# Brandner E-300

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Egyptian turbojet engine

E-300 Egyptian E-300 engine undergoing testing Type Turbojet National origin Egypt Manufacturer Egyptian General Aero Organisation Major applications Helwan HA-300

The **Brandner E-300** was an Egyptian [turbojet](/source/Turbojet) engine, developed for the [Helwan HA-300](/source/Helwan_HA-300) light jet fighter.

## Development

Austrian engineer [Ferdinand Brandner](/source/Ferdinand_Brandner), who had worked in the [Soviet Union](/source/Soviet_Union), leading the development of the [Kuznetsov NK-12](/source/Kuznetsov_NK-12) [turboprop](/source/Turboprop), the powerplant of the [Tupolev Tu-95](/source/Tupolev_Tu-95) bomber, moved to Egypt to lead a team to design an engine to power the [Helwan HA-300](/source/Helwan_HA-300) jet fighter that was simultaneously being designed by a team of Germans led by [Willy Messerschmitt](/source/Willy_Messerschmitt).

The new engine underwent bench testing in 1963, and was flight tested under the wing of an [Antonov An-12](/source/Antonov_An-12), before being installed in a [HAL HF-24 Marut](/source/HAL_HF-24_Marut) for high speed testing, in which form it flew on 29 March 1967.[1] The E-300 was installed in the third HA-300 prototype (the first two were powered by [Bristol Siddeley Orpheus](/source/Bristol_Siddeley_Orpheus) engines), but testing stopped in the taxi-test stage before flight tests. The programme of HA-300 was abandoned in May 1969.[2]

## Variants

**E-300-A**
- Military version for HA-300

**E-300-C1**
- Civil version of E-300-A, proposed for Project 206 three-engined airliner.[1]

**E-300-C2**
- Proposed growth version of E-300-C1.[1]

**E-300-AF**
- Projected turbofan development.[1]

## Specifications (variant)

*Data from* Jane's All The World's Aircraft 1969-70[1]

#### General characteristics

- Type: Afterburning [turbojet](/source/Turbojet)

- Length: 4,300 mm (169.3 in)

- Diameter: 840 mm (33 in)

- Dry weight: 860 kg (1,896 lb)

#### Components

- Compressor: nine-stage [axial compressor](/source/Axial_compressor)

- [Combustors](/source/Combustor): can-annular combustion chamber

- [Turbine](/source/Turbine): two-stage axial turbine

#### Performance

- Maximum [thrust](/source/Thrust): 32.4kN (6,275 lbf) dry, 47.2 kN (10,582 lbf) with reheat

- [Overall pressure ratio](/source/Overall_pressure_ratio): 6:1

- [Thrust-to-weight ratio](/source/Thrust-to-weight_ratio): 3.310 dry, 5.581 with reheat

## References

1. ^ [***a***](#cite_ref-Janes_69_p671_1-0) [***b***](#cite_ref-Janes_69_p671_1-1) [***c***](#cite_ref-Janes_69_p671_1-2) [***d***](#cite_ref-Janes_69_p671_1-3) [***e***](#cite_ref-Janes_69_p671_1-4) Taylor 1969, p. 671.

1. **[^](#cite_ref-Info_2-0)** Group Captain Kapil Bhargava. ["Messerschmitt's HA-300 and its Indian Connection"](https://web.archive.org/web/20080705050530/http://www.bharat-rakshak.com/IAF/History/1960s/Kapil-HA300.html). *Memoirs*. Indian Air Force. Archived from [the original](http://www.bharat-rakshak.com/IAF/History/1960s/Kapil-HA300.html) on 2008-07-05. Retrieved 2008-08-08.

## Bibliography

- [Taylor, John W. R.](/source/John_W._R._Taylor) *Jane's All The World's Aircraft 1969-70*. London:Jane's Yearbooks, 1969.

## External links

- [\[1\]](http://www.leteckemotory.cz/motory/e-300/)

- [\[2\]](https://grabcad.com/library/brandner-e-300-engine-1)

v t e Egyptian General Aero Organisation (EGAO) aircraft and engines Fighters HA-200 HA-300 Trainers Bü 181 Engines E-300

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