RU2717409C1 - Vertically oriented turbojet engine of power plant of vertical take-off and landing aircraft, vertical take-off and landing aircraft power plant, as well as vertical take-off and landing aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the field of aviation, in particular to designs of lifting engines, power plants of vertical take-off and landing aircraft. Vertically oriented turbojet comprises annular loop combustion chamber, turbine located outside combustion chamber. Turbine is connected with shaft above combustion chamber, or turbine shaft passes inside annular combustion chamber. Torque from turbine shaft to compressor is transmitted by reduction gear. Nozzle consists of two cone-shaped, interconnected static parts: one larger size, another smaller size located inside the first one with some gap. Cone-shaped nozzle has shape of discontinuous ring like horseshoe. Power plant of vertical take-off and landing aircraft consists of one or several vertically oriented (lifting) engines and one or several horizontally oriented turbojet engines with variable thrust vector.

EFFECT: high speed of horizontal flight, manoeuvrability and stability of aircraft in all modes of flight.

3 cl, 2 dwg

Description

Field of Technology:

Engine and Aircraft

An analogue of a vertically oriented turbojet engine of a power plant of an aircraft of vertical takeoff and landing is a turbojet engine. It can be called a prototype.

A jet engine is an engine that provides forward movement by quickly releasing a stream of liquid or gas in a direction opposite to the direction of movement. Scientific and Technical Encyclopedic Dictionary [Electronic resource]: enc-dic.com. (Date of treatment: 03/04/2015).

A turbojet engine is an aircraft engine in which energy is generated by reactive power of expanding gases. At the front, air enters the compressor, is pumped into the combustion chamber, mixed with fuel and ignited, which causes explosive expansion of the gas. Scientific and Technical Encyclopedic Dictionary [Electronic resource]: enc-dic.com. (Date of treatment: 03/04/2015).

A disadvantage of currently known jet engines, including turbojet engines (analogue and prototype) is the incomplete use of their potential.

An analogue of the power plant of an aircraft of vertical take-off and landing is a turbojet engine. He has no prototype.

A turbojet engine is an aircraft engine in which energy is generated by reactive power of expanding gases. At the front, air enters the compressor, is pumped into the combustion chamber, mixed with fuel and ignited, which causes explosive expansion of the gas. The power plant of the aircraft vertical takeoff and landing.

A disadvantage of the currently known jet turbojet engines is the incomplete use of their potential.

Well-known analogues of the Aircraft of vertical take-off and landing are a helicopter, a plane with a vertical take-off and a tiltrotor, the second of which is a prototype.

An airplane is an aircraft heavier than air with a wing, on which aerodynamic lift is generated during movement, and a power plant that creates thrust for flight in the atmosphere. Encyclopedia "Technique". [Electronic resource]: eps-dic.com. (Date of treatment: 03/04/2015).

A helicopter is an aircraft in which the lifting force is created by means of a screw (s). Able to perform vertical take-off and landing, hovering, moving forward, backward, sideways. Scientific and Technical Encyclopedic Dictionary [Electronic resource]: enc-dic.com. (Date of treatment: 03/04/2015).

A tiltrotor is an aircraft with vertical take-off and landing with a variable thrust vector created by screw engines. [Electronic resource]: www.rosinform / 2013. (Date of treatment: 05/18/2015).

The disadvantages of the Aircraft with vertical takeoff is that it has only one distinctive quality compared to a conventional aircraft - the ability to take off from a limited space, while being limited in maneuverability, has a tendency to tip over during takeoff, and is extremely difficult to control, especially when moving from a vertical horizontal flight mode and vice versa.

The disadvantages of the Helicopter are that, being inferior to the aircraft in speed and distance to overcome distances, in some cases it is also limited in its maneuverability due to rotors and tail rotors (meaning the possibility of touching these screws, for example, electric wires on poles and other items).

The shortcomings of the Tiltrotor are expressed in that, surpassing the helicopter in speed and distance of covered distances, it has the above-mentioned disadvantages of the helicopter, in the Tiltrotor the problem of the so-called “vortex ring” characteristic of the helicopter is more pronounced, when the rotor blades fall into the vortex stream that was before This is created by the rotor itself, which leads to a decrease in the lifting force of the blades.

Disclosure of the essence of a vertically oriented turbojet engine of a power plant of an aircraft of vertical take-off and landing.

