RU2068377C1 - Jet airliner - Google Patents

Abstract

FIELD: aeronautical engineering; aircraft manufacture. SUBSTANCE: power plant of airliner consists of twin-jet engines with rectangular nozzles provided with controllable flaps. Each pair of engines is provided with common heat exchanger and steam generator whose outlet is connected with turbine inlet; rectangular nozzles have bevel exit sections. EFFECT: enhanced reliability. 2 cl, 6 dwg

Description

 The invention relates to aircraft, and in particular to aircraft construction.

 Known jet passenger aircraft TU-134, containing the fuselage, wing, tail, landing gear and power plant. The disadvantage of the aircraft is that the power plant runs on chemical fuel, which is expensive. In addition, the exhaust gases of chemical fuel flowing out of jet engines pollute the environment.

 Also known is the TU-144 supersonic jet passenger plane containing the fuselage, wing, horizontal tail, landing gear and power plant [II] The disadvantage of this aircraft is that the power plant also runs on chemical fuel and is also expensive and harmful to the environment. In addition, the control of the TU-134, TU-144 aircraft is carried out by flaps arranged in the wing body, occupying a large usable area. Controlled mechanisms and flap assemblies also occupy a large useful wing area, which leads to a reduction in the area for placing fuel tanks in the wing body.

 The flap control system of the aircraft is ineffective, since the aircraft takes a long path during take-off and landing, which affects the fuel economy on board the aircraft. In addition, aircraft require long runways.

 The task to be solved by the claimed invention is aimed at creating the economy of a short-take-off and landing passenger aircraft, in the engines of which water vapor is used as a component of the working fluid.

 The proposed hybrid passenger jet aircraft containing the fuselage, wing, tail, powerplant and landing gear, in which the new is that the aircraft is equipped with hybrid rocket launchers, which are formed of two turbojet engines interconnected through a vertical strut, in the body of which are arranged steam generators.

 Also new is the fact that in the case of turbojet engines heat collectors are arranged, connected to steam generators and a system for supplying water vapor to the engine turbine.

 New in the aircraft is also the fact that turbojet engines are formed by two nozzles and controlled dampers. The inner nozzle of the engine has a cylindrical shape with a transition to a second rectangular shape. The rectangular nozzle of the turbojet engine has a vertical angular cut, in the channel of which a controlled shutter is arranged, which, when deflected, due to the beveled cut of the rectangular nozzle, forms an exhaust channel through which the gas stream expires during accelerated take-off.

 The use of water vapor in turbojet engines as a component of the working fluid will reduce the consumption of chemical fuel by 30–40%. This will increase the radius of the flight range of the aircraft, as well as reduce environmental pollution.

 The use of a power plant with new design engines in an airplane allows you to free the wing from the flaps, which makes it possible to increase the wing area to accommodate fuel tanks.

 The use of turbojet engines with two nozzles in an aircraft gives the aircraft an accelerated take-off and improves aircraft control for all flight modes.

 In FIG. 1 shows an airplane, side view (general view); figure 2 shows a plane, a top view; figure 3 is the same, front view.

 A hybrid passenger jet aircraft contains a fuselage 1, in which a wing 2 is arranged, and a tail unit 4 with a vertical keel 3 is arranged at the rear of the fuselage 1.

 In the lower nose of the wing 2, a hybrid power plant 5, in the lower part of the fuselage 1, the landing gear of the aircraft is 6.7.

 A fairing 8 is arranged in the nose of the fuselage 1, and in the upper nose of the fuselage 1 there is a cockpit 9 and an entrance door 10.

 In the central part of the fuselage 1 arranged portholes of the passenger compartment 11.

 Figure 4 shows a diagram of a hybrid rocket launcher (accelerated take-off). The installation comprises a housing 12, in which an air intake 13, a compressor 14, which is connected to the combustion chamber 15. is placed. A vertical strut 16 connects two engines, forming a hybrid reactive installation. In the central part of the vertical strut 16, a steam generator 17 is arranged with a steam inlet 18. The steam inlet 18 is connected to a pipe 19, which is connected to a ring 20 in which the steam nozzles 21 are arranged. In the engine housing 12, a heat intake 22 is arranged behind the steam ring 21, and in the inner case of the heat intake 22 is arranged a gas turbine 23 connected to the inner nozzle 24. The inner nozzle 24 is connected to the rectangular nozzle 26. A controlled shutter 27 is arranged in the nozzle body 26, which is fixed through the axis 36 in the upper part of the rectangular nozzle 26, cat When deflected, it forms the exhaust channel 25.

