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June 1, 1965 R June 1, 1965 R. M. DENNING ETAL 3,186,661 AIRCRAFT PROPULSION POWER PIANTS Filed May 8, 196 6 Sheets-Sheet l Inventors FFAGLIPAW MACACA/ZOEWW/MYG W/L A /A/07Eaa, JAWAFS Mazata 1. EFYAS 72/W267ASA eys June 1, 1965 R. M. DENNING ETAL 3,186,661 AIRCRAFT PROPULSION POWER PLANTS Filed May 8, 1961 6 Sheets-Sheet 2 68· Inventors atavaaaaayadaivas June 1, 1965; R. M. DENNING ETAL 3,186,661 AIRCRAFT PROPULSION POWER PLANTS Filed May 8, 196 6 Sheets-Sheet 3 49 A5 43 9 [zz-ZZZZZZZZ-44,2 Inventor 7tazz, waca/2Ewe william Ja/7es Alewig June 1, 1965 R. M. DENNING ETAL 3,186,661 AIRCRAFT PROPULSION POWER PLANTS Filed May 8, 1961. 6 Sheets-Sheet 5 Inventors 4/4Aam?, vaas a lawas torneys June 1, 1965 R. M. DENNING ETA 3,186,661 AIRCRAFT PROPULSION POWER PLANS Filed May 8, 1961 6 Sheets-Sheet 4 zzzzzzzzzzzzzzzzzzzzzz= ——— Zaar yaa aw aayas June 1, 1965 : R. M. DENNING ETAL 3,186,661 AIRCRAFT PROPULSION POWER PLANTS Filed May 8, 1961 6 Sheets-Sheet 6 Zazzazzazz7ZZZZZZZZZZZZZZZZZZZZZZZZZZ2 ???? P Z ???? ??????; ' By?? ????s ??? ?? ????? 3,186,66 United States Patent Office Patented jume 1, 1965 2 3,186,661 ing a wall of a diffuser portion of the engine intake ARCRAFT PROPULSONPOWERPLANTS duct, and actuating means are provided for moving the Ralph Murch Denning, William James Lewis, Terence two ramps to vary the distance of the apex from the op Edward Gouvenót Gardiner, Peter Michael Runacres, posite side of the engine air intake duct. and Philip William Davis, all of Bristol, England, The invention also includes a power plant as defined assignors to Bristol Siddeley Eagines Limited, Bristol, in the last preceding paragraph in which the com England, a British company pression ramp extends forward of the leading edge of Filed May 8, 1961, Ser. No. 108,594 the base wall to pivotal bearings carried by the side Claims priority, application Great Britain, May 13, 1960, walls, so that on the ramps being moved by the actuat 17,035/60 10 ing means the leading edge of the base wall is also 5 Caims. (CH. 244-53) moved, and in which the actuating means has one or more This invention relates to a power plant for the propul operative connections with the base wall to provide sup sion of aircraft at supersonic speeds, the power plant port therefor intermediate its ends. being of the kind having an engine air intake opening A further feature of the invention consists in that spaced away from the surface of a part of the airframe, an adjustable discharge nozzle, for an aircraft power for example an aerofoil surface or a body surface, by plant of a kind which delivers a flow of jet gas and also an opening for the intake of boundary layer air so that a Secondary flow of gas around the jet gas, includes the air entering the engine air intake arrives with the means movable into a position obstructing rearward out full free stream relative velocity. Although a convenient flow of the jet gas, means movable into a position pro arrangement is for the boundary layer intake to have the 20 viding in an outer wall of the power plant, downstream same width as the engine air intake, this is not neces of the outlet opening of a duct for the secondary flow, sary. For example the boundary layer intake may be at least one opening for lateral outflow of the jet gas, divided up by struts connecting the engine to the rest and means, adjacent to the outlet opening of the sec of the aircraft. ondary flow duct, movable into a position closing the The power plant according to the invention comprises Secondary flow duct. an airflow energising device, for example a turbojet en The invention is illustrated by examples shown in the gine, turbofan engine, combustor, heat exchanger or the accompanying drawings in which: like, hereinafter referred to generically as an engine, an FiGURES 1A and 1B together form a section through engine intake duct extending to the inlet of the engine a power plant taken in longitudinal-vertical plane; from a forwardly facing engine air intake opening, a jet & FIGURE 2 is a cross section towards the air intake pipe extending from the outlet of the engine to a rear end of the power plant take at the line 2-2 in FG wardly facing discharge opening, a boundary layer air URE 1A; duct extending from an intake opening, separated from FIGURE 3 is a cross section towards the outlet end the engine air intake opening by a wall having a sharp R the power plant taken at the line 3-3 in FIGURE leading edge and having an opposite wall extending a 