RU2276739C1 - Method and device for creating reactive thrust made in form of centrifugal ramjet engine - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention is designed for rotating propellers of different application. Proposed centrifugal ramjet engine contains combustion chamber 4 with reaction nozzle 5 to which compressed air is fed through inlet hole 3 and inlet air duct 2 with preliminary compression in compression chamber 6 owing to velocity head at movement of engine over circumference together with propeller blade 1 secured on engine shaft to end of which it is connected. Compressed air from compression chamber moves along radial air duct 7 into combustion chamber with acceleration under action of centrifugal force appearing at rotation of propeller. Air flow getting in specified order provides dynamic pressure onto wall of combustion chamber, thus ensuring additional compression of air, and fuel is combusted in said area of increased compression of air. Gaseous combustion products move at acceleration from combustion chamber through reaction nozzle, thus creating reactive thrust. Combined use of ramjet and centrifugal capabilities provides considerable compression of air which increases efficiency of engine in operation.

EFFECT: provision of effective engine of simple design and low weight.

3 cl, 1 dwg

Description

The invention relates to jet propulsion systems and is intended to bring into rotation the propellers for various purposes, mainly rotors of helicopters.

A known method of creating jet thrust, used in ramjet engines (ramjet), in which for the combustion of fuel use atmospheric oxygen, which is compressed by high-pressure (see "Polytechnical Dictionary". / Ed. By academician A.Yu. Ishlinsky, ed. . "Soviet Encyclopedia", M., - 1980, p. 420) (1).

The disadvantage of the aforementioned method of creating reactive thrust is the need to achieve a high speed of movement for its effective use.

The closest in combination of features with the claimed invention is a method of creating jet thrust, in which air compression is carried out by a high-speed pressure when the jet engine moves around a circle together with a blade fixed to the rotor shaft of the helicopter, said engine, an inlet, is attached to the end of said blade which is directed in the direction of movement, the combustion of fuel is carried out in compressed air in the combustion chamber, and the combustion products are sent to the jet nozzle to create Ia jet thrust (see. Russian patent 2127819, MPK 6 F 02 K 7/10, 20.03.99, Bulletin. №8) (2).

The disadvantage of this method of creating reactive thrust is air compression only due to the high-speed pressure with incomplete braking of its flow, which at the usual rotor speed reduces the efficiency of using this method.

A ramjet is known as a ramjet engine containing a diffuser that provides braking of the oncoming air stream and its compression, a combustion chamber and a jet nozzle (see (1), p. 420 and the diagram on p. 421).

The disadvantage of this ramjet is the possibility of its use only at a speed of movement significantly higher than the speed of sound.

The closest in combination of features with the claimed invention is a terminal jet engine containing an air duct with an inlet, which are turned in the direction of movement when the rotor of the helicopter is rotated, allowing high-pressure compression of the oncoming air flow with its subsequent use for burning fuel in the combustion chamber with the creation of reactive thrust during the expiration of combustion products through a jet nozzle (see (2) RF patent 2127819).

This engine does not provide air compression sufficient for its effective operation, due to the use of only one high-pressure head with incomplete braking of the air flow.

The present invention by a method of creating jet thrust and a device for its implementation allows to obtain a technical result, which consists in increasing the compression of air supplied to the combustion chamber, which allows to increase its efficiency and efficiency without significantly complicating the device and without increasing the mass.

The specified technical result on the method of creating jet thrust is achieved by the fact that air compression is carried out by the high-speed pressure when the air-jet engine moves around the circumference along with a blade fixed to the rotor shaft. Said engine is attached to the end of said blade, the engine air inlet is directed in the direction of travel, the fuel is combusted in compressed air in the combustion chamber, and the combustion products are sent to the jet nozzle to create jet thrust. According to the invention, in addition to the primary air compression by braking it in the inlet duct, additional air compression is carried out in front of the combustion chamber and directly in the combustion chamber. For this, a compression chamber located behind the inlet duct is used, in which, along with the above primary compression of the air due to its inhibition, the direction of movement of the air is changed with the rotation of its flow in a radial duct relative to the axis of rotation and further into the combustion chamber. In the radial duct, air is additionally accelerated by the action of centrifugal force upon rotation of the engine together with the rotor blade, then the air flow is braked in the cavity of the combustion chamber and the dynamic pressure of the specified air flow on the wall of the combustion chamber is used to convert its kinetic energy into compression and This area of greatest air compression produces combustion of fuel supplied from the nozzle. In this case, collectively use direct-flow and centrifugal air compression capabilities.

The specified method of creating jet thrust is carried out in a ramjet centrifugal jet engine, which is attached to the end of the rotor blade (for example, the rotor of the helicopter) and contains an inlet duct with an inlet that faces in the direction of movement when the rotor of the rotor of the helicopter is rotated to allow compression the high-pressure head of the oncoming air flow with its subsequent use for burning fuel in the combustion chamber with the creation of reactive thrust during the expiration of the combustion products through a jet nozzle. According to the invention, behind the inlet duct, a compression chamber, a radial duct, a combustion chamber and a jet nozzle are arranged in series, which are passages for air and gaseous products of combustion. At the same time, in the compression chamber it is possible to initially compress the air with an oncoming high-pressure head with simultaneous rotation of the air flow into the radial duct, where it is accelerated by centrifugal force, which makes it possible to additionally compress the air in the combustion chamber. Moreover, the walls of the compression chamber and the combustion chamber are barriers to the flow of air, providing the possibility of its braking and compression.

The outer surface of the wall of the combustion chamber and the jet nozzle are in the flow of oncoming air with the possibility of cooling.

