RU2417U1 - ROTARY REACTIVE ENGINE - Google Patents

Abstract

A rotary-jet engine comprising a housing, an axial compressor, combustion chambers, a fuel mixture supply, ignition and purge system, characterized in that in each axial compressor located in the right and left rotary compressor compartments of the detachable housing, rigidly fixed at both ends the shaft passing through all the compartments of the casing and installed perpendicular to the longitudinal axis of the jet engine, the blades are made of three stages, and each stage is at a different angle to the longitudinal axis of the compressor, with in which the guide stage of the blade located at the inlet forms an angle of up to 40-50, the compressor stage is from 0 to 10 and the drop stage is up to 70 - 80, and the compressor surface is divided into several identical sectors, within each of which the length of the guide stage of each blade is gradually increased and at the compressor stage of each blade the thickness is gradually increased towards the discharge stage, the thickness of the latter is constant and its side planes form slotted channels with the side planes of adjacent blades, with At the end of the last stage of each compressor, a rotary internal combustion engine (ICE) is installed, the rotor of which is integral with the shaft, and the outer diameter of the rotor is located in the disk-shaped part of the rotor-compression compartment housing, in which through cylindrical compressed air supply channels are made, the centers of sections of which are evenly spaced around the circumference, and the axis of each channel is in the longitudinal axial plane of the rotary internal combustion engine, and in the stationary disk of the housing, the supply channels are compressed

Description

PQTQPHQ-REACTIVE DIGITOR

The invention relates to a variety of jet, aircraft engines, namely, rotary-reactive.

As a prototype, a turbojet single-circuit engine 1 was selected. These engines differ in relative structural and technological; simplicity and quite widely used: on airplanes and aircraft with subsonic and supersonic flight speeds. Them. dignity is a significant increase in thrust with an increase in speed, especially on supersonic aircraft.

The main disadvantage of the turbojet engine is its high fuel consumption, which limits the flight range and increases the cost of their operation. For these reasons, at present, new aircraft with turbojet engines, as a rule, are not designed.

Known axial compressor containing a cylindrical body and placed in it a rotor with impellers equipped with a friction or gear drive of counter-rotation of the wheels 2J. The blades of each wheel are slotted. The disadvantage of this compressor is the design complexity and low pressure created during its operation, due to the large angle of inclination of the blades to the longitudinal axis of rotation.

Also known axial, multi-stage: a compressor containing the impellers and guide vanes 3, in which in the first steps, in the middle and last steps, the inclination angle of the output, the edges of the guide vanes, respectively, is 65-70, 60-65. The disadvantage of this compressor is its bulkiness and complexity in manufacturing. This design contributes to the occurrence of air turbulence in the inter-blade channels., Which leads to a decrease in pressure, characteristics and loss of efficiency.

The purpose of the invention is to increase the pressure characteristics of the compressor, engine life and power of a rotary-jet engine, its economy, as well as increasing safety and speed, while simplifying the design and maintenance. This goal is achieved by the fact that in a rotary-jet engine containing a housing, an axial compressor, a combustion chamber, a fuel mixture supply system, ignition and purge, according to the invention in each axial compressor located in the right and left rotorIf /

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but-compression compartments of the detachable case, rigidly fixed at both ends of the shaft passing through all the compartments of the case and installed perpendicular to the longitudinal axis of the jet engine, its blades are made of three-stage, and. each step is at a different angle to the longitudinal axis. compressor, with which the guide stage of the lobes located at the inlet forms an angle of up to 40 50 50 °, the compression stage is from O to 10 ° and the discharge stage is up to 70--80. The cylinder surface of the compressor is divided into several identical sectors, within each of which; there is a gradual increase in the length of the guide stage of each blade, which contributes to the formation of an air intake CAVITY, and the compression stage of each blade gradually increases the thickness towards the discharge stage. The thickness of the latter remains constant, and its lateral planes: form slotted channels with the lateral planes of adjacent blades. A rotary internal combustion engine is installed on a single shaft at the end of the last stage of each compressor, the rotor of which is made integral with the shaft, and the outer diameter of the rotor is installed in the disk-shaped part of the rotor-compression compartment housing. Through cylindrical channels of compressed air supply are made into the atomic disk of the casing. The centers of the sections of these channels are evenly spaced around the circumference, and the axis of each channel is located in the longitudinal axial plane of the internal combustion engine., Whose rotor is located coaxially with its body. In the disk of the fixed housing, the arrangement of the cylindrical channels alternates with the mixing chambers. The cross section of the rotor is conditionally divided into several sectors, within each of which a longitudinal groove is made for: supply of compressed air connected to the compressor high pressure cavity, the ignition chamber connected to the base of the combustion chamber by a channel, opposite; the wall of which has nozzle channels located at an angle of 30-45 ° to the end plane of the rotor, through - a purge groove connected to the high-pressure cavity of the compressor. Longitudinal fuel channels are made in the engine rotor body of the internal combustion engine, radial from which are diverted into each sector of the rotor, flowing into the storage chambers, from the latter, in turn, nozzle nozzles. On the inner end surface of the body of the rotary internal combustion engine, thrust steps are made in the form of triangular grooves, straight at the corner, grooves extending from the junction lines of the planes connecting the cavity of the combustion chamber of the rotary engine with the installation area of the combustion engine of the jet engine. In space