35 substantial distance forwardly of the sharp leading edge FIGURE 4 is a longitudinal-vertical section through so as to generate a boundary layer, to an outlet open the adjustable nozzle shown in FIGURE 1 B but to a ing having a common boundary with, and discharging larger scale and with the nozzle in a different state of in substantially the same direction as, the discharge adjustment; opening of the jet pipe, and a nozzle, adjustable in re 40 FIGURE 5 is a longitudinal vertical section through spect of outlet plane area, through which both the engine a second constructional example also comprising three efflux and the air discharged from the boundary layer similar units arranged side by side but the aftermost air duct pass into the atmosphere. part is shown only in outline, FIGURE 6 being a larger Preferably the boundary layer air duct is arranged so scale drawing of this part; that, in a condition of the power plant appropriate for 45 FIGURE 7 is a longitudinal-horizontal section cor use at supersonic flight speeds, its cross sectional area responding to FiGURE 5 in which only two of the three is nowhere less than at its intake opening, and in units are fully shown, one of these being sectioned at cludes a divergent subsonic diffuser portion. a plane near the top of the unit so as to show the ar According to a feature of the invention, a power rangement of the boundary layer ducting and the other plant as defined in the last preceding paragraph, for 50 being sectioned through the engine air duct; mounting below an aircraft wing, comprises a Substan FIGURES 8 to 11 are transverse sections at the planes tially flat-topped forward section containing the engine marked 8 to 11 on FIGURE 5. air and boundary layer air intake ducts and the engine, The constructional example shown in FIGURES 1 to a rear section containing the jet pipe discharge opening, 4 of the drawings is a multiple power plant composed the boundary layer air duct outlet opening and the 55 of three similar units mounted side-by-side below wing mechanically adjustable nozzle, this section being ar structure 10 forming part of the airframe of an aircraft ranged with the centre line of discharge through these intended for flight at supersonic speeds. The units may elements lying approximately along the top of the for however be used singly, or more than three may be ar ward section, and an interconnecting intermediate Sec ranged side-by-side. Each unit is approximately square tion containing the jet pipe. 60 in cross section, comprising a flat topped forward section According to a feature of the invention two opposite side walls of an inlet end portion of an engine air bounded at the top by the lower skin 11 of the wing struc intake duct in a power plant of the kind mentioned ture, at the sides by vertical walls 2 which extend in the first paragraph are continuous with the side Walls through the wing structure to its upper skin 13 and at the of a superimposed portion of the boundary layer air 65 bottom by a lower wall 14. Rear and intermediate sec duct, the two ducts being separated by a wedge structure tions of each unit are bounded at the top by an upper comprising a substantially flat base wall connected at wall 15 which is an extension of the upper skin 3 of the its leading and trailing edges to two ramps hinged to: wing structure and at the bottom by an upswept portion gether to form an apex, the base wall constituting a Wall of the lower wall 14. The walls 2, 4 and 15 are in of the boundary layer duct, the leading ramp constitut 70 general of double skin "honeycomb" construction to ing an external compression surface of air entering the provide the necessary strength and stiffnes without undue engine air intake duct and the trailing ramp constitut weight. 3,186,661 3 Each unit comprises a turbojet engine 16 mounted in so that for an initial part of their travel an upstream part a central part of the space enclosed by the four walls 48 overlapping the end of the pipe 39 moves approximate if, S2, 4 and 15 so that it is spaced from each Wall to ly about a centre near the plane of the opening 33. The allow air to flow lengthwise over its exterior surface. part 49 is curved about the said centre and co-operates From the inlet 17 of the engine an engine air intake duct 5 with labyrinth seal members 40a on the outside of the S3 extends to an engine air intake opening 19 at the pipe 38 so that, until the movement of the nozzle mem front end of the unit.
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