Gas turbine engine pylon

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircrafts. Pylon (30) has streamlined shape defined by two opposite side surfaces and longitudinally between leading edge (31) and trailing edge (33). On each of its side surfaces (36) pylon (30) has sequence of deflectors (40), which are transversely spaced apart from each other and which determine between each other converging and curved channels (60). Channels (60) are made so that to accelerate air flows, flowing in channels (60) during aircraft takeoff or flight so as, to deflect said air flows towards engine jet blast.

EFFECT: invention reduces engine noise.

10 cl, 6 dwg

 



 

Same patents:

Jet engine housing // 2556411

FIELD: aircraft engineering.

SUBSTANCE: jet engine housing comprises stiff thin-wall shell secured to the holder and provided with suction and jet nozzles. Parallel thin-wall ribs arranged one above the other and inclined to central axis are arranged on side of said shell on section from fuel combustion chamber to jet nozzle outlet. Said ribs develop lift in motion in air. Said ribs featured variable width increasing in airflow motion direction.

EFFECT: increased wing lift.

2 cl, 3 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft engine attachment assembly bottom rear streamlined cowling. Cowling 30 comprises two lateral panels 44 jointed by transverse inner ribs 46 spaced apart in cowling lengthwise direction X. Cowling 30 comprises also heat-protection cover 32 blown by engine first stage flow 36. In compliance with this invention, cowling 30 comprises additionally two lengthwise connection walls 58 separating said heat-protection cover 32 from inner transverse ribs 46. Note here that first lateral end 62 or every said connection walls 58 is secured at appropriate lateral end of heat-protection cover 32 while second lateral ends 64 are secured to transverse inner ribs 46.

EFFECT: better aerodynamics.

10 cl, 5 dwg

FIELD: transport.

SUBSTANCE: aircraft comprises fuselage, two wings arranged in symmetry on fuselage sides, and jet engine nacelle secured by means of pylon 18 to every wing. Every said pylon is provided with shaped bearing housing 20, 30 arranged to create resultant propulsion by oblique airflow. Housing 20, 20 extends from end 20a, 30a secured on jet engine pylon 18 toward elongation inclined for 30° with respect to wide wing top surface.

EFFECT: lower drag.

8 cl, 7 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft industry. Lifting wing of aircraft consists of framework, skin, deflection elements of air flow slipping the upper and lower aerodynamic surfaces, outer wing with the engine on the end, which is attached to framework. Lifting wing has mini-wings located on both sides of the engine and creating the lifting force which compensates gravity force from engine weight. Between adjacent engines there located is common mini-wing.

EFFECT: invention is aimed at increasing lifting force.

2 cl, 2 dwg

Engine aircraft // 2076830
The invention relates to aircraft, and in particular to the design of the hoods propulsion engines of the aircraft

Power plant // 2022886
The invention relates to aircraft engine industry, in particular, the power plant of the aircraft with turbofan engines, fitted units, located mainly on the boxes drives

Aircraft wing // 2554026

FIELD: aircraft engineering.

SUBSTANCE: aircraft wing comprises top and bottom airfoils converging at acute angle from the side of oncoming airflow confined by the walls of cavity arranged between top and bottom airfoils. Jet engines, ejectors and downflow air deflectors are arranged at said airfoils. Said jet engines and ejectors are arranged between top and bottom airfoils. Suction nozzles of jet engines and inlet of ejectors are communicated with chambers provided with flat/bulged air intake grates arranged from above.

EFFECT: decreased drag, higher lift.

5 cl, 6 dwg

Subsonic airliner // 2529309

FIELD: transport.

SUBSTANCE: subsonic airliner has high-lift swept low wing with elongation λ≥11.5. Wing sweep in line of chord fourth varies from χ=25° to χ=30°. Rigging angles of the wing support profile twist vary over outer wing span. Every outer wing is set at angle of transverse V. Turbojet nacelles on pylons are mounted under outer wings. In flight, axis of right turbojet and its nacelle (14) are located at positive angle to aircraft mirror axis. In flight, axis of left turbojet and its nacelle (14) are located at negative angle to aircraft mirror axis. Both nacelles are located at positive angle in vertical mirror axis. Outer surface of airframe mid part is shaped to oval.

