RU2301349C2 - Rotary sector turbine engine - Google Patents

Abstract

FIELD: mechanical engineering; rotary internal combustion engines.

SUBSTANCE: proposed rotary sector turbine engine contains engine and gas turbine. Engine has body-stator with space of regular cylindrical form where rotor disk is installed on shaft. Body-stator and rotor disk are divided into main sectors consisting of filling up sectors. Elements of working chambers with intake channels, electric spark plugs and exhaust channels are main in body-stator in main sectors on filling sectors. Elements of sealed working chambers are made on rotor disk in filling sectors. In process of rotation, elements of working chambers of rotor and body-stator form, in succession, metering chambers with intake channels to combustion chambers with spark plugs and exhaust channels in which operating processes of internal combustion engine take place in all chambers and in all main sectors simultaneously. Intake and exhaust channels are opened and closed by disk of rotor at its rotation. Full turn of engine shaft is provided at operation of number of combustion chambers of engine equal to square of number of main sectors on engine multiplied by number of filling sectors in main sector. Rotary sector engine and gas turbine are fitted on one shaft. Flows of hot gases from combustion chambers of constant shape and constant volume of rotary sector engine are directed under high pressure to blades of gas turbine through nozzle assemblies made in body-stator or diaphragm in number equal to number of main sectors on engine which are uniformly distributed over perimeter of body-stator. Hot gases are directed to gas turbine in interrupted portions.

EFFECT: improved specific performance characteristics of rotary stator engines and gas turbines.

2 cl, 5 dwg

Description

The invention relates to mechanical engineering, namely to internal combustion engines without using a crankshaft, which use the work of the pulse of ignition and expansion of the combustion products of the fuel, which is perceived by the walls of the sealed combustion chambers on the rotor disks and the turbine cavities in the cavities of the stator bodies.

According to the method of mixture formation, engines relate to engines with external mixture formation of liquid fuel in a pipeline, followed by injection by a pump, and a gas mixer when a combustible working mixture of gaseous fuel and air is supplied, and mixed mixture formation when using multicomponent fuel. Ignition is carried out by spark plugs.

Known internal combustion engines without using a crankshaft. They can be divided into engines in which the work of expanding the combustion products is perceived by rotor blades mounted on disks or drums of rotation of the shaft, in which there is a certain gap between the edges of the blades and the internal faces of the cavities of the stators, and structures with a gap between the edges of the walls of the combustion chambers and the internal cavity of the opening in the stator housing is completely closed and each combustion chamber in the engines is tight.

The first include turbine, gas turbine, turboprop, turbojet engines, in which the work of expanding the products of combustion of fuel is perceived by working blades fixed in disks or in drums of rotation of the shaft.

Continuous-shape continuous combustion chambers (PF) and constant volume (PO) are installed directly and motionless on the motor stator housing. Such engines are mainly used in aircraft power plants.

Known gas turbine installation with the combustion of fuel in a constant volume. The engine is twin-shaft. Combustion chambers of constant shape and constant volume are separated from the turbine. Combustion products, having elevated pressure and temperature, rush through nozzles to traction turbines that are mounted on the engine output shaft (RF patent No. 2147341, publ. 2000.04.10).

