Soloviev D-20
From Infogalactic: the planetary knowledge core
| D-20 | |
|---|---|
| Type | Turbofan |
| Manufacturer | Soloviev Design Bureau |
| Major applications | Tupolev Tu-124 |
The Soloviev D-20P was a low-bypass turbofan engine rated at 52.9 kN (11,900 lbf) thrust. It was built by the Soloviev Design Bureau. The engine was used on the Tupolev Tu-124.
Contents
Specifications
Data from Gunston.[1]
General characteristics
- Type: Twin-spool turbofan engine
- Length:
- Diameter:
- Dry weight: 1,468 kg
Components
- Compressor: Three-stage LP, eight-stage HP, axial flow
- Combustors: 12-chamber cannular
- Turbine: Two-stage LP turbine, single-stage HP turbine
Performance
- Maximum thrust: 5,400 kg
- Overall pressure ratio: 13:1
- Bypass ratio: 1:1
- Air mass flow: 113 kg/s at 8,550 rpm
- Power-to-weight ratio:
See also
- Related lists
References
Notes
<templatestyles src="Reflist/styles.css" />
Cite error: Invalid <references> tag; parameter "group" is allowed only.
<references />, or <references group="..." />Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
 |
This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |
- ↑ Gunston 1989, p. 164.
