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Aviation History
1952
1952 - 1583.PDF
6 June 1952 689 CENTRIFUGAL FINAL STAGE COMPRESSOR CLAMPING-BOLT combining throttle valve interconnected with h.p. J shut-off cock and actuator. * and barometric pressure control TORQUEMETER PRIMER CONNECTION STARTING FUEL PUMP SCAVENGE OIL FILTER ACCESSORY-DRIVE COUPLING FUEL MANIFOLD AIRSCREW COUPLING AND PARKING BRAKE assembly, the various auxiliary units being simply mounted externally and picking up their individual drives. The extreme tail of the sun-gear shaft is serrated for engage ment with the drum of the airscrew-parking brake, and this is of two-shoe contracting type operated by an electric actuator through normal toggle linkages. An internally toothed ring gear is formed integrally with the brake drum, and meshes with a spur pinion serrated to the nose of the intermediate transmission shaft, i.e. the shaft which connects the power turbine to the reduction gear. The shaft end-pieces are machined forgings of nitrided steel, the skirts of which are welded to a large-diameter thin-walled tube; the critical whirling speed of the shaft is outside the speed range of the engine, and in this regard blancing bosses are formed on the end forgings. The method of mounting adopted for the Proteus 705 is distinctly unusual but, in its simplicity and fundamental rigidity, should be most efficient. The rear skirt of the reduction gear casing is through-bolted to the compressor difruser casing—a fine casting in RR 50—and nipped between the two is a conical section steel ring in D.T.D. 184. This is peripherally bolted through a rectangular section ring in conjunction with which (on its rear face) is a further conical section ring, the inner lip of which is bolted up to the compressor casing. To complete the triangulation a third cone ring extends between the dirruser casing and the common attachment to the compressor casing. The compressor casing (in RR 50) is cast in upper and lower halves bolted together through the horizontal centre plane of the engine. Dovetail-section grooves accommodate the 12 rows of stator blades—lost-wax cast in HR Crown One or, alternatively, forged in D.T.D. 282 stainless steel—and an ingenious system is adopted for the lateral bedding of the blades. Approximately at 30 deg radial stations in each stage are "expander" blades, the roots of which are laterally tapered. Spigots on these blades pierce the casing and serve as draw-bars through which the exertions of coil springs are transmitted. The tapered faces of the blade roots engage complementarity tapered faces on the adjacent blades, and by this means the spring pre-load of the "expander" blades serves to hold the intermediate gangs of blades squeezed up together, and at the same time provides some degree of accommodation for expansion movement. Each of the 12 rotor stages in the axial compressor is comprised of forged D.T.D. 282 blades diagonally fir-tree anchored in forged
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