
NASA Marshall & University of Alabama Paper

Development of a Combined Cycle Gas Turbine/Steam plant for Training Marine and Power Engineers
Maine Maritime Academy ASME Expo 2007

Activities Around the SR -30 MiniLab at PSU
Penn State 
    Midwave Infrared Imaging Fourier Transform Spectrometry of Combustion Plumes- Dissertation
Air Force Institute of Technology
  SR-30 Small Turbojet Engine Laboratory
United States Naval Academy
  DynJet, A MatLab Program for Calculating Steady-State Performance of One-Spool Turbojet Engines
Israel Institute of Technology
   Georgia Tech AE3051Lab.pdf
Georgia Institute of Technology

Experimental Opportunities

Experimental and research opportunities include scientific, engineering, thermodynamic and environmental investigations. With a wide array of sensors, experiments relating to secondary education physics and chemistry through graduate level fuels and combustion research are readily performed. Standard courses in engineering thermodynamics and fluid mechanics benefit from textbook direct examples conducted and measured in real time. The limitations of theoretical models and the variability of experimental technique can be experienced first hand. In addition to academics, the MiniLab™ is ideally suited for general gas turbine familiarization and jet engine operational training for aviation and military professionals.

Examples of Gas Turbine computations ~

With measured values of compressor inlet temperature and pressure, turbine inlet temperature and pressure, turbine exit temperature and pressure, fuel flow and inlet and exit areas, possible calculations include:

  • Compressor Analysis - compressor pressure ratio, power required, rotational speed and compressor efficiency
  • Turbine Analysis - work and power developed, expansion ratio and turbine efficiency
  • Cycle / Brayton Type Analysis - mass flow rate, inlet and exit velocity, station temperature and pressures, combustion and thermal efficiency, specific fuel consumption and power / thrust developed
  • Combustion Analysis - excess air and fuel-air ratio
  • General Analysis - diffuser and nozzle performance and efficiency

Jed E Marquart, PH.D., PE Ohio Northern University"MiniLab™ is an extremely exciting teaching tool… a one of a kind device for the demonstration and study of gas turbine power!"

Jed E. Marquart, Ph.D., P.E.
Professor of Mechanical Engineering
Ohio Northern University