Famous rotary piston internal combustion engine F. Wankel (Dictionary-reference mechanisms. A.F. Krainev. "Engineering", 1981, p.31). In the stator housing of the engine there is a cavity of complex configuration, with which the rotor-piston is in contact, the profile of which is made according to the epitrochoid. The triangular rotor-piston is mounted so that it can rotate on an eccentric shaft rigidly connected to the gear wheel. The wheel interacts with the fixed wheel. A rotor piston with a wheel is run in on a fixed wheel. Its faces glide over the surface of the cylinder, cutting off the variable volumes of the chambers. The injection of the working mixture is carried out through the inlet channel, the mixture is ignited from the spark plug. The exhaust gas is produced through a special exhaust channel. Rotating around a stationary gear along a complex curve, the rotor-piston touches the outer surfaces of the inner walls of the cylinder stator housing. To seal the combustion chambers installed on the rotor-piston at the vertices of the "triangle", it seems the rotor-piston in the context, the sealing plate, which under the action of centrifugal force is pressed against the housing. During the rotation of the rotor-piston, the volumes of the chambers formed between its surfaces and the walls of the cavity of the housing change sequentially. In these chambers, the processes of intake, compression and ignition of the fuel, expansion and exhaust gas flow take place. Opening and closing of the inlet and outlet channels are carried out by the rotor-piston itself. In the engine for one revolution of the rotor-piston, all the working processes of a conventional four-stroke engine occur, and simultaneously, but in different working chambers: three flashes of fuel, three working strokes, three exhaust emissions, three inlets of a fresh portion of fuel. The engine is high-speed, compact, light in weight. The main reason for its long development is the problem with the compaction of combustion chambers, i.e. difficulty with hermetic overlap in the epitrochoid stator cavity. On one shaft, only two such engines are mated.

The rotary sector internal combustion engine (RSDVS) (see RF patent No. 2235895, published September 10, 2004) contains a stator housing with a cavity of regular cylindrical shape, in which a rotor disk with elements of working chambers PF and PO is installed on the shaft. Elements of working chambers with inlet, outlet and purge channels and installed electric spark plugs are made on the stator housing. During external mixture formation, liquid fuel is injected under pressure, the gas working mixture is supplied through a gas mixer, and multicomponent fuel is supplied in a mixed way.

The stator housing and the rotor disk of the engine are divided into main and filling sectors. The main sectors consist of filling sectors. Elements of working chambers with inlet, outlet and purge channels and with installed electric spark plugs are made in the main sectors of the stator housings. Elements of sealed working chambers are made on the rotor disk in the filling sectors. During rotation, the elements of the working chambers on the stator housing and the rotor disk are combined and form metering chambers, into which a certain subsequent portion of the finished working mixture is set, a combustion chamber with spark plugs and with exhaust and purge channels. In them, the processes of injection of the finished working mixture of fuel, ignition of this mixture, stroke, removal of combustion products. The opening and closing of the inlet, outlet and purge channels is carried out by the rotor disks during their rotation. The processes in the main sectors proceed simultaneously. A full revolution of the engine shaft is carried out when the number of combustion chambers on the rotor disk is triggered, equal to the square of the number of main sectors multiplied by the number of filling sectors in the main sector. These are rotary sector motors of types

- роторный секторный двигатель с «n» количеством основных секторов и минимальным количеством заполняющих секторов ("с"), равным 3 в основном секторе;

- a rotary sector engine with “n” the number of main sectors and a minimum number of filling sectors (“c”) equal to 3 in the main sector;

- роторный секторный двигатель с «n» количеством основных секторов и с минимальным количеством заполняющих секторов «с» в основном секторе, плюс еще заполняющий сектор «а», установленный в основном секторе до заполняющего сектора с камерой сгорания со свечой зажигания;

- a rotary sector engine with “n” the number of main sectors and with a minimum number of filling sectors “c” in the main sector, plus a filling sector “a” installed in the main sector before the filling sector with a combustion chamber with a spark plug;

- роторный секторный двигатель с «n» количеством основных секторов с одним дополнительным заполняющим сектором «b» после заполняющего сектора со свечой зажигания в основном секторе, в котором выполнены исходящие сопла.

- a rotary sector engine with "n" the number of main sectors with one additional filling sector "b" after the filling sector with a spark plug in the main sector in which the outgoing nozzles are made.

из камер сгорания выбрасывается поток расширенных горячих газов с высоким давлением, который не используется.In a rotary sector engine, which provides for the use of high-class fuel in engines of types

a stream of expanded hot gas with high pressure that is not used is emitted from the combustion chambers.

An object of the invention is to increase the specific performance of rotary sector engines and gas turbines.

