Gas Turbine Jet Engine | ThermoFlux - 7086
Product Overview
The Gas Turbine Jet Engine ThermoFlux - 7086 is a fully functioning aero-derivative turbojet engine test stand with a thrust range of 10 to 100 N, maximum speed of 120,000 rpm, and kerosene fuel consumption of 550 ml/min at maximum thrust. The single-shaft engine features a centrifugal compressor, multi-injector combustion chamber, and ceramic-bearing centrifugal turbine mounted on sliding rails with a linear thrust transducer on a wheeled trolley. This gas turbine jet engine unit measures temperature across five points (3x 0 to 1200°C and 2x -100 to 400°C), pressure (1x -1 to 1 bar and 4x 0 to 4 bar), differential pressure (-25 to 25 kPa), speed (0 to 120,000 rpm), and force (0 to 200 N), with all data shown on a physical mimic panel and DAQ screen display. Optional LabVIEW-based DAQ software is available for Windows-based PC data acquisition.
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Technical Specifications
Gas Turbine Jet Engine ThermoFlux - 7086, Technical Specifications
| Parameter | Value |
|---|---|
| Engine Type | Single-shaft, aero-derivative turbojet |
| Compressor Type | Single-stage centrifugal |
| Turbine Type | Single-stage centrifugal |
| Turbine Bearings | Ceramic (oil-free) |
| Combustion Chamber | Multiple fuel injectors |
| Thrust Range | 10 to 100 N |
| Thrust Measurement | Electronic, linear thrust transducer |
| Engine Weight | 1430 g |
| Overall Engine Size | 265 mm x 111 mm |
| Ancillaries Weight (incl. battery) | 410 g |
| Maximum RPM | 120,000 rpm |
| Idle RPM | 32,000 rpm |
| Idle Thrust | 0.45 kg / 1 lb |
| Full Power Pressure | Slightly over 2 bar |
| Fuel Type | Kerosene with lubricant mix |
| Fuel Delivery | Electrically driven gear pump, Engine Control Unit controlled |
| Fuel Consumption at Max Thrust | 550 ml/min |
| Operator Control | Throttle lever |
| Starting System | Decoupling electric starter, fully automatic |
| Mounting | Two sliding rails on wheeled trolley |
| Differential Pressure Range | -25 to 25 kPa |
| Pressure Range | 1x -1 to 1 bar / 4x 0 to 4 bar |
| Temperature Range (High) | 3x 0 to 1200°C |
| Temperature Range (Standard) | 2x -100 to 400°C |
| Speed Measuring Range | 0 to 120,000 rpm |
| Force Measuring Range | 0 to 200 N |
| Exhaust | Low back pressure duct or direct external vent |
Technical Data
Jet Engine
| Parameter | Value |
|---|---|
| Thrust | 100 N / 10 kg |
| Engine Weight | 1430 g |
| Overall Size | 265 mm x 111 mm (10.4" x 4.4") |
| Ancillaries Weight (incl. battery) | 410 g |
| Maximum RPM | 120,000 rpm |
| Idle RPM | 32,000 rpm |
| Idle Thrust | 0.45 kg / 1 lb |
Fuel
| Parameter | Value |
|---|---|
| Fuel Type | Kerosene with jet oil lubricant mix |
| Fuel Consumption at Max Thrust | 550 ml/min |
Thrust
| Parameter | Value |
|---|---|
| Thrust Range | 10 to 100 N |
| Measurement Method | Electronic |
Speed and Pressure
| Parameter | Value |
|---|---|
| Maximum Speed | 120,000 rpm |
| Full Power Pressure | Slightly over 2 bar |
Exhaust
| Parameter | Value |
|---|---|
| Exhaust Duct | Very low back pressure |
| Venting Option | Direct vent to outside area |
Measuring Ranges
| Parameter | Value |
|---|---|
| Differential Pressure | -25 to 25 kPa |
| Pressure | 1x -1 to 1 bar / 4x 0 to 4 bar |
| Temperature (High Range) | 3x 0 to 1200°C |
| Temperature (Standard Range) | 2x -100 to 400°C |
| Speed | 0 to 120,000 rpm |
| Force | 0 to 200 N |
Key Features
Key Features
- Gas Turbine Jet Engine Type: Single-shaft aero-derivative turbojet, single-stage centrifugal compressor and turbine
- Thrust Range: 10 to 100 N, measured electronically via linear thrust transducer
- Force Measurement Range: 0 to 200 N
- Maximum Speed: 120,000 rpm, idle 32,000 rpm
- Turbine Bearings: Ceramic, oil-free operation
- Combustion Chamber: Multiple fuel injectors
- Fuel: Kerosene with lubricant mix, gear pump controlled by Engine Control Unit
- Fuel Consumption at Max Thrust: 550 ml/min
- Operator Control: Throttle lever
- Starting System: Decoupling electric starter, fully automatic
- Engine Dimensions: 265 mm x 111 mm, weight 1430 g
- Mounting: Two sliding rails on wheeled trolley
- Temperature Measurement: 3x 0 to 1200°C and 2x -100 to 400°C across five measurement points
- Pressure Measurement: 1x -1 to 1 bar and 4x 0 to 4 bar
- Differential Pressure Range: -25 to 25 kPa
- Speed Measurement Range: 0 to 120,000 rpm
- Display: Physical mimic diagram for gas flow temperatures and engine pressure ratio
- Data Acquisition: DAQ system records and displays all data on screen
- Exhaust: Low back pressure duct or direct external vent
- Protective Grating: Fitted over jet engine
- Software: Optional LabVIEW-based DAQ software, Windows compatible
