Tumansky R-79V-300

R-79V-300
The engine, divided by sections
TypeTurbofan
National originSoviet Union, Russia
ManufacturerAMNTK Soyuz
First run1984
Major applicationsYakovlev Yak-141
Number built26 (including 16 flight-worthy engines)

The Tumansky R-79V-300.[1] is an afterburning turbofan developed by NPO Soyuz in the Soviet Union, now AMNTK Soyuz in Russia. The R-79 is a vectored-thrust afterburning turbofan used as powerplant for the supersonic Yak-141 vertical takeoff/landing (VTOL) fighter aircraft designed by Yakovlev to replace the Yak-38[2]

Design and development

The development of the R-79 began in the late 1970 under the direction of V.K. Kobchenko with development project designation Izdeliye 79 ('Product 79'). The design and development of the R-79V-300 was driven by the requirement of designing a power plant for a supersonic V/STOL aircraft working alongside two lift engines (RD-41). Unlike its predecessor, the thrust-vectored non-afterburning turbofan Tumansky R-27 used in the Yak-38, the R-79 single exhaust design combined with a three-joints ring swivel nozzle made possible an afterburner turbofan capable of operate in any nozzle position.[3]

The R-79V-300 used in the Yak-141 is a two-shaft axial-flow afterburning turbofan with counter-rotating spools to reduce weight and gyroscopic forces on the engine. The engine has a three-stage low-pressure compressor (fan) and an eleven-stage high-pressure compressor, with bleed air from after the 6th stage for roll control. Both compressors are driven by a pair of counter-rotating 2-stage turbines. However the bleed air for roll control, up to 10 kg/s taken from the core will reduce the thrust. Paired with two RD-41 (4.1 kN, 4,260 kgf) they totals a thrust in hovering mode of 20,500 kgf (45,194.8 lbf) at ISA conditions.[4]

Ground testing, production and test flights extended from 1983 to 1991 when the Yak-141 was cancelled.[5]

Further developments

During the 1990s Soyuz developed an alternative rectangular nozzle for vector control in the pitch axis, replaced the analogue electronic engine controller with a FADEC and increased thrust.[6] Nevertheless, this improved version and a non-augmented R-79V-300 variant designated VK-21[7] have no reported application. In the early 2000s AMNTK Soyuz developed a 30 MW gas turbine using the core and turbines of the R-79V-300 replacing the low pressure compressor and adding a 5-stage power turbine developed by JSC Kuznetsov.[8]

Variants

R-79V-300[1][9]
With a 3-wedge ring swivel nozzle capable of 0 – 95º vector control with full afterburner. 152 kN (34,000 lbf) thrust
R-79M (R179-300)[6]
Improved version with higher maximum thrust, FADEC and new rectangular nozzle that enable a control of ±20° in the pitch axis. 176–200 kN (40,000–45,000 lbf) thrust.
R-579SPS-300[10]
Improved engine presented at 2021 MAKS.
VK-21[7]
Proposed non-augmented version of the R-79V-300. 110.8 kN (24,900 lbf) of thrust.
GTE-30-300[11]
Aero-derivative gas turbine with a capacity of 30MW and 33 MW peak power with a thermal efficiency of 36% developed since 2002–2003 and presented at 2005 MAKS but with little information after that. Airflow: 99.3 kg/s, Overall pressure ratio: 22.1:1.

Applications

Specifications (R-79V-300)

Data from Zrelov, Maslov, 1999;[1] Butowski, Fricker, (1995)[12]

General characteristics

  • Type: Contra-rotating twin-spool, axial flow, afterburning turbofan
  • Length: 523 cm (205.9 in)
  • Diameter: 171.6 cm (67.6 in) overall, 124 cm (48.8 in)[7] without afterburner-nozzle. 110 cm (43.3 in) inlet.
  • Dry weight: 2,750 kg (6,062.7 lb) including nozzle and accessories

Components

  • Compressor: 3-stage low pressure compressor, 11-stage high pressure compressor with bleed air from the 7th stage for roll control
  • Combustors: Annular
  • Turbine: 2-stage low pressure turbine, 2-stage high pressure turbine

Performance

  • Maximum thrust:
    • 152 kN (34,171.0 lbf) with full afterburner
    • 137 kN (30,798.8 lbf) with afterburner and 10 kg/s of bleed air[3]
    • 122.5 kN (27,539.1 lbf) hovering with afterburner (limited to 2.5 minutes)[13]
    • 103 kN (23,155.3 lbf) dry
  • Overall pressure ratio: 22
  • Bypass ratio: 0.80 - 0.81[1][9]
  • Air mass flow: 180 kg/s (396.8 lb/s)
  • Turbine inlet temperature: 1,347 °C (1,620 K; 2,457 °F)
  • Specific fuel consumption: 67.2 kg/(kN·h (0.66 lb/(lbf·h)) dry, 169 kg/(kN·h (1.66 lb/(lbf·h))[9] with reheat

See also

References

  1. ^ a b c d Зрелов В.А, Маслов В.Г. (1999). Основные... pp. 90–91.
  2. ^ Bill Gunston, Yefrim Gordon (1997). Yakovlev Aircraft since 1924. United Kingdom: Putnam Aeronautical Books. p. 190. ISBN 0-85177-872-0.
  3. ^ a b Bill Gunston, Yefrim Gordon (1997). Yakovlev Aircraft since 1924. United Kingdom: Putnam Aeronautical Books. p. 191. ISBN 0-85177-872-0.
  4. ^ Piotr Butowski, John Fricker, (1995), pp. 31-32
  5. ^ Piotr Butowski, John Fricker, (1995), pp. 31, 36
  6. ^ a b "R179-300". ANMTK Soyuz. Archived from the original on 6 Aug 2002. Retrieved 17 Aug 2008.
  7. ^ a b c "VK-21". AMNTK Soyuz. Archived from the original on 6 Sep 2002.
  8. ^ "урбины и дизели, СЕНТЯБРЬ-ОКТЯБРЬ 2005 (Turbines and Diesel, September-October 2005), p.46" (PDF).
  9. ^ a b c "Авиационные двигатели [Aircraft engines]". AMNTK Soyuz. Archived from the original on 17 Aug 2008. Retrieved 17 Aug 2008.
  10. ^ "АМНТК "Союз" представил первый российский двигатель для сверхзвукового пассажирского самолета на МАКС-2021 [AMNTK Soyuz presented the first Russian engine for a supersonic passenger aircraft at MAKS-2021]". 2021.
  11. ^ "Газотурбинные установки [Gas turbine units]".
  12. ^ Piotr Butowski, John Fricker (1995). Yakovlev's V/STOL Fighters... p. 31.
  13. ^ Piotr Butowski, John Fricker (1995). Yakovlev's V/STOL Fighters... p. 35.

Further reading

  • Piotr Butowski, John Fricker (1995). Yakovlev's V/STOL Fighters Yak 36, Yak 38, Yak 41 and Yak 141: The Full Story of Russia's Rival to the Harrier. Aerofax Inc. / Midland Counties Publications Ltd. ISBN 978-1-85780-041-8.
  • Зрелов В.А, Маслов В.Г. (1999). Основные данные отечественных авиационных ГТД и их [Zrelov V.A., Maslov V.G. Basic data of domestic aviation gas turbine engines and their application in educational design.] (in Russian). Russia: Samara State Aerospace University. ISBN 5-7883-0056-8.
  • http://www.leteckemotory.cz/motory/r-79/index.php?en
This article is issued from Wikipedia. The text is available under Creative Commons Attribution-Share Alike 4.0 unless otherwise noted. Additional terms may apply for the media files.