Motorlet M-701
The Motorlet M-701 is a Czechoslovak jet engine. It was used to power the Aero L-29 Delfín jet trainer, with about 9,250 engines built between 1961 and 1989.
| M-701 | |
|---|---|
 | |
| Motorlet M701 turbojet engine (displayed at the Aviation Museum in Košice, Slovakia) | |
| Type | Turbojet |
| National origin | Czechoslovakia |
| Manufacturer | Motorlet |
| First run | 1958 |
| Major applications | Aero L-29 Delfín |
| Produced | 1961–1989 |
| Number built | more than 9,250[1] |
Development and design
In 1955, the Czechoslovakian aero-engine company Motorlet commenced design of a new turbojet engine to power the Aero L-29, a jet trainer being designed by Aero for a competition to equip all Warsaw Pact air forces. The resulting design, designated Motorlet M-701 was a single-shaft centrifugal-compressor turbojet and was the first jet engine designed in Czechoslovakia (although Motorlet had previously built the Klimov VK-1 under license).[2]
The M-701 was first run in 1958, and engine no. 4 was tested on an Avia B-228 flying laboratory in December 1959.[3] Engine no. 8 powered the third prototype L-29 when it flew on 12 July 1960 (the first two prototypes had flown the previous year powered by Rolls-Royce Viper engines). The L-29 was selected as the winner of the competition and was ordered in large numbers, with the M-701 entering production at Jinonice near Prague in 1961. By the time production ended in 1989, more than 9,250 had been built.[3]
Applications
Specifications
Data from Jane's All the World's Aircraft 1971-72.[4]
General characteristics
- Type: Single shaft centrifugal flow turbojet engine
- Length: 2,067 mm (81.38 in)
- Diameter: 896 mm (35.28 in) (max. width) × 928 mm (36.53 in) (max. height)
- Dry weight: 330 kg (728 lb)
Components
- Compressor: Single-stage centrifugal
- Combustors: 7 straight-flow combustion chambers
- Turbine: Single-stage axial-flow with 61 blades
Performance
- Maximum thrust: 8.75 kN (1,962 lbf) (Take-off power: 15,500 rpm), 7.87 kN (1,764 lbf) (Rated power: 14,950 rpm)
- Overall pressure ratio: 4.3 : 1
- Air mass flow: 19.6 kg/s (37.25 lb/s)
- Specific fuel consumption: 1.14 lb/(lbf⋅h) (at rated power)
- Thrust-to-weight ratio: 2.7
References
- Ing. Marián Hocko (2007-10-05). "M-701". Letecké motory (in Slovak).
- "Walter (Motorlet) M701 (Czech Republic)". Jane's Aero-Engines. Jane's. 16 July 2008. Retrieved 13 January 2009.
- Rada, Jiří (1967). "Projekt letadla L-29 a motoru M701". walterjinonice.cz (in Czech). Retrieved 28 September 2015.
- Taylor, John W.R., ed. (1972). Jane's all the world's aircraft. the annual record of aviation development and progress (Sixty-second year of issue. ed.). London: Jane's. p. 631. ISBN 978-0354000949.