 The dotted line shows the position of the shutter 28 in the retracted horizontal position.

 In the upper part of the rectangular nozzle 26, a hydraulic mechanism 29 is arranged, which is movably connected through a rod 30 and a hinge 32 to a rack 31, which is attached to the body of the rectangular nozzle 26. The hydraulic mechanism rod 33 is movably connected to a hinge 34 and a rod 35. Position 37 shows the hydraulic mechanism in the retracted position .

 The steam reactor 38 is arranged in the lower part of the casing of the vertical strut 16 and is connected to the heat inlets 22 (Fig. 5,6), the pipe 19 flows into the pipe 39, which is connected to the ring 20.

 In FIG. 5 shows a diagram of a hybrid rocket launcher (vertical back section). The circuit includes an engine casing 12, a vertical strut 16, a steam generator 17, a steam intake 18, a pipe 19, a gas turbine 23, an internal nozzle 24, an exhaust channel 25, a controlled shutter in a horizontal position 28, a hydraulic mechanism 29, a strut 31, a hinge 32, an axis 36, pipeline 39.

 In FIG. 6 shows a diagram of a hybrid rocket launcher (horizontal section). The circuit includes an engine casing 12, an air intake 13, an air compressor 14, a combustion chamber 15, a vertical strut 16, a steam intake 18, a pipe 19, a ring 20, a nozzle 21, a heat intake 22, a gas turbine 23, an internal nozzle 24, a rectangular nozzle 26 controlled a shutter 28 (in the retracted position), a hydromechanism 29, a thrust 30, a stand 31, a hinge 32, a rod of a hydromechanism 33, a hinge 34, a thrust 35, an axis 36, a steam reactor 38, a pipeline 39.

 Device hybrid jet passenger aircraft operates as follows. To take off the aircraft, the power plant 5 is started (Fig. 1), at this time the air stream is pumped through the air intake 13 into the compressor 14 (Fig. 4), then the air stream enters the combustion chamber 15, where it mixes with the fuel, forming a gas stream. The gas stream ignites, converting into a burning gas, which leaves the combustion chamber 15 and enters the blades of the gas turbine 23, bringing it into rotation.

 The burning gas stream, flowing around the inner case of the heat intake 22, moves to the inner nozzle 24, at which time the force from the hydromechanism 29 is transmitted through the rod 33 to the thrust 35, which, rotating on the hinge 36, tilts the shutter 27, forming the exhaust channel 25.

 The gas stream leaving the internal nozzle 24 enters the exhaust channel 25, which, when exiting the exhaust channel 25, creates a lift for the aircraft. At this time, the aircraft carries out accelerated take-off. At the same time, the temperature from the burning gas stream is transferred to the housing of the heat intake 22, from the heat intake 22, the temperature is transmitted to the walls of the steam reactor 38 (FIGS. 5-6). Under the influence of temperature, water in the steam reactor 38 boils, at this time steam forms in the steam generator 17, which enters the steam intake 18, then the steam moves through the pipeline 39 (Figs. 5-6), from the pipeline 39 the steam enters the ring 20, from the ring 20 the steam exits through the nozzles 21. Next, the steam enters the blades of the gas turbine 23, increasing its rotation. Then the steam is mixed with the gas stream, reducing its chemical percentage, and when leaving the nozzle 26 into the atmosphere reduces environmental pollution by chemical gases.

 After accelerating takeoff, the engines of the power plant 5 go on a horizontal flight. The hydromechanism 29 (Fig. 4) through the rod 33, which, rotating on the hinge 34, drives the rod 35, which is fixedly mounted on the surface of the valve 27, rotating on the hinge 36, removes the valve 27 in a horizontal position. The hydromechanism 29 through the thrust 30, which rotates on the hinge 32, leads the rod 33 and the thrust 35 to position 27, at which time the gas stream flows through the nozzle 26 in a horizontal position, creating a horizontal thrust to the aircraft.

Claims (2)

 1. A jet passenger aircraft containing the fuselage, wing, tail, landing gear and power plant with turbojet engines with rectangular nozzles with controlled flaps, characterized in that the power plant includes at least one pair of turbojet engines equipped with a common heat exchanger and steam generators, with this exit from the steam generator is connected to the entrance to the turbine.  2. The aircraft according to claim 1, characterized in that the rectangular nozzle is made with an oblique cut.

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