In the drawing, a section along the axis of the engine shows the implementation of the method of creating jet thrust on the example of the corresponding device in the form of a direct-flow centrifugal jet engine. The arrows in the drawing show the direction of movement of air and combustion products.

The proposed method of creating jet thrust will be shown by the example of the operation of a direct-flow centrifugal jet engine, the description of which is given below.

The direct-flow centrifugal jet engine (PCVRD) is attached to the end of the blade 1, mainly to the rotor blade of the helicopter, and contains the inlet duct 2 with the inlet 3, which are turned in the direction of movement when the rotor of the helicopter rotates, allowing compression by the high-speed flow head oncoming air, followed by its use for burning fuel in the combustion chamber with the creation of reactive thrust during the expiration of the combustion products through the jet nozzle. Behind the inlet duct, a compression chamber 6, a radial duct 7, a combustion chamber 4, and a jet nozzle 5 are arranged in series, which are passages for air and gaseous products of combustion. In this case, in the compression chamber 6, it is possible to initially compress the air with a counter-flowing pressure with simultaneous rotation of the air flow into the radial duct 7, where it is accelerated by centrifugal force, which makes it possible to additionally compress the air in the combustion chamber 4. Moreover, the walls of the compression chamber 6 and combustion chambers 4 are barriers to the flow of air, providing the possibility of its braking and compression.

The outer surfaces of the walls of the combustion chamber 4 and the jet nozzle 5 are in the flow of oncoming air with the possibility of cooling. To control the intensity of the air flow washing the cooled surfaces of the combustion chamber and the jet nozzle, an external casing is used, covering the cooled surfaces, with a damper in its front part that controls the amount of air passed into the space between the casing and the combustion chamber.

Direct-flow centrifugal jet engine operates as follows.

When rotating, for example, a rotor of a helicopter, oncoming PCVRD blades 1 attached to the ends of its blades 1 are affected by oncoming air flows that enter the inlet 3 and then into the inlet duct 2 and the compression chamber 6. Under the action of the high-speed pressure and due to the inhibition of the air flow primary air compression occurs in the inlet duct 2 and compression chamber 6, which exceeds the compression of air in known ramjet engines, since there is no complete air braking in them and compression occurs in motion creeping flow only by reducing its speed. In contrast, in the proposed PCVRD, the wall of the compression chamber 6 is an insurmountable barrier to the flow of air, providing more significant compression. From the compression chamber 6, air is sent to the radial duct 7, where it is subjected to centrifugal force and gives it acceleration. The accelerated air flow from the radial duct 7 enters the combustion chamber 4 and acts on its wall with complete braking, which leads to additional significant compression of the air. A nozzle 8 spraying fuel is directed to the region of greatest air compression, with the possibility of its most intense combustion under the indicated conditions with a corresponding increase in temperature and pressure, which ensures the expiration of gaseous products of combustion through the jet nozzle 5 with a more significant acceleration, which ensures a corresponding increase in jet propulsion. This leads to increased efficiency and engine efficiency. Moreover, in the aggregate, direct-flow and centrifugal capabilities of air compression using simple means are used.

Claims (3)

1. The method of creating jet thrust, mainly to bring the rotor of the helicopter into rotation, in which the air is compressed by speed when the jet engine moves around the circumference, together with a blade mounted on the rotor shaft, the said engine, an input engine, is attached to the end of the blade the inlet of the engine inlet is directed in the direction of movement, the combustion of fuel is carried out in compressed air in the combustion chamber, and the gaseous products of combustion are sent to the reactive e nozzle for generating reactive thrust, characterized in that in addition to the primary compression of the air by braking it in the inlet duct, additional compression of the air is carried out in front of the combustion chamber and directly in the combustion chamber, in addition, a compression chamber located behind the inlet duct is used, in which, along with air compression in connection with its braking, they change the direction of air movement with the rotation of its flow in a radial air duct relative to the axis of rotation and further into the combustion chamber, in an additional radial air duct They accelerate the air by applying centrifugal force to it when the aforementioned engine rotates together with the rotor blade, then the created air flow is braked in the cavity of the engine combustion chamber and the dynamic pressure of this air flow on the wall of the combustion chamber is used to convert its kinetic energy into compression and in this area of the greatest air compression, the fuel supplied from the nozzle is burned, while in the aggregate they use direct-flow and centrifugal possibility of compressing air in said motor. 2. Direct-flow centrifugal jet engine, which is attached to the end of the blade of the main rotor of the helicopter, containing the inlet duct with an inlet, which is turned in the direction of movement when the rotor of the rotor of the helicopter is rotated to allow compression of the oncoming air flow with its subsequent use for burning fuel in the combustion chamber of the engine with the creation of reactive thrust during the expiration of gaseous products of combustion through a jet nozzle, characterized the fact that a compression chamber, a radial duct, a combustion chamber and a jet nozzle are arranged sequentially behind the inlet duct, which together are passage for air and gaseous products of combustion, while the compression chamber provides the possibility of primary air compression with a counter velocity head with simultaneous rotation of the air flow into the radial duct, where it is accelerated by centrifugal force in connection with the rotation of the aforementioned engine together with the rotor blade, which makes it possible the possibility of additional compression of air in the combustion chamber of the engine, while the walls of the compression chamber and the combustion chamber are barriers to the flow of air, providing the possibility of its braking and compression. 3. The engine according to claim 2, characterized in that the outer surface of the wall of the combustion chamber and the jet nozzle are in the flow of oncoming air with the possibility of cooling.