A vertically oriented turbojet engine of a power plant for an aircraft of vertical takeoff and landing is a device containing a well-known scheme of a turbojet jet engine that produces energy by the reactive power of expanding gases, with an increase in their pressure by compression, which differs from it in that it is intended for a fundamentally new the aircraft, combining the properties of a helicopter and an airplane, has a different design of units, as well as units, and consists of shown in figure 1 from an annular combustion chamber, 3 in combination with a loop method of its device, is placed in a vertical position. Inside it passes the shaft of the turbine 4, the turbine 5 is also placed in a vertical position under the combustion chamber, the torque from the turbine shaft to the compressor 6 is transmitted through a reducer 7, the gas jet stream, leaving the combustion chamber and passing the turbine, enters the nozzle 8, consisting of two cone-shaped statically connected parts, one larger size 9, the other smaller size 10, located inside the first with some clearance, we increase towards the end into which the jet stream enters. This nozzle is located in the lower part of the aircraft in an upright position. Due to the cone shape of the nozzle, the jet stream 11, proceeding from it in a continuous stream, diverges from its center, axis in different directions, forming an extensive disk of lifting force of a larger size than a significant part of the dimensions, respectively, and mass, of the aircraft itself, on which the engine is installed, which gives it special stability in vertical movement, the diameter of the nozzle depends on the size of the aircraft. Its extreme borders coincide with the dimensions of the middle part of the fuselage of the aircraft. The aircraft on which the vertically oriented engine is mounted is designed in such a way that its center of gravity coincides with the center of the cone-shaped nozzle. The air supply system to the engine is a dual-circuit 12, part of the air enters the combustion chamber, the other passes through the external circuit and is involved in cooling the engine and lowering the temperature of the gases leaving the nozzle; in vertical flight, air enters the engine in addition to the horizontal air intakes, also from the vertical air intakes, arranged in the fuselage of the aircraft on which it is installed.

Alternatively, an alternative to a cone-shaped nozzle on a vertically oriented turbojet engine, a nozzle resembling the shape of a horseshoe 13 can also be used, which also consists of two parts, one larger, another smaller, located inside the first with some clearance, increasing towards the end into which the jet jet, with the deviation of the nozzle at the exit of the jet from the center, the axis of the vertical oriented turbojet engine out, so that the jet stream diverges from its center in different directions, forming an extensive disk of lifting force of a larger size than a significant part of the dimensions, respectively, and mass, of the aircraft, which ensures its stable flight in vertical mode.

Alternatively, other types of combustion chambers may be used in a vertically oriented turbojet engine.

To reduce the axial dimensions, as an option, the annular combustion chamber of a vertically oriented turbojet engine is arranged so that the turbine is placed, as shown in figure 1, around it 14 and the gases generated during the combustion of the fuel emit to the outside of the ring of the combustion chamber to the turbine, or inside it is 15, here the gases leave the ring in the inner side also to the turbine. Gases, falling on the turbine blades located at a certain angle, set it in motion. In the first case, the turbine is connected to the shaft by additional devices above the combustion chamber. In the second, the turbine shaft passes inside the annular combustion chamber.

Such an annular combustion chamber has small axial dimensions, but large transverse ones, however, this corresponds to the design idea of the aircraft for which such an engine is intended.

The proposed device design is based on the action of Newton’s second law, according to which in inertial reference frames the acceleration acquired by a material point that is directly proportional to its force does not depend on its nature, coincides with it in direction and is inversely proportional to the mass of the material point.

The essence of a vertically oriented turbojet engine of a power plant for an aircraft of vertical take-off and landing is that it, using the classical scheme of a turbojet engine, provides the movement of the aircraft in a vertical plane with a much greater degree of stability than the currently known analogues.

The engine also allows the aircraft on which it is installed to acquire unique properties that combine the properties of an airplane, helicopter or tiltrotor.

The task of the proposed technical solution of a vertically oriented turbojet engine of a power plant of an aircraft of vertical take-off and landing.

The task of a vertically oriented turbojet engine of a power plant for an aircraft of vertical takeoff and landing is that it provides a fundamentally new distribution of tractive effort, which determines that the aircraft on which it is installed has previously unknown properties, especially combining the maneuverability and stability of the aircraft in vertical flight mode.

