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The Saturn/Lyulka AL-34 was an unbuilt turboshaft/turboprop engine for rotary and fixed-wing aircraft, proposed by the Soviet Union in the early 1990s. In turboprop form, the engine was offered for light aircraft such as the Sukhoi Su-86 eight-passenger business airplane, the Myasishchev M-101T Gzhel business jet, the ROS-Aeroprogress T-101 Grach nine-passenger aircraft, its derivative T-108 Zolotoy Orel nineteen-passenger aircraft, and the Krunichev T-511 "AIST-M". As a turboshaft, the AL-34 was proposed to power the Mil Mi-54 and the Kazan Ansat helicopters. The engine was also considered for unconventional aircraft such as the Mil Mi-30L Vintoplan tiltrotor aircraft, and it was to be an auxiliary engine for powering the boundary layer control system and air cushion on the EKIP flying saucer (a flying wing aircraft).

The AL-34 was one of the few engines to use a recuperator to recover and reuse waste heat from combustion.

The engine came in two versions. The AL-34-1 was an engine that produced 550 horsepower (410 kW) in cruise conditions. It weighed 363 pounds (165 kilograms), which included a compact, 88 lb (40 kg) recuperator. The AL-34-2 was a twin-configuration engine producing 1,100 hp (820 kW), weighing about 1,200 lb (540 kg), and using a common gearbox in a single module.

In October 2000, Saturn/Lyulka confirmed that it was still developing the AL-34 engine in the 1,000 to 1,500 hp (750 to 1,120 kW) power range, and it was working with Kawasaki on stationary powerplant applications. The AL-34 would cost 200-240 thousand dollars, and it would require about 22 million dollars to complete development. As late as January 2004, the engine was still being proposed for the T-511 "AIST-M" derivative of the Krunichev T-411 Aist light utility aircraft. However, the AL-34 never entered production.

Specifications

Data from (for AL-34-1 only)

General characteristics

• Type: turboshaft or turboprop with recuperator
• Length: 1.609 m (5.28 ft; 1,609 mm; 63.3 in)
• Diameter: 0.676 m (2.22 ft; 676 mm; 26.6 in)
• Dry weight: 165 kg (363 lb)

Components

• Compressor:
• Fuel type: TS-1, T-1, RT, 25%
• Oil system: MK-32 (MS-20), 75%; MK-8P (MS-8P)

Performance

• Maximum power output: Takeoff: 1,000 hp (750 kW); Cruise: 550 hp (410 kW)
• Bypass ratio: 6.15
• Specific fuel consumption: Cruise: 0.348 lb/(hp⋅h) (0.158 kg/(hp⋅h); 0.212 kg/kWh)

References

Citations

1. Jerram, Mike (February 1991). "European correspondence". Flying: World's most widely read aviation magazine. Vol. 118, no. 2. pp. 20–21. ISSN 0015-4806.
2. ^ Zrelov, V. A. (2002). Отечественные ГТД. Основные параметры и конструктивные схемы (Часть 1) [Domestic engines. Basic parameters and construction diagrams. (Part 1) Study guide] (PDF) (Report) (in Russian). Samara State Aerospace University. pp. 99–102. ISBN 5-7883-0210-2. OCLC 1020674498.
3. ^ Kolokolnikov, G.; Chevkinov, V. (June 1992). T-101 aircraft highlighted. Russia: Economic and Social Affairs. FBIS report: Central Eurasia (Report). FBIS Report. Vol. FBIS-USR-92-127. Translated by Foreign Broadcast Information Service (FBIS) (published October 3, 1992). pp. 29–31. hdl:2027/uiug.30112001465522. {{cite report}}: Unknown parameter |agency= ignored (help)
4. Kolganov, V.; Sakharov, V. (April 1993). T-108 aircraft production highlighted. Russia: Economic and Social Affairs. FBIS report: Central Eurasia (Report). FBIS Report. Vol. FBIS-USR-93-130. Translated by Foreign Broadcast Information Service (FBIS) (published October 7, 1993). pp. 55–58. hdl:2027/inu.30000008301206. {{cite report}}: Unknown parameter |agency= ignored (help)
5. ^ Andrianov, Arnold; Polavsky, Yuri (January 19, 2004). "'АИСТ-М' РАСПРАВЛЯЕТ КРЫЛЬЯ" ['AIST-M' spreads wings]. Крылья Родины [Wings of the Motherland] (in Russian). No. 1. pp. 3–7. ISSN 0130-2701.
6. Kozlov, Dmitry (November 17, 2009). Пресс-конференция ОАО 'МВЗ им. М.Л.Миля,' посвященная 100-летию со дня рождения М.Л.Миля [Press conference of OJSC 'Mil Moscow Helicopter Plant' dedicated to the centenary of the birth of M. L. Mil]. AviaPort.ru (in Russian) (published November 20, 2009).
7. Kartashov, V.; Stepanov, A. (2001). Kazan helicopter plant chief designer's report: ANSAT helicopter design features (PDF) (Report). hdl:20.500.11881/1337 – via European Rotorcraft Forum (ERF) Document Repository.
8. Mikheev, Vadim (October 2006). "Проект "винтоплана" Ми-30" [Project of hybrid helicopter-airplane Mi-30] (PDF). промышленность - проект (industry - project). Взлёт: Национальный аэрокосмический журнал [Take-off: National aerospace magazine] (in Russian). No. 22. Translated by Pushkin, Pavel. pp. 18–19. ISSN 1819-1754 – via Nexis Uni.{{cite magazine}}: CS1 maint: date and year (link)
9. ^ Dawson, Dorothy (June 29 – July 5, 1994). "Saucerful of secrets". Lifting-Body Craft. Flight International. Vol. 145, no. 4427. pp. 30–31. ISSN 0015-3710. Gale A16143330.
10. ^ McDonald, Colin F.; Massardo, Aristide F.; Rodgers, Colin; Stone, Aubrey (May 2008). "Recuperated gas turbine aeroengines, part II: Engine design studies following early development testing". Aircraft Engineering and Aerospace Technology. 80 (3): 280–294. doi:10.1108/00022660810873719. ISSN 1748-8842.
11. "Saturn/Lyulka diversifies business to cope with Russian economic crisis". Reshaping Russia's Propulsion Industry. Aviation Week & Space Technology. Vol. 136, no. 13. March 30, 1992. pp. 44–46. ISSN 0005-2175.
12. Nesterov, Victor (October 4, 2000). "ОАО 'А. Люлька-Сатурн' — без прикрас" [OJSC 'A. Lyulka-Saturn' - unvarnished]. Авиапанорама [Aviapanorama] (in Russian). No. 5. ISSN 1726-6173.
13. "Готовы предложения по дальнейшему совершенствованию авиадвигателя Ал-34" [Proposals for further improvement of the Al-34 aircraft engine are ready] (in Russian). Finmarket News Agency. October 13, 2000.

Bibliography

• Plot of takeoff SFC vs. takeoff shp for shaft engines, Vick, 2013
• Jerram, Mike (May 1992). "European correspondence". Flying: World's most widely read aviation magazine. Vol. 119, no. 5. pp. 42–43. ISSN 0015-4806.

• Saturn aircraft engines