Turbo-jet engines of TJ 100 type are designed as drive unit for MAE UAV and pilot flying vehicles.
Development of this engine was founded in the year 2001, and its first serial production engine was bought by INTA in 2004. Several serial produced version is at present, versions untrue by lengthof output nozzle, fastening foot and by power. Since 2008 more than 650 units of TJ100 have been delivered.
PBS produce TJ 100, TJ 100C, TJ100E, and TJ 100I at power level of 100 daN (225 lbf), TJ 100A and TJ 100S are produced with power of 110 daN (247 lbf).
TJ 100 is single-shaft engine with single-stage radial compressor, annular combustion chamber, single-stage axial turbine, and stationary exhaust jet.
In the compressor intake there is a brushless starter generator, which enables the starting from the board network and power generating in course of the engine operation.
The intake air is compressed in the radial compressor wheel, proceeds through radial and axial diffuser into the combustion chamber, where it is mixed with fuel sprayed by several fuel nozzles. Combustion gases arising in fuel burning in the combustion chamber expand through the single-stage axial turbine and exhaust jet into the atmosphere.
The rotor of the engine is mounted on 2 ball bearings lubricated with pressure oil.
Characteristics of TJ-100A
|Static Thrust||100 daN||225 lbf|
|Spf. Fuel Consumption||1.2 kg/daN.hr||1.2 lb/lbf.hr|
|Oil Consumption||180 ml/hr||0.16 qt/hr|
|Fuel Consumption||< 128 kg/hr|
|Electric Power Output||28 V/800W||28 V/800W|
|Dimensions and weight|
|Weight - Engine||16 kg||35 lb|
|Weight - Wth/Access||19 kg||41 lb|
|Outside Diameter||272 mm||10.7 in|
|Length||485 mm||19 in|
|Max Running Altitude||10 000 m||< 281 lbs/hr|
|Max starting Altitude||8 000 m||26 246 ft|
|Flight speed range||< Mach 0.8|
|Speed range on startup||< Mach 0.6|
|Temperature operating range||-40°C to +50°C|