The ability to provide the technical result described above when implementing the invention is based on a combination of two physical laws: the underlying engine of the conservation of momentum and the so-called Newton’s second law, according to which the change in momentum is proportional to the applied driving force and occurs in that direction by which this force acts. This law, as is well known, describes the relationship between the force applied to a material point and what happens as a result of the acceleration of this point. The effect of this Law is manifested when organizing the placement of the engine, as well as the jet stream in a special way, constructed as described above. Here the jet stream serves as the mentioned force, and the fuselage of the aircraft is the material point.

The power plant of the aircraft vertical takeoff and landing is as follows.

Organized in the above order, a vertically oriented engine provides takeoff and landing of the aircraft on which it is mounted in a vertical plane, as occurs in a helicopter. The lifting force is provided not by rotating the screws, but by discarding the working fluid, that is, by exiting the jet stream, in the opposite direction to the movement.

A vertically oriented turbojet engine of a power plant for an aircraft of vertical take-off and landing is shown in Figure 1.

Disclosure of the essence of the power plant of the aircraft vertical takeoff and landing.

The power plant of the aircraft for vertical take-off and landing consists of a vertically oriented turbojet engine and a horizontally oriented turbojet engine with a variable thrust vector located at the rear of the aircraft, which ensures high speed of the aircraft in the horizontal direction, in this mode, the vertically oriented engine supports the lifting force of the aircraft apparatus. The operation of both engines is related, as the transition from vertical to horizontal flight, the performance of a vertically oriented turbojet engine decreases, and the performance of a horizontally oriented turbojet increases, in this flight mode, a vertically oriented turbojet engine is used to maintain lift, when returning to vertical flight, the specified ratio changes in the reverse order, these proportions are provided by manual control or com by a puter.

The air supply system in a vertically oriented turbojet engine is a dual-circuit 12, part of the air enters the combustion chamber, the other passes through the external circuit and is involved in cooling the engine and lowering the temperature of the gases leaving the nozzle, in vertical flight, air enters the engine in addition to horizontal air intakes, also from vertical air intakes located in the fuselage of the aircraft on which it is mounted. Such an air supply system is also used in a horizontally oriented turbojet engine.

As options, the power plant of a vertical takeoff and landing aircraft may have a different combination of the number of vertically oriented and horizontally oriented turbojet engines: one vertically oriented engine and one horizontally oriented engine, four vertically oriented engines and two horizontally oriented engines, or another combination; alternatively, one vertically oriented engine is provided with several nozzles; if several vertically oriented engines or one such engine with several nozzles are installed on the aircraft, they are placed so that the center of gravity of the aircraft remains between them.

The proposed device design is based on the action of Newton’s second law, according to which in inertial reference frames the acceleration acquired by a material point that is directly proportional to its force does not depend on its nature, coincides with it in direction and is inversely proportional to the mass of the material point.

The essence of the power plant of an aircraft of vertical take-off and landing is that it, using the classical scheme of a turbojet engine, ensures the movement of the aircraft in both vertical and horizontal planes with a much greater degree of stability than the current analogues.

Also, the special distribution of the thrust of the installation allows the aircraft on which it is installed to acquire unique properties that combine the advantages of an airplane in speed and a helicopter in maneuverability.

The task of the proposed technical solution of the power plant of the aircraft vertical takeoff and landing.

The task of the power plant of the aircraft of vertical take-off and landing is that it provides a fundamentally new distribution of traction forces, which causes the aircraft on which it is installed to have previously unknown properties, combining speed, maneuverability and survivability, stability at a new level, as in vertical and horizontal flight modes.

The ability to provide the technical result described above when implementing the invention is based on a combination of two physical laws: the underlying engine of the conservation of momentum and the so-called Newton’s second law, according to which the change in momentum is proportional to the applied driving force and occurs in that direction by which this force acts. This law, as is well known, describes the relationship between the force applied to a material point and what happens as a result of the acceleration of this point. The effect of this Law is manifested when organizing the placement of the engine, as well as the jet stream in a special way, constructed as described above. Here the jet stream serves as the mentioned force, and the fuselage of the aircraft is the material point.

The power plant of the aircraft vertical takeoff and landing is as follows. Organized in the above order, a vertically oriented engine provides takeoff and landing of the aircraft on which it is mounted in a vertical plane, as occurs in a helicopter, a horizontally oriented engine ensures its movement in a horizontal plane, just like an airplane moves. Thus, a combination of the properties of a helicopter and an aircraft is achieved in one aircraft. The lifting force is provided not by rotating the screws, but by dropping the working fluid, that is, by the exit of the jet stream, in the opposite direction to the movement.