The technical problem is solved in a rotary sector turbine internal combustion engine containing a rotary sector engine and a gas turbine, the rotary sector engine has a stator housing with a cavity of regular cylindrical shape, where a rotor disk is installed on the shaft, the stator housing and the rotor disk are divided into main sectors, the main sectors consist of filling sectors; on the stator housing in the main sectors, elements of working chambers with inlet channels, electric spark plugs and sknymi channels on the rotor disk in sector filling elements made of sealed working chambers. During rotation, the elements of the working chambers of the rotor and the stator housing are sequentially compiled into dispenser chambers with inlet channels, into combustion chambers with spark plugs and exhaust channels, in which processes of the internal combustion engine occur, moreover, in all chambers and in all main sectors simultaneously. Opening and closing of the inlet and outlet channels are carried out by the rotor disk during its rotation. A full revolution of the engine shaft occurs when the number of combustion chambers on the engine is triggered, equal to the square of the number of main sectors on the engine times the number of filling sectors in the main sector. According to the invention, the rotary sector engine and the gas turbine are made on the same shaft, the hot gas flows from the combustion chambers of constant shape and constant volume of the rotary sector engine under high pressure are directed to the blades of the gas turbine through nozzle devices made in the stator or diaphragm body in an amount equal to the number of main sectors on the engine, which are uniformly distributed around the perimeter of the stator housing, while hot gases are sent to the gas turbine in intermittent portions. Several rotary sectorial turbo engines can be placed on one shaft of a single unit.

The operation of a gas turbine in conjunction with a rotary engine is different from that of conventional conventional gas turbines.

High-pressure expanded hot gas flows to known gas turbines are supplied from PF and PO combustion chambers installed directly on the engine casing. In rotary sector turbo-engines, combustion chambers are mounted on rotor disks.

Combustion chambers installed on known gas turbines are fixedly mounted and are involved indirectly in transmitting torque to the engine shaft by transferring the energy of the hot gas stream to the turbine blades. In rotary sector turbo engines, the combustion chambers themselves are directly involved in transmitting torque to the engine shaft and direct the flow of hot gases through nozzle devices to the turbine blades.

Hot gas flows to known gas turbines are sent to the nozzle apparatus by the same combustion chamber. In rotary sector turbo engines, the flow of hot gases through the same nozzle apparatus is sent periodically, in several portions, from successively suitable combustion chambers to the nozzle apparatus on the rotor disks.

Hot gas flows to known gas turbines are sent by the same combustion chamber in a continuous stream. In rotary sector engines, hot gas flows are sent intermittently. Only the fast rotation of the rotor disk ensures the continuity of the flow of hot gases with high pressure to the gas turbine design.

The kinetic energy flows of the product are sent to known gas turbines by a single nozzle apparatus. In rotary sector engines, hot gas flows are sent by the number of nozzle devices equal to the number of main sectors of the rotary sector engine in the direction of the gas turbine.

Drawings illustrating the invention:

и газовой турбиной;figure 1 - rotary sector turbo engine with a rotary sector type engine

and gas turbine;

figure 2 is a section along A;

figure 3 is a section along b;

4 and 5 are diagrams of the operation of a gas turbine.

содержит корпус-статор 1 с полостью 2 правильной цилиндрической формы, в которой с минимальным зазором установлен на валу 3 диск 4 ротора с рабочими камерами 5 постоянной формы и постоянного объема. На корпусе-статоре 1 выполнены впускные каналы 6 и сопловые аппараты 7 в диафрагме 8 и установлены свечи зажигания 9. При внешнем смесеобразовании жидкое топливо впрыскивается под давлением или газовая рабочая смесь подается через газосмеситель (не показаны). Корпус-статор 1 и диск ротора 4 разбиты на основные 10 и заполняющие секторы, в которых выполнены элементы герметичных рабочих камер 5. В каждом основном секторе 10 корпуса-статора 1 выполнены части рабочих камер с впускными каналами 6, сопловыми аппаратами 7 и установленными свечами зажигания 9. В диске ротора 4 выполнены элементы рабочих камер 5. В процессе вращения диска ротора 4 (работы двигателя) из частей рабочих камер на корпусе-статоре 1 и диске ротора при совмещении образуются совместно с частями рабочих камер на корпусе-статоре с впускными каналами 6 дозаторные камеры, в которых накапливается последующая порция газовой рабочей смеси. При совмещении частей рабочих камер на диске ротора с частями рабочих камер с установленными на корпусе-статоре с электрическими свечами зажигания и с соплами образуются камеры сгорания.A rotary sector turbo engine consists of an internal combustion engine without using a crankshaft — a rotary sector engine and a gas turbine mounted on the same shaft. Type Rotary Sector Motor

