Motorlet M-701
| 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] |
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The Motorlet M-701 is a Czechoslovakian jet engine. It was used to power the Aero L-29 Delfín jet trainer, with about 9,250 engines built between 1961 and 1989.
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
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): Max height 928 mm (36.53 in)
- 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 (at rated power)
- Thrust-to-weight ratio: 2.7:1 (0.026 kN/kg)
See also
- Related lists
References
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Wikimedia Commons has media related to Motorlet M701. |
- ↑ M-701 at slovak language
- ↑ "Walter (Motorlet) M701 (Czech Republic) - Jane's Aero-Engines:". Jane's Aero-Engines. Jane's. 16 July 2008. Retrieved 13 January 2009.
- 1 2 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.