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MiniLab™ Gas Turbine Lab

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

Mini Lab

Click image to enlarge

A National InstrumentsTM 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

Engine inlet

                   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 models of all primary 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 engine and alert the operator to the problem. 

On-Board Jet Engine Data Acquisition (click image to enlarge)

On-Board Jet Engine Data

The pre-installed MiniLab™ Interactive Virtual Instrument (VI) Panel displays and records pertinent engine data for follow-on study. This LabVIEWTM 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 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 for later retrieval and analysis and the VI code is even open for user programming and customization!

An engine cut-away model is also available. 

SR30 Turbojet Engine Cut Away

                                                                             SR30 Turbojet Engine Cutaway Model

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. 

Click on image below to view a sample lab procedure

Mini-Lab Technical Papers

 Sample Technical Papers

PDF icon  United States Naval Academy
EA 429 Propulsion Course
PDF icon  Fuel-Thrust Dynamics of a Gas Turbo Engine
Universidad Autonoma de Nuevo Leon, Mexico
 PDF icon University of Minnesota Undergraduate Student Laboratory Procedure
  Thermal EnergyTechnology Semester Group TE6-604 Modelling and Validation of the SR30 Turbojet Engine, Aalborg University   Wentworth Institute of Technology Design and Implementation of a data acquisition platform on a legacy gas turbine system    
PDF icon  "Design, Implementation, and Evaluation of a Passive Thrust Augmentation Device for the SR-30 Turbojet" 
University of Stuttgart, Germany
PDF icon  University of California, Chico Undergraduate Lab Procedure
University of California, Chico
 PDF icon Boston University Undergraduate Student Laboratory Procedure
Boston University
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Recycled Fuel Performance in the SR-30 Gas Turbine
John Brown University
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2000 Annual Technical Report
Stanford University
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Research on Small Turbojet Engines
Royal Military Academy of Belgium
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Characterizing the Performance of the SR-30 Turbojet Engine
University of Minnesota
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On-Line Validation of Measurements on Jet Engines Using Automatic Learning Methods
University of Liege
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Engine Mapping and Water Ingestion in the SR-30 Turbojet
Royal Military Academy, Belgium
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Brayton Power Cycle Experiment – Jet Engine
University of Toledo
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Gas Turbine Experiment and Instrumentation Design
University California Davis
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AME 40431: Gas Turbine Propulsion
Notre Dame Lab
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Design of a Comprehensive Condition Monitoring System for Gas Turbine Engines
Ryerson University  
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Development of a Jet Engine Experiment for the Energy Systems Laboratory
ASME IMECE 2003 Paper Kettering University
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Soft Computing Applications on SR-30 Turbojet Engine
NASA Marshall & University of Alabama Paper
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Development of a Combined Cycle Gas Turbine/Steam plant for Training Marine and Power Engineers
Maine Maritime Academy ASME Expo 2007
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Activities Around the SR -30 MiniLab at PSU
Penn State 
PDF icon    Midwave Infrared Imaging Fourier Transform Spectrometry of Combustion Plumes- Dissertation
Air Force Institute of Technology
PDF icon  SR-30 Small Turbojet Engine Laboratory
United States Naval Academy
PDF icon  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

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

Mini Lab
CAD Models 
Spray View
Hush Kit

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

Sixteen years ago, Wentworth Institute of Technology in Boston acquired a MiniLabTM Gas Turbine Power System from Turbine Technologies, Ltd.  The...

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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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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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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