comprises a stator housing 1 with a cavity 2 of regular cylindrical shape, in which a rotor disk 4 with working chambers 5 of constant shape and constant volume is mounted on the shaft 3 with a minimum clearance. On the stator housing 1, inlet channels 6 and nozzle apparatuses 7 in the diaphragm 8 are made and spark plugs 9 are installed. During external mixture formation, liquid fuel is injected under pressure or the gas working mixture is supplied through a gas mixer (not shown). The stator housing 1 and the rotor disk 4 are divided into main 10 and filling sectors, in which the elements of hermetic working chambers are made 5. In each main sector 10 of the stator casing 1, parts of the working chambers with inlet channels 6, nozzle devices 7 and installed spark plugs are made 9. Elements of the working chambers are made in the rotor disk 4. During the rotation of the rotor disk 4 (engine operation) from the parts of the working chambers on the stator housing 1 and the rotor disk, when combined, they are formed together with the parts of the working chambers on the stator housing with the inlet and channels 6 metering chambers in which a subsequent portion of the gas working mixture is accumulated. When combining the parts of the working chambers on the rotor disk with the parts of the working chambers installed on the stator housing with electric spark plugs and nozzles, combustion chambers are formed.

On the disk 4 of the rotor along the borders of the parts of the working chambers 5, grooves 11 are made for installing sealing plates 12 on them.

Processes in all major sectors occur simultaneously. A full revolution of the engine shaft is carried out when the number of combustion chambers 5 on the rotor disk 4 is activated, which is equal to the square of the number of main sectors 10 times the number of filling sectors in the main sector 10.

(фиг.1-3) установлена газовая турбина 13 с лопастями 14, закрепленными на барабане 15, и с соплами 16. Поток горячих газов от роторного секторного двигателя под высоким давлением направляется через сопловые аппараты 7, выполненные в диафрагме 8 или корпусе-секторе 1, по периметру (на чертеже - стрелка с одним штрихом), на лопасти 14 газовой турбины 13. Турбина вращается. Отработавший газ выходит через выходные сопла 16 (стрелка с двумя штрихами). И РСДВС, и газовая турбина работают на одном валу. На валу установлены подшипники 17.On the shaft 3 motor type

(Fig.1-3) a gas turbine 13 with blades 14 mounted on the drum 15 and nozzles 16. is installed. The flow of hot gases from the rotary sector engine under high pressure is directed through nozzle devices 7 made in the diaphragm 8 or the housing sector 1 along the perimeter (in the drawing - an arrow with one stroke), on the blades 14 of the gas turbine 13. The turbine rotates. The exhaust gas exits through the outlet nozzles 16 (arrow with two strokes). Both the RSDVS and the gas turbine operate on the same shaft. Bearings 17 are mounted on the shaft.

на газовую турбину направляется прерывистый поток горячих газов из четырех сопловых аппаратов, установленных через 90° по периметру корпуса-статора (фиг.5) с подачей силы потока горячих газов F. Рассмотрим работу сопряженной газовой турбины с роторным секторным турбодвигателем.In rotary sector motor type

an intermittent flow of hot gases from four nozzle devices is sent to the gas turbine, installed 90 ° along the perimeter of the stator casing (Fig. 5) with the supply of hot gas flow force F. Let us consider the operation of the conjugated gas turbine with a rotary sector turbo engine.