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me} to the cameras burning up. jet engine: passes, a single shaft and two compressors, there is a nozzle, part of the jet engine housing, and the end surfaces of the combustion chambers are docked to the front frontal wall of the jet engine housing.

The rotary-reactive engine is illustrated by two drawings. Figure 1 presents a top view, figure 2, section A-A, figure 3, rotary two with compressor, section AA - figure 4, figure 5 is a view along arrow B of the axial compressor, figure 6 view along arrow B on the axial compressor blades.

A rotary-jet engine consists of a housing 1., which has three compartments: a right and left compartment for installing an axial three-stage compressor and a rotary internal combustion engine in the cradle, as well as an installation area for the combustion chambers of a jet engine located in the middle, with a frontal one a closed wall, in which the combustion chambers abut against the end surface, and a jet nozzle on the opposite side. In the housing 1, on the shaft 2, three-stage axial compressors 3 are installed, the blades of which consist of guide parts 4 that create: air movement, compression parts 5 that create pressure, discharge parts 6 that lock, compressed air into a narrow inter-blade space, disk-shaped, part of the body 7, through cylindrical compressed air supply channels 8, mixing chambers 9, two rotor 10, longitudinal groove for compressed air supply 11, ignition chamber 12, connecting channels 26, combustion chamber 13, nozzle channels 14 and 25, through products inlet, groove 15, high pressure cavity of compressor 16, longitudinal fuel channels of the rotor two 17, from which radial channels 18 are discharged, which flow into the accumulating fuel chambers 19, from which the nozzle nozzles 2Q, stop stages 21 / on the internal end surface of the engine rotor case are discharged, slotted channels 22, a combustion chamber of a jet engine 23 and 24.

The rotary-jet engine operates as follows. Rotation of axial compressors is carried out from rotary internal combustion engines. When the compressor rotates, the guide stages of the blades, as a result of their significant inclination, take air and supply it further to their compression stages. The compression surfaces of the blades create maximum pressure. The pressure created by the blade moving in front is compensated by an increase in its thickness. Thus compressed air enters the inter-blade slotted channel. The angle of inclination of the discharge stage of 70-80 prevents the reverse movement of air, in case of sharp

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increasing pressure behind the compressor, and increases the rate of flow of air,

A rotary-jet engine can operate with two, or with one two in: jet engine mode. Work in jet engine mode is as follows. Internal combustion engines drive axial three-stage compressors, which, through purge channels, located in the disk-shaped part of the casing, are rotary compression 1x. compartments serve compressed air. in the installation area of the combustion chambers of a jet engine. with the help of nozzles, fuel is supplied. The resulting fuel mixture is ignited, and the jet of jet gas rushes into the nozzle.

