Viper Mk 633-47 afterburning.

[kaiserbill]

I'm looking for information, particularly technical specifications, of the Viper Mk 633-47 afterburning turbojet.

This was developed for use on the Yugoslav J-22 and Romanian IAR-93 aircraft.

It appears to be a Viper Mk 632, as licence produced in Yugoslavia, but obviously fitted with a newly designed afterburner.

It would be interesting to see how it compared technically to the J-85 afterburning engine as used in the F-5 aircraft, which it seems to be a close competitor to....in performance not timeline.
But there seems to be a complete lack of information out there on it.

Things such as diameter, length, weight, SFC etc would be interesting to see.

 

[d29]

The main difference between Viper 633-41 (Yugoslavia) and 633-47 (Romania) is that the latter has an anti-icing system.

Basic dimensions/performances:
Inlet diameter of air intake casing = 490,22 mm
Max. width/height of the engine = 708 / 843,5 mm
Length of the base engine = 2433 mm
Length of the reheat section (nozzle open) = 2189 mm
Max. weight of the engine = 431,5 kg
Max. weight of reheat section = 135 kg
Max. RPM = 13760 rpm
Turbine entry temperature: approx. 1243 °K
Air mass flow = 26,8 kg/s
Compressor pressure ratio = 5,9
Min. thrust without reheat = 1693 daN / with reheat = 2161 daN
Max. SFC without reheat = 1,040 kg/daN h / with reheat = 1,866 kg/daN h
Max. JPT without reheat = 750 °C / with reheat = 760 °C

Viper 633-41 cross section

1. Nose bullet assy.
2. Air intake casing assy.
3. Front main bearing
4. Compressor rotor blade 0.stage (29 off)
5. Compressor stator vane 0.stage (28 off)
6. Compressor shaft assy.
7. Blow-off valve flange
8. Compressor diffuser casing assy.
9. Primary air tubes with fuel feed pipes (24 off)
10. Igniter plug (2 off)
11. Combustion chamber outer casing assy.
12. Combustion chamber assy.
13. Turbine nozzle assy. 1.stage (15 segments with 4 vanes each)
14. Turbine disk assy. 1.stage (73 blades)
15. Turbine nozzle assy. 2.stage (15 segments with 4 vanes each)
16. Turbine disk assy. 2.stage (67 blades)
17. Outer exhaust cone assy.
18. Reheat fuel feed pipe
19. Reheat fuel manifold
20. Flame stabilizer - outer
21. Flame stabilizer – inner
22. Reheat chamber
23. Reheat chamber top support
24. Variable nozzle
25. Reheat chamber lower support
26. Bellows unit (compensator of thermal expansion)
27. Thermocouples junction box
28. Inner exhaust cone assy.
29. Exhaust cone drain valve
30. Rear main bearing
31. Combustion chamber drain valve
32. Turbine shaft assy.
33. Centre main bearing
34. Low pressure fuel filter (non-reheat fuel)
35. Starter-generator
36. Fuel pump (non-reheat fuel)
37. Accessory gearbox assy.
38. Hydraulic pump
39. Radial driveshaft for accessory gearbox

The following reheat accessories are not shown in the cross section:
Low pressure reheat fuel filter
Air turbo pump (provides sufficient fuel under all operating conditions to meet the reheat fuel system requirements)
Flow control unit (supplies correctly metered fuel for re-heat operations)
Shut off valve (prevents a fuel flow to the reheat burners when reheat is selected 'OFF')
Pressure maintaining valve (maintain a reheat system delivery pressure above the minimum pressure requirement for correct fuel flow metering in the reheat Flow Control Unit)
Hot streak accumulator (provides shot of metered fuel to non-return valve injectors)
Non-return valve injector (2 off) (directs the shot of fuel from the Hot Streak Accumulator into the engine gas stream to initiate light-up of the reheat fuel system)
Nozzle actuation ram (4 off) (hydraulically operated unit designed to provide the force necessary to move the variable engine exhaust nozzle mechanism)
Nozzle control valve (Micro-jet) (regulates the nozzle area relative to reheat or altitude conditions, thereby maintaining the required pressure differential across the turbine necessary to provide optimum combustion efficiency)
Air control valve (controls and regulates the bleed air flow from the compressor to the air turbo pump)

 

[kaiserbill]

Inlet diameter of air intake casing = 490,22 mm
Max. width/height of the engine = 708 / 843,5 mm
Length of the base engine = 2433 mm
Length of the reheat section (nozzle open) = 2189 mm
Max. weight of the engine = 431,5 kg
Max. weight of reheat section = 135 kg

So..the engine itself with afterburner is larger than the afterburning J85, particularly in length and weight.
4.6m long and weighing in at 566kg.

 

[kaiserbill]

Seeing as it's such a rarely seen engine, here are a couple of pics.

 

[kocovgoce]

The french helped yugoslavia to develop afterburnig somewhere the power of the engine was increased by 34 percent power of the engine.The F-5 had better aerodynamics and smaller wings and thin wings which makes less resistance. The Eagle is a heavier aircraft from f-5 for 1 ton J-22 was and modeled after a Tornado

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