Dobrynin VD-7M
This engine powered among other aircraft, in particular the first series of machines, Tupolev Tu-22. In its time it was the most powerful mass-produced turbojet engine with afterburner in the USSR. Maximum thrust it amounted to 16 000 kg with afterburner. This is the classic jet engine (jednoproudový) with axial compressor and afterburner.
The direction of rotation of the motor: Right (clockwise) when viewed from the rear.
Compressor: Axial, 9 degrees. Compression ratio 11:1 at the first nadzvukovém degree. Variable inlet vanes. Exhaust air from steps 5 and 6.
Combustion chamber: Annular tube 14 of the combustion tubes.
Turbine: 2 stages.
Afterburner: direct the flow of gas, providing 50 percent more thrust than the maximum dry thrust.
Output nozzle: Segmented with variable cross-section.
The engine management is ensured by a classical system controlled from the cockpit by push-pull rods and cables. The control system includes regulation of the engine speed, fuel flow, set the input of the blades of the compressor and regulate the air outlet from the compressor.
The engine was complemented by the cabinets of the auxiliary drives for the propulsion lubricating systems, electrical systems and related automatic control, monitoring and electronic systems.
Start engines on the ground was carried out electrically with the help of a pair of generators STG-18TBP (low voltage).
time to reach max thrust (without afterburner): max 23
time to reach max thrust (with afterburner): max 32 with
Type of fuel (normal operation): T-1 or TS-1 kerosene
Type of fuel (for starting): B-70 aviation gasoline
Engine driven machine attachments:
SGS-30-8 AC generator - one
STG-18TBP AC generator - two (used also as starting the generator)
Weight nenainstalovaného engine: 3750 kg
Length (including the section of the afterburner): 7300 mm
The length of the section of the afterburner: 4600 mm
Max diameter (in the afterburner): 1410 mm
The nominal thrust was 92% of maximum thrust. At altitudes above 5500 m, it was possible to use travel
the degree of afterburner for a period of up to 120 minutes of full afterburner for a period of 30 minutes.
The values in the table are in terms of the ISA.
Dobrynin RD-7M2
Source:
Tupolev Tu-22 Blinder By Sergey Burdin, Alan E. Dawes, ISBN 1-84415-241-3.
This engine powered among other aircraft, in particular the first series of machines, Tupolev Tu-22. In its time it was the most powerful mass-produced turbojet engine with afterburner in the USSR. Maximum thrust it amounted to 16 000 kg with afterburner. This is the classic jet engine (jednoproudový) with axial compressor and afterburner.
The direction of rotation of the motor: Right (clockwise) when viewed from the rear.
Compressor: Axial, 9 degrees. Compression ratio 11:1 at the first nadzvukovém degree. Variable inlet vanes. Exhaust air from steps 5 and 6.
Combustion chamber: Annular tube 14 of the combustion tubes.
Turbine: 2 stages.
Afterburner: direct the flow of gas, providing 50 percent more thrust than the maximum dry thrust.
Output nozzle: Segmented with variable cross-section.
The engine management is ensured by a classical system controlled from the cockpit by push-pull rods and cables. The control system includes regulation of the engine speed, fuel flow, set the input of the blades of the compressor and regulate the air outlet from the compressor.
The engine was complemented by the cabinets of the auxiliary drives for the propulsion lubricating systems, electrical systems and related automatic control, monitoring and electronic systems.
Start engines on the ground was carried out electrically with the help of a pair of generators STG-18TBP (low voltage).
time to reach max thrust (without afterburner): max 23
time to reach max thrust (with afterburner): max 32 with
Type of fuel (normal operation): T-1 or TS-1 kerosene
Type of fuel (for starting): B-70 aviation gasoline
Engine driven machine attachments:
SGS-30-8 AC generator - one
STG-18TBP AC generator - two (used also as starting the generator)
Weight nenainstalovaného engine: 3750 kg
Length (including the section of the afterburner): 7300 mm
The length of the section of the afterburner: 4600 mm
Max diameter (in the afterburner): 1410 mm
The nominal thrust was 92% of maximum thrust. At altitudes above 5500 m, it was possible to use travel
the degree of afterburner for a period of up to 120 minutes of full afterburner for a period of 30 minutes.
The values in the table are in terms of the ISA.
| the Conditions and the mode of the engine | the Number of revolutions of the engine per minute | Thrust (kg) | Specific fuel consumption (kg fuel/kg thrust/hour) | Maximum gas temperature in the turbine (Celsius) |
| a take-off on earth | 7400 | 16000 | 2.0 | 630 |
| Max. thrust without the afterburner on the ground | 7400 | 10500 | 0.82 | 630 |
| of the Nominal pull of the earth | 7100 | 8600 | 0.78 | 540 |
| Travel (cruise) thrust at sea level (81.5% nominal tensile strength) | 6850 | 7000 | 0.78 | 510 |
| Max. thrust with afterburner at 11000 m, the speed of 1500 km/h | Max. 7450 | 9700 | 2.1 | 630 |
| Move with a travel (cruise) afterburners in the 11000 m, the speed of 1300 - 1400 km/h | Max. 7450 | 7500 | 1.65 | 630 |
| Nominal thrust at 11000 m, the speed of 1000 km/h | 7150 | 2500 | 1.0 | 540 |
| Idle on the ground | Max. 3250 | max 450 | -- | 410 |
Dobrynin RD-7M2
| Parameter | Value |
| the Thrust during takeoff at sea level (kg) | 16500 |
| Specific fuel consumption (kg fuel/kg thrust/hour) | 2.05 |
| Move at full auxiliary combustion and TAS (True Airspeed) 1500 km/h at a height of 11000 m (kg) | 11000 |
| Specific fuel consumption (kg fuel/kg thrust/hour) | 2.25 |
| Safety speed limit due to the oscillations of the blades of the compressor at an altitude 0 - 4000 m and an ambient temperature of +40 degrees Celsius and lower (km/h) | 1020 |
| Safety speed limit due to the oscillations of the blades of the compressor at an altitude 0 - 4000 m and an ambient temperature of +40 to +60 degrees Celsius (km/h) | 910 |
Source:
Tupolev Tu-22 Blinder By Sergey Burdin, Alan E. Dawes, ISBN 1-84415-241-3.