A Selection of the More Important Aircraft and Engine Specifications Published Recently 362,453 . Oil engines; cylinders. Royce, pas s aft of the engine through the front frame Sir F. H., Nightingale Road, Derby. Sept. 4, an d taper rearwardly in width and depth. The 1930, No . 26399. [Classes 7 (ii) an d 7 (iii).] nacelle mountings are braced to the wing spars Scavenging air enters b y wires K attache d t o lugs D6 fixed t o th e clamping plate s D3 of the leading strut and the ring D of a two-stroke cylinder by th e trailing strut. Two or more nacelles may be tangentia l ports c3 and staye d apart laterally by struts L, Fig. 2, having exhaus t leaves b y one or sleeves L1 and locating blocks L2 clamped between more ports in a substan th e rings D, D1. In a modification, Fig. 5, the tially cylindrical com bustion chamber a3 into which liquid fuel is in jecte d by a transversely- arrange d injector c. A shoulde r aa2 is closely approache d by the pis ton , the clearance being thu s limited to th e com bustio n chamber a3 stru t and nacelle frames are combined, being com which preferably con posed of outer strips of metal M, M1 connected by tain s one large exhaust Hanged webs N, N1. Webs N, N1 are shaped to valv e b. Air is supplied form a central opening, ovoid in the case of the b y a blower t o a cham- front strut and circular for the rear strut. The be r e. The injector c strip s M, M1 may be laminated. Fairings are provided for the interplane and internacelle struts ma y have a single orifice and be radial or tangential o r alternatively, struts of streamline section may t o th e chamber a3. b e employed. The space within th e nacelle behind 363,109 . Mounting nacelles on aircraft. Fig . 2, so tha t they can be operated either by a Short, A. E., and Short, H. O., Seaplane Works, single lobe 64 o r b y four lobes 59 on a cam 56. The Rochester , Kent. Nov. 29, 1930, No. 35983. lobe 64 is carried a t one end of a n arm 54 pivoted a t [Class 4.] 55 and carrying a t the other end a weight 65 held Nacelles are mounted on the interplane struts agains t a casing 51 by a spring 66. The lobe 64 of multiplane aircraft by means of frames carried extend s through a peripheral opening in a cam b y tandem single struts, each strut being provided structur e consisting of members 51, 52 attache d to wit h an independent frame shaped to receive the th e crankshaft, and between which the arm 54 is skin of the nacelle which extends between the pivoted . The cam 56 is rotatably mounted on an struts . Tandem interplane struts B, B1, Fig. 1, extension of the member 52 an d is driven through of circular section carry sleeves C, C1 formed with reductio n gearing 60 . . 63 a t one-eighth crankshaft flat-sided locating blocks C2, C3, respectively, to speed in the opposite direction to th e crank shaft. which are clamped rings D, D1, Fig. 4, clamping Durin g slow running (i.e. below 1,400 r.p.m.), the plate s D2, D 3 being provided for the rings of the ca m lobe 64 is in th e position shown in th e full lines leading strut. The nacelle comprises overlapping in Fig. 3, and actuates th e levers 41 . As this lobe annula r metal sheets E, E1 . . E9, the junctions 64 is rotated a t crankshaft speed, it gives a faster betwee n the sheets being strengthened by angle- injection stroke to the pump plunger than that section hoops F. The sections E3, E8 fit round given by the slow moving lobes 59. As th e speed th e frames carried by the leading and trailing of revolution increases, th e lobe 64 becomes ineffec struts , respectively. The upper portions of sections th e engine may accommodate liquid fuel or oil tive , centrifugal force withdrawing it into th e cam E . . E 3 are cut away along a line E10, a hinged tank s and may house a starter motor. According structure , as shown by the dotted lines in Fig. 3, cowling G being provided for this portion. An t o the Provisional Specification, steel or other an d then the cam lobes 59 actuate the levers 41 . engine H is mounte d on seats comprising horizontal blocks may be mounted beneath the bearers I, I1 Th e lobe 64 is fixed on the crankshaft to lift the plates , I, I1, Fig. 2, and vertical plates I2, I3 fixed for attachment to the engine feet. rocker levers before they contact with th e lobes 59, t o the inside of the nacelle body. These seats 363,891 . Oil Engines. Packard Motor Car Co., Detroit, Michigan, U.S.A. Feb. 16, 1931, No . 4896. Convention date, April 2, 1930. [Classes 7 (ii), 7 (iii), 7 (v), an d 7 (vi).] Th e plunger of a fuel-injection pump is operated a t different speeds relative to the speed of rotation of the crankshaft by a pair of cams, the cam in use a t the lower speed operating th e pum p plunger durin g normal running of the engine, and the cam in use a t the higher speed operating the plunger durin g slow running of the engine. In a radial- cylinder four-stroke engine, fuel is fed by a low- pressur e pump from a reservoir into a manifold 34 which is connected to fuel pumps associated with each cylinder. An overflow conduit 35 connected t o th e uppermost cylinder conducts excess fuel back thu s causing the lobes 59 to pass under the levers t o the reservoir. Fuel is drawn into pump barrels ineffectively, and th e lobes 59 ar e made so long tha t 30 when an inlet port 32 is uncovered by the th e levers ride on them after being raised by the plunger 31, an d is forced by the plunger through a lobe 64 so tha t th e lobe 64 operates only every other nozzle A after the plunger has closed the port 32. rocke r in each revolution. Between injection Each nozzle A an d pum p B ar e formed as a n integral strokes , the rockers contact with a base circle 56 structure . To vary the length of the plunger t o allow th e pump s t o fill wit h oil. The cam lobe 64 * These abstracts of complete specifications of Patents recently stroke , each plunger bears on a spring-pressed ha s a gradually rising face to reduce shocks caused published are specially compiled, by permission of H.M. Stationery membe r 36 and is actuated from a curved face 43 Office, from abridgments which are issued by the Office classified b y th e contact of th e lobe with th e rocker levers. into groups. Sets of group abridgments can be obtained from of a rocker lever 41 throug h a link 40 an d a plunger- Crank casings.—A partition 12 in a barrel crank- the Patent Office, 25, Southampton Buildings, London, W.C.2, actuatin g rod 39. The link 40 is adjusted on the case 11 separates the compartment 13 containing either sheet by sheet as issued, on payment of a subscription of face 43 by turning a ring 44 to which is fixed a link 5s. per group volume, or in bound volumes at 2s. each. Copies of th e connecting-rods from a compartment 14 con the full specifications can be obtained from the same address, 45 joined to the link 40. The ring 44 is moved by tainin g the accessories. A rear cover 15 provided price 1s. each. a rack and pinion 48 operated by a lever 49. The wit h apertures 16 enables th e engine to be fixed to Except where otherwise stated, the specification is unaccom levers 41 are provided with lateral extensions 67, panied by drawings if none is reproduced. a suitable support.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jul 1, 1932
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