The power plant of the aircraft vertical take-off and landing is presented in figure 1.

Disclosure of the essence of the aircraft vertical-horizontal movement.

The essence of the aircraft vertical takeoff and landing, as a technical solution is expressed in the following. It is a device containing a well-known diagram of aircraft, which are heavier than airborne devices, characterized by the fact that due to the unique characteristics and special distribution of traction forces of the power plant installed on it, the absence of rotors and tail rotors allows you to combine and exceed the advantages of a helicopter in maneuverability that are not available to aircraft, as well as the advantages of the aircraft in speed and distance traveled, not achievable for helicopters and convertiplanes.

Such properties of an aircraft of vertical take-off and landing are achieved due to the special power plant of the aircraft of vertical take-off and landing with a fundamentally new distribution of tractive effort, consisting as shown in figure 2 of a vertically oriented turbojet engine 1 and a horizontally oriented turbojet engine 2. Power plant of the aircraft vertical take-off and landing can be installed on an aircraft vertical take-off and landing in different variations, in particular, in the singular, and in the case of large aircraft, for example, in the case of its cargo or passenger destination, there may be several, with a different combination of the number of vertically oriented and horizontally oriented engines, for example four vertically oriented turbojet engines and one or two horizontally oriented turbojet engines. The control of the aircraft, its maneuvering, is carried out by changing the thrust of the engines of the power plant of the aircraft of vertical take-off and landing.

The operation of the aircraft is as follows. The vertically oriented engine mounted in the above order, mounted on it, ensures its take-off and landing in the vertical plane, as happens with a helicopter, and the horizontally oriented engine ensures its movement in the horizontal plane, just like an airplane moves. Thus, a combination of the properties of a helicopter and an aircraft is achieved in one aircraft. The lifting force is provided not by rotation of the screws, but by the discarding of the working fluid, the release of the jet stream, in the opposite direction to the movement. The absence of rotors and tail rotors deprives the declared aircraft of the aforementioned drawbacks inherent in helicopters and convertiplanes. Moreover, the claimed device is more maneuverable than an airplane, and does not need runways.

The aircraft vertical take-off and landing is presented in figure 2.

The task of the proposed technical solution of the aircraft vertical takeoff and landing.

The objective of the proposed technical solution of the aircraft of vertical takeoff and landing is that, due to the properties reflected above, while maintaining the speed and flight range of the aircraft, due to the above design and power plant of the aircraft, vertical takeoff and landing achieves and also surpasses maneuverability helicopter and tiltrotor. These unattainable qualities for an analogue and prototype give the aircraft the ability not only to take off from a limited space and land on a limited space, but to fly at extremely low speeds and low altitudes, to pass between various obstacles (for example, buildings and power lines in settlements, rocks in mountains, etc.), hang at certain heights.

The ability to achieve the specified technical result is achieved through a special power plant of an aircraft of vertical take-off and landing, during the course of which the above Newton’s Second Law is realized.

Brief Description of the Drawings:

The figure No. 1 depicts a vertically oriented turbojet engine, a power plant of an aircraft of vertical take-off and landing with a map of units and assemblies:

1) vertically oriented turbojet engine;

2) horizontally oriented turbojet engine;

3) a combustion chamber;

4) turbine shaft;

5) turbine;

6) compressor;

7) gearbox;

8) conical nozzle;

9) the outer part of the cone-shaped nozzle;

10) the inside of the cone-shaped nozzle;

11) the direction of the jet;

12) the direction of air movement for the combustion chamber and engine cooling;

13) an alternative nozzle.

14) option of a combustion chamber with a turbine placed around it

15) version of the combustion chamber with the placement of the turbine inside it.

2. The figure No. 2 shows the aircraft vertical takeoff and landing:

16) aircraft;

1) vertically oriented engine;

2) horizontally oriented engine;

17) the chassis.

The implementation of a vertically oriented turbojet engine power plant aircraft vertical take-off and landing.

The specified engine can be equipped with a power plant of an aircraft of vertical take-off and landing, ensuring the achievement of the above-mentioned useful properties.

