- SR 30 Engine within Turbine Technologies Ltd. U.S. Mini-Lab Small Jet Engine Test Bench (150 Nt)
- S.T. Turbomeca Marbore II Turbojet C Medium Size Jet Engine test Bench (3,000Nt)
- Olympus Engine of AMT Netherlands
- Olympus Technical Data
- Olympus Test Rig (Planned)
Diagnostics EQUIPMENT AVAILABLE (itemized list)
Engines & Test Rigs
SR 30 Engine within Turbine Technologies Ltd. U.S. Mini-Lab Small Jet Engine Test Bench (150 Nt)
Mini-Lab is a relatively small turbine engine test cell. The engine is shrouded by a steel enclosure and heavy polycarbonate operators viewing windows. A microprocessor based digital panel meter provides continuous engine thrust readouts. The SR-30 was developed for drone or unmanned aerial vehicles. The engine weighs less than 10 lb measures 6.75 inches in diameter and is 10 inches long. It burns about 7 lb. Of kerosene per hour while developing 40 lb of static thrust. It features an axial turbine a reverse flow annular combustor and a centrifugal compressor. The turbine and nozzles are made from advanced nickel alloys using a vacuum casting process at the Turbine Technologies facility.
S.T. Turbomeca Marbore II Turbojet C Medium Size Jet Engine test Bench (3,000Nt)
Marbore is a small turbojet designed in 1950 for training aircrafts. It was produced under license by Allison (J69), production department of Beijing (WP11) and by ENMASA (M21).
Standard specifications
- 1st rev 1950
- Weight 140 kg
- Power 4000 to 4800 Nt
- Production period 1950-1979 Marbore II
- 1962-1979 Marbore VI
- Engines Produced 4353 Marbore II 1194 Marbore VI
Olympus Engine of AMT Netherlands
“The Olympus engine has been constructed from a single radial compressor and an axial turbine.. The time required for the turbine to spool up and down is influenced by the low mass of its axial turbine wheel – from min. RPM to max. RPM in less than 4 seconds and from max. RPM to min. RPM in less than 2 seconds. The combustion chamber is of the annular type, which is provided with a unique, “low pressure” fuel system, developed by AMT. From this same fuel system both hybrid bearings are also lubricated. A separate oil supply for lubrication is therefore no longer necessary. The turbine is protected by means of a microprocessor controller (ECU) that regulates the maximum turbine performance within the software limits. The ECU is fully automatic and needs no adjustment”.
| Property | Metric Value | British Value |
|---|---|---|
| Ambient | 280K and sea level | |
| Diameter | 130mm | 5.1 inch |
| Length | 270 mm | 10.6 inch |
| Weight turbine | 2400 gr | 5.3 Lbs |
| Thrust max RPM | 190 N | 42 Lbf |
| Thrust min RPM | 7 N | 1.5 Lbf |
| Pressure ratio max. RPM | 4:1 | 4:1 |
| Mass flow max. RPM | 400 gr/sec | 0.9 Lb/sec |
| Maximum RPM | 110,000 | 110,000 |
| Exhaust temperature | 650 C | 1200 F |
| Maximum exhaust temperature | 700 C | 1290 F |
| Fuel usage max. RPM | 550 gr/min | 19 oz/min |
| Fuel type | Kerosene/paraffin/A-1/white spirit | |
Diagnostics EQUIPMENT AVAILABLE (itemized list):
- Fully instrumented 50 KW pulsating spray combustion experimental facility
- 2 systems of AEROMETRICS PDPA (Phase Doppler Particle Analyzer, Digital Signal Analyzer)
- 1 D DANTEC LDV (Laser Doppler Velocimeter) system (frequency counter based)
- 1 (self made) LDV system for the Pressurized Fluidized Bed Combustor
- 1 (self made) LDV system (for blood flow measurements)
- PIV (self made) System (for simultaneous whole field flow measurements)
- Two (combined & synchronized) Nd Yag 750 mJ lasers
- 1K x 1K thermoelectrically cooled (16 bits) PRINCETON CCD camera
- High Speed Sony CCD camera
- 500 mm f.l. ACTON RESEARCH spectrometer
- 7W Ar Ion laser, 25mW Ar-Ion lasers, 5 mW HeNe lasers.
- 400 MS/S LeCroy digital oscilloscope
- About 15 Pentium III and IV PC’s
- Ancillary electro & optical equipment
(150 Nt)
View from Compressor Side
Marbore II C Turbojet
(The Netherlands)