A rotary internal combustion engine operates as follows. Fuel through the holes in the rotor shaft through the longitudinal channels 17 and radial 18, which are diverted from them, is supplied to the accumulation chambers 19, of which through the nozzle nozzles 20 it enters the mixing chambers 9. Then, when the rotor of the ICE 10 rotates, the mixing chambers 9 of the housing combined with the longitudinal grooves li of the rotor, through which compressed air flows from the high pressure cavity 16 of the compressor 3 into the mixing chambers, forming a finished fuel mixture for combustion. With further rotation of the rotor, the ignition chamber 12 is combined with the mixing chamber 9, after which the fuel mixture ignites. The ignition chamber is connected by a channel 26 to the combustion chamber 13, with which the mixing chamber is further combined. The ignited fuel ignited and began to burn. In this case, formed; from combustion, the gases in the blast wave hit the walls of the combustion chamber and rush along the nozzle channels 14 located tangentially to the inner cylindrical surface of the body of the internal combustion engine, thereby driving the internal combustion engine rotor. Then the compressed gases through the nozzle channels 25, leaving the combustion chamber at an angle of 30-45. to the end plane of the rotor, they are directed to the inner end surface of the ICE body, on which the thrust stages 21 are made, further perceiving the impacts of the nozzle jets of gas, creating additional rotation of the ICE rotor. Slit channels 22 depart from the junction line of the planes of the persistent steps. The gases escape through these slotted channels to the area of the combustion chambers 23, where they burn out.

"4 2. The use of internal combustion engines, simpler to manufacture, replaced the expensive, and the natal: gas turbine.

3. The exhaust gases of the internal combustion engine enter the general line of compressed air and together with it enter the combustion chamber, where they completely burn out.

4. Application in the design of two: combustion chambers, allows to increase them. volume and, therefore, temperature, which significantly increases engine power.

5. The engine power is increased due to the operation of two compressors,

6. The end walls of the combustion chambers abut against the frontal wall of the engine casing, which is a hard stop for pushing burning gases, thereby increasing engine power and speed.,

7. Since each compressor is equipped with a rotary engine and they are all mounted on a single shaft, therefore, in small and medium modes, one or the other engine can alternately work.

8. Since there is no turbine, the safety of head-on collisions in flight with foreign objects increases.

Information sources:

1. Design and engineering of aircraft gas turbine engines. Under the general editorship of Dr. D.V.ronin.

Moscow, Mechanical Engineering. 1989, p. 5.

2. Copyright certificate f-216176 class P04 29/38, 1971

3. The certificate of authorship No. 953271 cells, P04s 19 / B2, 1982. Author

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 § / A iLE.Popkov

Claims (1)

A rotary-jet engine comprising a housing, an axial compressor, combustion chambers, a fuel mixture supply, ignition and purge system, characterized in that in each axial compressor located in the right and left rotary compressor compartments of the detachable housing, rigidly fixed at both ends the shaft passing through all the compartments of the casing and installed perpendicular to the longitudinal axis of the jet engine, the blades are made of three stages, and each stage is at a different angle to the longitudinal axis of the compressor, with which the guide stage of the blade located at the entrance forms an angle of up to 40 - 50 ^o , the compressor stage is from 0 to 10 ^o and the drop stage is up to 70 - 80 ^o , and the compressor surface is divided into several identical sectors, within each of which the length of the guide stage of each blade is gradually increased, and at the compressor stage of each blade the thickness is gradually increased towards the discharge stage, the thickness of the latter is constant and its side planes form slotted channels with the side planes of adjacent blades moreover, at the end of the last stage of each compressor, a rotary internal combustion engine (ICE) is installed, the rotor of which is made integral with the shaft, and the outer diameter of the rotor is located in the disk-shaped part of the housing of the rotor-compression compartment, in which through cylindrical compressed air supply channels are made, section centers which are evenly spaced around the circumference, and the axis of each channel is in the longitudinal axial plane of the rotary internal combustion engine, and in the stationary disk of the housing feed channels and compressed air alternate around the circumference with the mixing chambers, and the rotor cross section is divided into sectors, within each of which there is a longitudinal groove for supplying compressed air connected to the compressor high pressure cavity, an ignition chamber connected by a channel to the base of the combustion chamber, the opposite wall which has nozzle channels located at an angle of 30 - 45 ^o to the end plane of the rotor, a through purge groove connected to the high-pressure cavity of the compressor, while in the rotor body ICE made longitudinal fuel channels, from which radial channels are diverted to each sector of the rotor, communicating with storage chambers, the latter, in turn, are diverted nozzle nozzles, and on the inner end surface of the body of the rotary ICE thrust steps are made in the form of triangular with a right angle grooves, from the junction of the planes of which slit channels extend, connecting the cavity of the combustion chambers of the rotary engine with the installation zone of the combustion chambers of the jet engine, in the space between the combustion chambers A single shaft of internal combustion engines and compressors is mounted and the nozzle part of the jet engine housing is located, the end surfaces of the combustion chambers docked to the front frontal wall of the jet engine housing.