The implementation of the power plant of the aircraft vertical takeoff and landing.

This installation can be equipped with newly built specifically for him aircraft of military and civil aviation, ensuring the achievement of the previously mentioned useful properties.

The implementation of the aircraft vertical take-off and landing.

An aircraft equipped with a power plant for a vertical take-off and landing aircraft with the new technical characteristics reflected above can be useful for law enforcement bodies and other law enforcement agencies to ensure a high degree of responsiveness and suppression of various criminal manifestations, for example, terrorist acts, attacks on collectors and etc.

Providing the aircraft with appropriate weapons, special equipment (night-vision devices, thermal imagers, etc.) and information from duty officers on law enforcement units, as well as from information processing centers from video surveillance cameras, its pilot will be able to quickly reach the scene of the offense and deliver selective, verified blows that will stop the crime or substantially impede its execution. Modern information systems, coupled with the capabilities of the aircraft, will allow the pilot to provide additional information (data, video) in flight, which will make it possible to adjust its actions and make them as effective as possible.

The creation and supply of law enforcement forces with such aircraft with their introduction into the global security system will allow timely suppressing such and other criminal manifestations or significantly minimizing their consequences.

This aircraft, already with different weapons, can also be used by units of the Ministry of Defense of the Russian Federation, since its unique qualities, which no other aircraft yet possess, will allow for more accurate and precise attacks on enemy targets in populated or fortified areas or when performing special tasks.

Finally, the aircraft can be used for medical (medical) aviation, becoming more efficient for its purposes than helicopters, due to the qualities noted above (speed and distance range that it can overcome while maintaining and even exceeding the degree of helicopter maneuverability).

Claims (3)

1. A vertically oriented turbojet engine of a power plant of an aircraft of vertical take-off and landing, containing an annular loop-shaped combustion chamber, the turbine is located outside the combustion chamber, while the gases generated during the combustion of the gases proceed to the outside of the ring of the combustion chamber to the turbine, or inside it, in this case, the gases exit the inner side of the ring also to the turbine, the gases, falling onto the turbine blades located at a certain angle, set it in motion, in the first case the turbine connected to the shaft above the combustion chamber, in the second - the turbine shaft passes inside the annular combustion chamber, the torque from the turbine shaft to the compressor is transmitted through the gearbox, the gas jet stream leaving the combustion chamber and passing the turbine enters a nozzle consisting of two cone-shaped, statically connected parts: one larger, the other smaller, located inside the first with a certain gap increasing towards the end into which the jet stream enters, such a nozzle is made with possibly Because of the location in the lower part of the aircraft, due to the cone shape of the nozzle, the jet stream, proceeding from it in a continuous stream, diverges from its center in different directions, forming a large lift disk larger than the dimensions of the aircraft, the diameter of the nozzle depends on the size of the aircraft the apparatus, its extreme boundaries coincide with the dimensions of the middle part of the fuselage of the aircraft, the engine and nozzle are configured to change the thrust vector relative to the vertical axis, the air supply system to the vert the gas-oriented engine is a dual-circuit, part of the air enters the combustion chamber, the other passes through the external circuit and is involved in cooling the engine and lowering the temperature of the gases exiting the nozzle; in vertical flight, air enters the engine in addition to horizontal air intakes, also from vertical air intakes, a cone-shaped nozzle shaped like a horseshoe. 2. The power plant of the aircraft vertical take-off and landing, consisting of one or more vertically oriented (lifting) engines, made according to claim 1, and one or more horizontally oriented turbojet engines with a variable thrust vector, providing high speed aircraft in the horizontal direction , the operation of the engines is connected, as the transition from vertical to horizontal flight, the performance of a vertically oriented engine decreases, and horizontally oriented water productivity increases, in this flight mode, a vertically oriented engine is used to maintain lift, when returning to vertical flight, the indicated ratio changes in the reverse order, these changes are provided by manual control or by a computer, the horizontally oriented engine has the same air intake system as and horizontally oriented engine. 3. Aircraft of vertical take-off and landing, containing a power plant according to claim 2, characterized in that the number of vertically and horizontally oriented engines is determined by the size and purpose of the aircraft, control of the aircraft, its maneuvering is carried out by changing the thrust of the engines, if there is one vertically oriented engine, the axis of its nozzle coincides with the center of gravity of the aircraft, and if there are several, the center of gravity is located between them.

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