таких точек - 4. Принимаем КПД силы F на газовой турбине по патенту РФ №2147341 (см. в описании работу устройства на фиг.3), равным единице. В роторном секторном турбодвигателе принимаем КПД, равным 0,5. Будем считать F=2F', где F' - сила, приложенная к одной лопасти. Силы F' приложены к четырем лопастям (L) турбины (L_1÷4) (фиг.4, 5). Под приложением сил горячего газа продукта F'_1÷4 турбина поворачивается на угол 90°. На лопасть L₁ действует момент силы F'₁, равный M₁=F'₁·r. В это же время на лопасть L₂ действует сила F'₂, момент силы - M₂=F'₂·r. На лопасть L₃ соответственно действует момент М₃=F'₃·r, на лопасть L₃ - M₄=F'₄·r.We determine the moment of force M relative to the axis (shaft) of rotation (see figure 4) according to the formula M = F · l (see the problem book in physics, A.G. Chertov, A.A. Vorobyov, M.F. Fedorov, M ., "Higher School, 1973, p.40, formula 1.77), where l is the shortest distance from the axis of rotation to the line of action of the force F or M = F · r · sinα (see ibid., Formula 1.78), where r - the distance from the axis of rotation to the point of application of force F, α is the angle between the direction of action of the force and the radius vector r drawn from the axis of rotation to the point of application of force. We accept the application of forces at one point in one direction and all the time at an angle equal to and and seeking to 90 °. Then M = F · r · l. The rotary sectorial turbo sectoral rotary engine type

such points - 4. We accept the efficiency of force F on a gas turbine according to the patent of the Russian Federation No. 2147341 (see the description of the operation of the device in figure 3), equal to unity. In a rotary sector turbo engine, we take an efficiency equal to 0.5. We will consider F = 2F ', where F' is the force applied to one blade. Forces F 'are applied to the four blades (L) of the turbine (L _{1 ÷ 4} ) (Figs. 4, 5). Under the application of hot gas forces of the product F ' _{1 ÷ 4, the} turbine rotates through an angle of 90 °. On the blade L ₁ acts the moment of force F ' ₁ equal to M ₁ = F' ₁ · r. At the same time the lobe L ₂ a force F _'2, the moment of force - M ₂ = F' ₂ · r. L on the blade _3, respectively ₃ acting moment M = F _'3 · r, the blade L ₃ - M ₄ = F' ₄ · r.

So, the moments of the sum of forces F ' _{1 ÷ 4} · r relative to the axis of rotation acted on the turbine blades. Record the rotation:

The total moment of forces acting on the turbine shaft, at a rotation angle of 90 °, was

where T1 ÷ T4 are the points of application of forces to the blades.

Thus, for a full revolution of the turbine shaft, the moment of forces relative to the axis of the turbine shaft was M ₄ = 4 · 4 · F '· r = 16F · r, where M ₄ is the sum of the moments of forces relative to the axis of the turbine shaft with four nozzle devices.

Even if the force F 'equated to _^1/2 F, then one turn of the shaft of the turbine will operate or force applied torques

M₄=8Fr.

M ₄ = 8Fr.

We define the work (A) of a constant moment of force acting on a rotating body (turbine)

A = Mφ (see the problem book on physics "Higher School" A.G. Chertov et al., 1973, M., p. 42 - table). Then A ₄ = 8Frφ, where A ₄ is the work of the constant moment of forces acting on the turbine with four nozzle devices, where φ is the rotation by one revolution: φ = 2πN, where N is the rotation frequency.

All calculations are carried out per revolution: φ = 2 · 3.14 · 1 rad = 6.28 rad. Substitute in the previously obtained: A ₄ = 8 · F · r · 6.28; A ₄ ≈48Fr kgcm (kilogram force meter).

Now, compare with the work performed by four turbines with the supply of hot gas forces through a single nozzle apparatus (see figure 4). The moment of forces relative to the axis of rotation of one gas turbine with one nozzle apparatus: M ₁ = Fl, where M ₁ is the moment of forces with one nozzle apparatus, the values of F, r, sinα are taken equal for all calculations. Count on one revolution of the shaft. The work performed by four gas turbines with one nozzle apparatus: 4A ₁ = 4F · r · 2 · 3,14 · 1; 4A ₁ ≈24Fr, assuming the work of hot gas flow forces with a coefficient equal to unity.