EFFECT: enhanced performances.

10 cl, 7 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to joint between engine pylon hinged structural beam and wing torsion box. Said joint comprises front and rear fittings of attachment of said beam to front and rear wing torsion box frames with rib arranged there between. Front assembly is composed by vertical pivot extending through pylon structural carcass. Said pivot has two locating seat for interaction with mating locating surfaces of the top and bottom panels of structural beam and is secured over two other locating surfaces at top and bottom lugs of the front frame. Coupling element is arranged inside said pivot. Rear attachment assembly is arranged at rear frame bottom part and composed of at least one clamp located in vertical plane and connected with rear part of hinged structural beam and with rear wing torsion box spar.

EFFECT: simplified design, higher reliability, longer life.

11 cl, 9 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Proposed device comprises stiff structure and attachment to secure engine on said stiff structure wherein said attachment comprises engine rear attachment 8 and thrust take-up device 9. Note here that said rear attachment 8 is secured to stiff structure by two transverse connection elements. Device 9 comprises two connections bars 26a, 26b jointed to cross-arm 28 by mechanical fastener, connection element 49 secured to rear attachment 8 and fastened with stiff structure by pin 60. Transverse connection elements of device 9 comprises means to limit turn of cross-arm 28 in failure of bars 26a, 26b and to transfer traction forces to stiff structure 10.

EFFECT: simplified design.

10 cl, 9 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Support frame 40 is closed by streamlined cowl 46 and rear suspension 44a, 44b mounted on rigid suspension structure 4. Note here that said frame is equipped with suspension structure 42 mounted on engine nacelle air intake 32.

EFFECT: decreased overall dimensions.

15 cl, 7 dwg

FIELD: transport.

SUBSTANCE: nacelle 1 comprises air intake 5 arranged ahead of turbojet engine 2, medium section, inner casing 6a to cover engine fan 3 and rear section 7 with outer element 7a. Said outer element 7a is jointed with fan casing rear section 61 to support turbojet engine 2 and incorporates means of joint with engine pylon to be connected with aircraft fixed element 13.

EFFECT: optimised clearance between fan vanes and engine inner vanes and their appropriate cases.

28 cl, 18 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to power plant with aircraft suspension and engine nacelle rear section. Proposed power plant comprises aircraft bypass turbojet engine and nacelle secured on intermediate crankcase to confine annular space for secondary flow around turbojet engine. Said nacelle has rigid cylindrical section and annular flange arranged on its front end to be secured on 180° of outer surface of intermediate flange. Note here that cylindrical supporting and guiding rear crankcase of turbojet engine on rear end also comprises means of fastening engine suspension elements to aircraft engine parts 22.

EFFECT: simplified attachment of aircraft engine and smaller side of its nacelle.

19 cl, 7 dwg

Bearing nacelle // 2424160

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to turbojet two-stage engine nacelle, aircraft power plant and aircraft incorporating said power plant. Nacelle 1 for turbojet two-stage engine 2 comprises front air intakes section 5, central section embracing engine fan 3, and rear section 7. Rear section comprises internal element 7b that makes engine rear casing. Said internal element has jointing appliances to allow attaching nacelle to pylon 12 arranged to be jointed to aircraft fixed element 13 on, at least, one part of said internal element.

EFFECT: reduced deformation of nacelle.

33 cl, 14 dwg

Aircraft wing // 2404904

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Proposed wing comprises carcass, envelopment, curved top and flat bottom aerodynamic surfaces, console with engine jointed to carcass and ejector with round inlet and outlet holes. Said ejector is arranged on upper aerodynamic surface that has flute-like recess on ejector inlet side. Aforesaid console is arranged along the recess bottom. Ejector confuser lies on upper aerodynamic surface, while diffuser lies partially on upper aerodynamic surface where above ejector outlet is located.

EFFECT: higher lift and thrust.

