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
Description
A complete gas turbine power plant designed for engineering, technical and military education as well as advanced research and study. The core gas-generator is representative of all major gas turbine types and permits ready textbook direct analysis of air equivalent Brayton and Gas Turbine cycles. Students are able to apply fluids, thermodynamic, combustion and gas turbine theory to the operation of an actual engine. Laboratory experience gained with the MiniLab™ is directly applicable to aero and marine turbine propulsion and industrial gas turbine applications.
The SR-30 Turbo-Jet engine is designed and manufactured by Turbine Technologies, LTD specifically for the MiniLab™ Gas Turbine Power System. The compact engine features a centrifugal flow compressor, reverse flow annular combustor and an axial flow turbine stage. The SR-30 follows the fundamental gas turbine cycle: Ambient air enters the engine through the bell shaped inlet. The air is then compressed, diffused and directed into the combustor can. Kerosene based fuel, introduced via six high-pressure atomization nozzles, is mixed with the compressed air and ignited. Heated combustion gas expands and accelerates through the vane guide ring causing the turbine to rotate. Useful work is extracted from this rotation as the turbine powers the compressor. The combustion gases are further accelerated through the thrust nozzle where the remaining heat energy is converted to kinetic energy in the form of jet thrust. The ejected gas returns to ambient atmospheric conditions thereby completing the thermodynamic cycle.
For safety and performance reasons, no off-the-shelf, former military or surplus components are used in any portion of the engine. All components are manufactured in-house to exacting specifications. Electronic controlled vacuum investment casting insures void and impurity free components. Computer numerically controlled machine centers maximize finished part accuracy. Individual component materials are selected based upon desired mechanical properties, durability and longevity. Combustor components and the vane guide ring utilize Inconel® 718 alloy. The integral bladed disk turbine wheel is manufactured from CMR 247 Super Alloy. All material is fully traceable and verified to possess the desired properties specific to the application. The completed engine undergoes rigorous final operational testing and inspection. Purpose built from the start, the SR-30 requires no questionable modifications prior to integration into the MiniLab™ Gas Turbine Power System.
The MiniLab™ cabinetry is composed of a rigid steel chassis mounted on rolling castors for portability and ease of storage, requiring no permanent facility modifications or additions. The SR-30 engine is securely mounted within the cabinet behind protective transparent polycarbonate shields affording the operator and observers clear, unimpeded viewing of the engine during operation. All engine accessories including fuel and oil pumps are located in the lower portion of the cabinet. No dedicated engine accessory drive is required, thereby eliminating the distraction of non-essential engine loading considerations in thermodynamic and performance analysis. Safe and reliable air starting provides for consistent and easy engine operation without the need for additional electric starters, complicated couplings, heavy cabling, high amperage current or auxiliary batteries. All fuel atomization is accomplished within the fuel control unit and adjacent nozzles. No gaseous fuels of any type are required for starting. A wide range of kerosene based or diesel blended fuels may be used without the need for any fuel preheating or conditioning.
A single button initiates automatic engine start. System parameters are monitored during all phases of engine operation by an electronic engine control unit. Any out-of-limit condition results in the safe shutdown of the engine. Fuel and oil levels are monitored continuously thereby eliminating the potential for damaged pumps due to dry operation. Engine speed is fully controllable. A liquid crystal display panel alerts the operator to any system faults. Total run time and cycle counts are digitally recorded. A single button, prominently marked and readily located safely shuts the system down.
Industrial grade sensors measure all key engine station parameters as well as overall system variables for real time display on the provided computer. Direct engine thrust is accurately measured through a pivoting bearing arrangement utilizing a calibrated load cell, eliminating problems inherent to linear bearings with critical alignment requirements. A USB connected digital data acquisition system is fully integrated and precalibrated. User configurable software allows the creation of custom data displays without the need for programming. Data can be recorded for playback or follow-on analysis. The full range of sensors allows calculations of fuel flow, thrust and pressure ratio to be compared directly to measured values.
Design, technical and manufacturing information and specifications are available for specific teaching and research requirements. Actual engine components and system parts are optionally available for use as teaching and training aids. As the original engine manufacturer, complete spares availability is guaranteed. A free, two year warranty is provided on the entire MiniLab™ system including the SR-30 engine. Additional service and support is available as necessary. On site operator training is available at additional cost.
A comprehensive Operator’s Manual details all aspects of system operation. Summary operating checklists allow rapid mastery of MiniLab™ Gas Turbine Power System operation. Safety instructions address all operating conditions.
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.