Let us compare the work performed by one gas turbine of a rotary sector turbo engine with the work performed by four turbines with one nozzle apparatus with the application of the same hot gas flow forces: A ₄ ≈48Fr kgcm and 4A ₁ = 24Fr kgcm (kilogram force meter).

A rotary sector turbo engine uses the advantages of a rotary sector engine and a gas turbine, engine power is increased and economic qualities are improved, because the gas flow is dosed and controlled by working chambers of the RSD, a smoother stroke of the rotor sector turbo engine is provided.

One gas turbine in a rotary sector turbo engine (with equal initial data) will have a capacity of at least "n" gas turbines with one nozzle device (where "n" is the number of main sectors on the engine).

Rotary sector turbo engine operates as follows.

) на лопасти 14 турбины на протяжении ~90° одновременно со всех четырех сопловых аппаратов каждый, через исходящие сопла 16.The starter rotates the shaft 3 RSDVS. From the inlet channels 6 to the composed working chambers 5, the finished working mixture enters. During rotation, the working chambers turn into metering chambers. With a rotation by the size of one filling sector, the metering chambers in the region of the electric spark plug 9 are converted into combustion chambers. An electric current is supplied, a spark appears, a fuel flash occurs, a flash pulse occurs, followed by the expansion of hot gases that press on the front walls of the combustion chambers and transmit torque to the rotor disk and, accordingly, torque to the motor shaft. With further rotation of the combustion chamber 5 are in the area of the outgoing nozzles 7 RSDVS. Expanded hot gas under high pressure rushes into the nozzle apparatus 7, the gas flow presses on the blades 14 of the gas turbine 13, causing it to rotate. Gases press (in type RSDVS

) on the turbine blades 14 over ~ 90 ° simultaneously from all four nozzle devices each, through outgoing nozzles 16.

The whole process in a rotary sector turbo engine occurs simultaneously in all working chambers.

, причем дополнительный заполняющий сектор также имеет исходящее сопло. При применении многокомпонентной рабочей смеси и ее особых условий применения используются РСДВС типов

или

.To increase the time of release of the product from the engine (if necessary), engines of the type

moreover, the additional filling sector also has an outgoing nozzle. When using a multicomponent working mixture and its special conditions of use, RSDVS types are used

or

.

Several rotary sector turbo engines are located on the same shaft of a single unit.

Rotary sector turbo engines are possible for driving vehicles and in stationary installations.

Claims (2)

1. A rotary sectorial internal combustion turbo engine, comprising a rotary sectorial engine and a gas turbine, the rotary sectorial engine has a stator housing with a cavity of regular cylindrical shape, where a rotor disk is installed on the shaft, the stator housing and the rotor disk are divided into main sectors, the main sectors are of the filling sectors, on the stator case in the main sectors for the filling sectors, the elements of the working chambers with inlet channels, electric spark plugs and exhaust channels, on the disk In the filling sectors, elements of sealed working chambers are made, during rotation, the elements of the working chambers of the rotor and the stator housing are sequentially compiled into metering chambers with inlet channels, into combustion chambers with spark plugs and exhaust channels in which the processes of the internal combustion engine proceed, in all chambers and in all major sectors at the same time, the opening and closing of the inlet and outlet channels is carried out by the rotor disk during its rotation, and the full rotation of the motor shaft is carried out with working the number of combustion chambers on the engine equal to the square of the number of main sectors on the engine times the number of filling sectors in the main sector, characterized in that the rotary sector engine and gas turbine are made on the same shaft, the flow of hot gases from the combustion chambers of constant shape and constant volume of the rotor a high-pressure sector engine is directed to the blades of a gas turbine through nozzle devices made in a stator housing or diaphragm in an amount equal to two main sectors on the engine, which are evenly distributed around the perimeter of the stator housing, while hot gases are sent to the gas turbine in intermittent portions. 2. The engine according to claim 1, characterized in that several rotary sectorial turbo engines are located on the same shaft of a single unit.

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