2 cl, 3 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly to aircraft turbojet engine attachment strut. Strut 4 has rigid structure 10 comprising central torsion box 22 and two lateral torsion boxes 24a, 24b rigidly secured to front part of said central torsion box 22 and arranged on its both sides. Lengthwise central torsion box 22 is formed by two side panels 30 jointed together by crosswise ribs 23, while each side torsion box comprises frame (28a, 28b, 29a, 29b, 46a, 46b). One of said crosswise ribs is furnished with two stiffness ribs (52a, 52b), made integral with rib 23 and extending from two side panels (30) of lengthwise central torsion box (22) outward. Stiffness ribs (52a, 52b) are secured to frame (28a, 28b, 29a, 29b, 46a, 46b) of side torsion boxes (24a, 24b), respectively.

EFFECT: improved aerodynamics, higher engine power and reduced fuel consumption.

17 cl, 12 dwg

Jet engine housing // 2556411

FIELD: aircraft engineering.

SUBSTANCE: jet engine housing comprises stiff thin-wall shell secured to the holder and provided with suction and jet nozzles. Parallel thin-wall ribs arranged one above the other and inclined to central axis are arranged on side of said shell on section from fuel combustion chamber to jet nozzle outlet. Said ribs develop lift in motion in air. Said ribs featured variable width increasing in airflow motion direction.

EFFECT: increased wing lift.

2 cl, 3 dwg

Aircraft (versions) // 2486105

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to supersonic airliner air intakes. In compliance with first version, aircraft comprises wing, fuselage, at least one turbojet engine arranged at fuselage tail. Turbojet air intake has two channels, one arranged atop the fuselage and another located at fuselage tail bottom. In compliance with second version, aircraft comprises two turbojets arranged at fuselage tail, one above the other in aircraft mirror plane. Top turbojet air intake is located on fuselage hose top while bottom air intake is arranged at fuselage nose bottom. Generator of compression shocks in said air intakes represents fuselage nose section compose of horizontal multistage wedge. In compliance with third version, aircraft incorporates, at least, one turbojet arranged in nacelle located under the wing. Aircraft fuselage is secured to its wing by said nacelle. Turbojet engines are provided with air intakes incorporating generator of compression shocks representing common vertical wedge.

EFFECT: possibility to make versatile supersonic airliners.

9 cl, 16 dwg

FIELD: machine building.

SUBSTANCE: rotation device contains fixed support (11) and movable support (12) designed with possibility of rotation around fixed support (11) and around axis (140) of rotation and device for connection of fixed (11) and movable (12) supports, which contains bearing designed with possibility to direct support (11) upon its rotation around support (12), flexible dynamic sealing (1) designed with possibility of tight seal between supports (11, 12) installed between frictional path (4) attached to one of supports (12 or 11) and mechanical structure attached to the other support (11 or 12). Tight seal includes metal spring (5) designed with possibility of contact force of sealing between path (4) and mechanical structure. Seal (1) is installed parallel to axis (140) so that contact force is applied parallel to axis (140). Support (11) contains gaskets (19), and seal (1) contains extended elements (14) distributed along seal (1) and meant for embedding of gaskets (19) to provide star-shaped direction of seal.

EFFECT: producing guiding device for rotation which provides better performance, in particular due to static tight sealing between mechanic elements attached to each other and dynamic tight sealing in frictional part.

6 cl, 9 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft structural element that may withstand increased temperatures, in particular, to aircraft nacelle rear frame. Said to aircraft nacelle rear frame comprises section around opening for passage of anti-icing system made from composite material based on geopolymer reinforced by fibers, and one more metal section.

EFFECT: reduced weight.

4 cl, 5 dwg

FIELD: transport.

SUBSTANCE: aircraft comprises fuselage, two wings arranged in symmetry on fuselage sides, and jet engine nacelle secured by means of pylon 18 to every wing. Every said pylon is provided with shaped bearing housing 20, 30 arranged to create resultant propulsion by oblique airflow. Housing 20, 20 extends from end 20a, 30a secured on jet engine pylon 18 toward elongation inclined for 30° with respect to wide wing top surface.

EFFECT: lower drag.

8 cl, 7 dwg

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