The Turbomeca Aspin was a small French turbofan engine produced by Turbomeca and first run in 1951. This geared turbofan design was the first turbofan to fly, powering the Fouga Gemeaux test-bed aircraft on 2 January 1952.
Fixed inner cone, annular turbine nozzle and outer pipe wherein the jet efflux and by passed secondary air mix. Annular air entry containing one row of variable-incidence entry vanes, a single stage compressor fan and one row of fixed straightening vanes. Fan is driven by compressor shaft through coupling and reduction gear. After fan the air is divided into primary and secondary flows, the former passing to the power section and the latter by-passing that section in an annular casing to the tailpipe where it mixes with the primary jet efflux.
A single-stage centrifugal compressor, with single-sided impeller, and the combustion chamber is annular type, with rotary fuel injection. The turbine is two-stage axial flow turbine, and the jet pipe has a fixed inner cone, annular turbine nozzle and outer pipe wherein the jet efflux and by passed secondary air mix.
Single throttle lever determine the fuel flow and position of variable incidence vanes. Egine speed controled by centrifugal governor. For rapid manoeuvrability a push button operates and electro-hydraulic servo-motor with over-rides manual control and at maximum rotation speed the throttle lever can be used solely to control the entry vanes to obtain rapid variation of thrust without having to oercome the inertia of the rotating assembly.
Throttle at "starter" setting only controls fuel delivery. Entry vanes are closed and engine speed governor is ineffective. Normal starter spins rotating assembly. When engine reaches a rotating speed of 70 per cent. of maximum governor and vane become operative.
Type: Geared turbofan
Maximum thrust: 200 kg (441 lb)
Diameter: 600 mm / 23.6 in
Length: 1210 mm / 47.5 in
Weight with accessories: 127 kg / 279 lb
Fuel burn: 0.628 kg/kg (0.628 lb/lb) trust/hr