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Aviation History
1918
1918 - 0563.PDF
MAY 23, 1918. at normal speed, 1418 ft. per min. ; brake mean pressureat normal speed, 118 lbs. sq. in. ; cu. ins. of stroke volume per B.H.P., 4-97 cu. ins. ; Sq. ins. of piston area'per B.H.P.,0-788 sq. in. ; B.H.P. per cu. ft. of stroke volume, 348-0 ; B.H.P. persq. ft. of piston area, 182-7.Direction of rotation of crank, anti-clockwise, facing propeller ; direction of rotation of propeller, left hand tractor ;normal speed of propeller, 977 r.p.m. ; ratio of crankshaft speed to propeller speed, 1 -382 : 1 ; type of gear reduction topropeller, Spur gear. Lubrication system, forced, multiple plunger pumps ;oil temperature, 37-5° C. (test figures) ; oil consumption Fig, 6.—Section of cylinder, and arrangement of^1 overhead valve gear and camshaft casing. per1 hour, 10-16 pints = 11.43 lbs.; oil consumption perB.H.P. hour, 0-042 pint •= 0-047 lb. ; specific gravity of oil, Q-900.Type of carburettors, Two, Mercedes, twin-jet; diameter otpjjokcs, 0-945 in. = 24 mms. ; bore of main jets, 0,078 in.—$ mms. ; bore of pilot jets 0-0197 in- = °-5 mms- ; Fuel «9bsumption per hour, 141*3 pints = 127-1 lbs. ; Fuel con- sumption per B.H.P. hour, 0-582 pint = 0-524 lb. ; specific gravity of fuel, 0-720 ; inside diameter of induction pipes, 2-125 ins- = 54 mms. Type of magnetos, two Bosch, H.L.8. ; Firing sequence of engine, propeller.. 1-3-2-4-8-6-7-5. speed of magnetos, engine speed ; magneto timing. (Degrees early full advance), 300 early. Inlet valve opens. Degrees on crank, 20 late ; Inlet valve closes. Degrees on rank, 51 ° late ; Diameter of inlet valve (smallest diam.) = d, 2-677 ins- =.68 mms.; Lift of inlet valve = h, 0450 in. = 11-4 mms. ; Area of inlet valve opening (T d h), 3780 sq. ins. = 24-40 sq. cms. ; Mean gas velocity through inlet valve at normal speed, 149 -5 ft. per sec.; clearance of inlet tappet, 0-012 in. •= 0-305 mm. Exhaust valve opens. Degrees on crank, 520 early ; Exhaust valve closes. Degrees on crank, 16-5° late; diameter of exhaust valve (smallest diam.) = d, 2-677 ins- = 68 mms. ; lift of exhaust valve •= h 0-412 in. = 10-48 mms. ; area of exhaust valve opening (ir d h), 3-460 sq. ins. = 22'4 sq. cms.; clearance of exhaust tappet, 0-018 in. ==0-457 mm. Weight of engine complete, without water, fuel or oil, 900 lbs. (including exh. manifold and propeller hub) ; weight per B.H.P., 900/242. 3-72 lbs.perB.H.P. ; weight of exhaust manifold, 19-5 lbs. ; weight of oil carried in engine, 17 pints = 19-13 lbs. ; weight of fuel per hour, 127-1 lbs. ; weight of oil per hour, 11-44 lbs. ; total weight of fuel and oil per hour, 138-5 lbs. ; gross weight of engine in running order, less fuel and oil, 1057 lbs. (Including cooling system, 242 x 0-65 lbs.); weight per B.H.P., 1057/242. 4-37 lbs. per B.H.P.; gross weight of engine in running order with fuel and oil for six hours, 1971 lbs. (tanks at 10 per cent, of weight of fuel and oil); weight per B.H.P., 1971/242, 8-15 lbs. per B.H.P. Delivery of water pump at 1350 r.p.m. of engine, 91 galls. permin. ; waterjacket capacity of one cylinder, 1280 cu.cms.; ratio of water pump speed to crankshaft speed, 1-5 : 1 ; water temperature. Inlet, 650 C. ; Water temperature, Outlet, 780 C. ; diameter of water pump inlet and outlet, 1-37 ins. = 35 mms. General Analysis of Weights. Description of Part. Cylinders (bare) Pistons complete with ringsand gudgeon pins Connecting rods completewith floating bushes Valves, inlet and exhaustcomplete Crankshaft, with floatingbe velgear Camshaft and case with halfcomprn. gear Reduction gear (large) withpropeller shaft and bear- ings completeReduction driving gear on camshaft, complete withbearings and thrust race Base chamber (top' half)Base chamber (bottom half) Carburettors, completeInduction pipes, complete .. Oil pump, completeWater pump, complete Vertical driving shaft, in-cluding magneto driving bevels and couplings, &c.Propeller Hub complete MagnetosIgnition wiring complete Exhaust manifoldMiscellaneous parts Total weight of complete engine No.per set 8 8 8 16 i i I i. M I 2 2 I I I I 2 2 I Averageunit weight in lbs. 19-25 685 5-00 1-312 94-5O 6o-oo 45-00 23-25 103-75 113-00 8-oo 7-25 12-50 9-00 iz-50 17-875 17-25 2-50 19-5 Weightof com- plete set in lbs. 154-00 54-So 40-00 20 • 992 94-5° 6o-oo 45-00 23-25 103-75. 113-00 16-00 14-50 12-50 9-00 12-875 I7-875 34-5O 5-00 19-5 48-958 900-00 Per-centage of total weight. 17-111 6-088 4"444 2-332 10-500 6-666 5-000 2-583 11-527 12-555 1-7771 -6n 1-388 .I-OOO 1-430 1-986 3-822 •5552-166 5-439 100 During calibration tests at the Royal Aircraft Factory, the engine showed a very good general performance, developing a maximum of 286 B.H.P. at 1,750 r.p.m., and an average of 242 B.H.P. at a normal crankshaft speed of 1,350 r.p.m. 561
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