80kg Thrust Turbojet Engine SXH-1200N （low cost）

Vue d'ensemble

The SXH-1200N 80kg thrust turbojet engine is a small turbojet engine with low cost, high thrust-to-weight ratio and high reliability independently developed by Feihang Power Technology Co., Ltd. The overall structure of single-stage centrifugal compressor + short annular downstream combustion chamber + single-stage axial flow turbine is adopted, and the form is simple. Adopt 0-2-0 support structure, one thrust ball bearing at the front and the rear share the radial load of the engine, and the rear bearing bears the axial load. The front and rear bearings use an elastic ring structure to adjust the rotor dynamics. The engine is fixed in the aircraft nacelle by the front casing mounting plate and the tail nozzle mounting edge. The engine rotor adopts an internal force transmission structure, and the force of the rotor is transmitted to the aircraft nacelle through the bearing seat, diffuser, mounting plate and front mounting section. As a whole, the engine has a simple and compact structure design, easy disassembly and assembly, efficient use of space and guaranteed strength requirements of parts, meeting the design requirements of low cost and high thrust-to-weight ratio. 80kg thrust turbojet engine SXH-1200N is a self-developed product with a number of national patented technologies. Automatic fuel one key start, ignition system is stable and reliable. ECU speed control, with multiple protection, data transmission, software can be upgraded, parameters can be adjusted to cope with different working environments, precise speed control, rapid throttle response, high altitude ignition start and many other advantages. High speed, thrust-weight ratio, high altitude ignition 1. Engine model and category Engine model: SXH-1200N 80kg thrust turbojet engine 2. Rotation direction of the engine rotor

Spécifications techniques

Caractéristiques principales : Engine model SXH-1200N 80kg thrust turbojet engine, Category Small Turbojet, Maximum diameter 203mm, Maximum length 501mm, The stability margin of the engine in the maximum state 15%., No Item Value, Maximum speed (r/min) 65000, Maximum thrust (daN) 100, Idle speed (r/min) 30000, Idle thrust (daN) 11, Engine dry weight (kg) 9.25, Thrust-to-weight ratio 11.89, Installed weight (kg) 11.5, Installed thrust-to-weight ratio 9.56, Air flow (kg/s) 1.8, Maximum thrust fuel consumption (kg/min) 2.6, Maximum exhaust temperature 750℃, Operating temperature range -25℃～+50℃, Maximum starting height (m) 5000, Maximum use height (m) 10000, Maximum working M 0.9, Start mode automatic fuel start, Maximum flight altitude 10000m, Maximum flight speed 1100km/h, Minimum working temperature -25℃, Maximum working temperature +50℃.

Spécifications techniques

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