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Aviation History
1949
1949 - 0258.PDF
170 FLIGHT ALVIS LEONIDES ENGINE DATA LE.23.HM WSJI.L No. of cylinders ... ... ... ... 9 Bore 4.80in (122 mm) Stroke 4.4lin (112 mm) Capacity 718 cu in (11.78 litres) Compression ratio ... ... ... ... 6.8 : t Supercharger ratio . 5 : IOverall diameter 4l.4in (1,050 mm) Overall length ... ... 32in (814 mm) 46.7in (I.IBB mm) Frontal area ... 9-6«? ft (0.89 sq m.)Weight 710 1b (312 kg) 780 Ib (354 kg) Weight/power ratio ... 1.29 Ib/h.p. I.SOIb/h.p.(0.59 kg/h.p.) (O.«8 ki/h.p.) Output displacement ..'. 0.76 h.p./cu in 0.72 h.p./cu in (46.6 h.p./litre) (44.1 h.p./litre) Output piston area 3.38 h.p./sq in 3.19 h.p./sq in (0.52 h.p./sq cm) (0.49 h.p./sq cm) Piston speed (max) 2,357ft/min 2,205ft/min (11.9 msec) (11.2 m/sec) B.M.E.P. (max) ... ... , 175 Ib/sq in 180 Ib/sq in : (12.3 kg/sq cm) (12.6 kg/sq cm) Maximum Power at Sea Level (I hour) b.h.p 493 475 r.p.m ., 3,000 2,900 Boost pressure (Ib/sq in) ... ... - ... -i-4^ +4 fuel consumpt (pt/b.h.p./hr) 0.670 0.670 Altitude (ft) ... 7,000 6,500 Maximum Power at Sea Level (S min) b.h.p 550 520 r.p.m 3,200 3,000 Boost pressure (Ib/sq in) ... ... ... +7 + H Fuel consumpt (pt/b.h.p./br) 0.750 0.750 Maximum Continuous Power b.h.p 400 415 r.p.m 2,800 2,800 Boost pressure (Ib/sq in) ... ... ... 2 !-24 Fuel consumpt (pt/b.h.p./hr) 0.620 0.640 Altitude (ft) 9,500 8,500 riuimuiH Weak Mixture Power b.h.p 330 ? 34S r.p.m 2,700 2,800 Boost pressure (Ib/sq in) 0 0 Fuel con!umpt (ptib.h.p./hr) ... ... 0.500 0.500 Altitude (ft) 13,000 14,000 Power for Helicopters . type of mounting, comprises steel plates bonded to rubber blocks which are held in pairs within each apex of the fabricated triangular mounting ring. The ring is made in two halves and welded around its centre line. End caps are then added. This type of mounting is compact, strong and fully flexible. It may be compared with the neat standard Dynafocul flexible mounting of the Westland unit. ••"•'-- It is worthy of mention that in addition to the 6-degree forward sloping angle of main drive shaft of the Bristol 171, there is also a i|-degree lateral angle to offset tail rotor torque-^ parallel to the swing effect on a fixed-wing aircraft. To complete the summary of important equipment car- ried in the Leonides power plants, mention must be made Bristol main and tail rotor gear- box which is driven by a vertical ht engine. Certain accessoMK essential to flying rom the tail rotor shaft. of the Gallay cabin heaters, either hot air or boiler type according to engine mark, which are included in the exhaust-pipe system. .Al-fris helicopter units are assured of an important future in British and probably some foreign machines. A new installation using two power units almost identical with the LE.23.HM is already on its way at Bristol. M. A. S. (Below left) Diffusers for a standard and a horizontal Leonides showing, in the latter case, venes drilled to permit oil to drain to the sump. (Below centre) A unique feature of the Bristol 171 installation is the transmission of more than 500 b.h.p. through a flexible shear coupling comprising light-alloy bolts, scalloped flange and steel cups bonded into rubber. (Below right) The unusual fabricated triangular three-point Dynaflex mounting for the Bristol 171.
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