Bristol Siddeley Viper Mark 520 Turbojet: A Description of the Development Background to this Small Turbojet Engine, its Technical Features and Performance

Abstract

THE Bristol Siddeley Viper 520 turbojet engine which powers the de Havilland DH 125 jet executivc aircraft, employs an eight‐stage axial compressor which is driven by a single‐stage turbine. The combustion chamber is of the annular vaporizing type. Two Viper 520 engines are mounted in nacelles attached to the rear fuselage of the DH 125 such that the intakes are clear of the fuselage boundary layer at this position. Maximum take‐off thrust of the engines is 3,000 lb. for a specific fuel consumption of 0·985 lb./lb. thrust/hr.

Citation

(1963), "Bristol Siddeley Viper Mark 520 Turbojet: A Description of the Development Background to this Small Turbojet Engine, its Technical Features and Performance", Aircraft Engineering and Aerospace Technology, Vol. 35 No. 2, pp. 39-43. https://doi.org/10.1108/eb033682