Experiments
- Demonstration of the turbojet principle
- Performance analysis of a turbojet at varying power
- Behaviour during operation of a jet engine including start-up procedure
- Determination of specific thrust
- Determination of specific fuel consumption
- Determination of lambda (fuel-air ratio)
Construction and Design
The Gas Turbine Jet Engine ThermoFlux - 7086 is assembled on a wheeled trolley for ease of positioning and storage. The complete engine and air inlet assembly is mounted on two sliding rails constrained by a linear thrust transducer, enabling direct electronic thrust measurement from 0 to 200 N. The engine is a single-shaft design with a single-stage centrifugal compressor, a multi-injector combustion chamber, and a single-stage centrifugal turbine. Ceramic bearings in the turbine eliminate the requirement for lubricating oil. A tailpipe ducts exhaust gas to a thrust-producing jet, with a low back pressure exhaust duct or direct external vent available.
Air enters via a calibrated nozzle for air mass volume determination. Fuel is kerosene with a lubricant mix, delivered by an electrically driven gear pump controlled by the Engine Control Unit for direct speed regulation. Operator input is via a throttle lever. Starting is fully automatic using a decoupling electric starter. A protective grating covers the engine.
Five temperature measurement points cover air inlet, fuel inlet, compressor outlet, combustion chamber outlet, and tailpipe, with ranges of 3x 0 to 1200°C and 2x -100 to 400°C. Pressure is measured at ambient, air inlet differential (-25 to 25 kPa), and compressor outlet, across ranges of 1x -1 to 1 bar and 4x 0 to 4 bar. Speed is measured from 0 to 120,000 rpm. This gas turbine jet engine unit displays all readings on a physical mimic diagram and a DAQ-based screen display system.
Software
ThermoFlux - 7086 Software (Optional)
- Developed in the National Instruments LabVIEW environment
- Designed specifically for data acquisition with this apparatus
- Records and displays all engine performance data on screen
- A set of electronic sensors is included when the software option is selected
- Compatible with any Windows operating system
Scope of Delivery
- 1 experimental unit
- 1 instructional manual
Standards & Compliance
- Manufactured under ISO 9001:2015 Quality Management System
- CE Marking - European Conformity where applicable
- Supplied with calibration certificate, operation manual, and experiment guide
- 12-month manufacturer's warranty (parts & labour from installation)
Ordering & Delivery
- Incoterms: CIF to destination seaport, FOB Mundra/Nhava Sheva, or Ex-Works Ambala
- Lead time: 3–5 weeks production + sea transit to destination
- Payment: LC (Letter of Credit) or T/T bank transfer against proforma invoice
- Documentation: commercial invoice, packing list, bill of lading, certificate of origin, insurance certificate
Frequently Asked Questions
Q1: What type of engine is used in the Gas Turbine Jet Engine ThermoFlux - 7086?
The unit uses a single-shaft aero-derivative turbojet engine with a single-stage centrifugal compressor, a combustion chamber with multiple fuel injectors, and a single-stage centrifugal turbine with ceramic bearings. The ceramic bearings eliminate the need for lubricating oil.
Q2: What is the thrust range and how is it measured in this gas turbine jet engine unit?
The thrust range is 10 to 100 N and is measured electronically using a linear thrust transducer constraining the engine and air inlet assembly on sliding rails. The force sensor measuring range covers 0 to 200 N.
Q3: What fuel does the engine use and how is it controlled?
The engine uses kerosene with a lubricant mix. Fuel is delivered by a small electrically driven gear pump controlled precisely by the Engine Control Unit, which directly regulates engine speed. The operator uses a throttle lever for speed control.
Q4: What temperatures and pressures are measured and at which locations?
Temperatures are measured at five points: air inlet, fuel inlet, compressor outlet, combustion chamber outlet, and tailpipe stream. Ranges are 3x 0 to 1200°C and 2x -100 to 400°C. Pressure measurements cover ambient air, air inlet differential pressure (-25 to 25 kPa), and compressor outlet, across ranges of 1x -1 to 1 bar and 4x 0 to 4 bar.
Q5: How are the measurement results displayed on this gas turbine jet engine test stand?
Results are displayed on a physical mimic diagram that shows gas flow temperatures and engine pressure ratio. A DAQ-based system also records and displays all indications on a screen. Optional LabVIEW-based DAQ software is available for full PC-based data acquisition on any Windows operating system.