WO2023238148A1

WO2023238148A1 - Internal combustion jet engine

Info

Publication number: WO2023238148A1
Application number: PCT/IN2023/050527
Authority: WO
Inventors: Subhash SUPNEKAR
Original assignee: Supnekar Subhash
Priority date: 2022-06-06
Filing date: 2023-06-05
Publication date: 2023-12-14

Abstract

An internal combustion engine for jet engine (1000) comprising a converging and diverging combustion chamber (10), a cylindrical housing (20), a top flange(30), a bottom flange (40), plurality of nozzles, piping network includes oxygen supply line(210) gaseous fuel supply pipeline (220), liquid fuel supply line (230), plurality of conical piston valves (50,60,70), first storage tank(110) for storing pure liquid oxygen, second storage tank (120) for storing gaseous fuel, third storage tank (130) for storing liquid fuel, plurality of control valve (80, 90,100) for controlling the flow of fuel into the combustion chamber. The disclosed internal combustion engine which can be used for any type of fluid systems which can work on high pressure or ultrahigh pressure with more efficient manner.

Description

INTERNAL COMBUSTION JET ENGINE

FIELD OF INVENTION

The present invention generally relates to an internal combustion engine. More particularly this invention relates to internal combustion engine for the jet engine which uses pure liquid oxygen in internal combustion jet engine. More specially, the disclosed system is designed to use of pure liquid oxygen in internal combustion jet engine to improve the performance and combustion efficiency of it.

BACKGROUNND OF THE INVENTION

Airplane is a preferred kind of long-distance passenger transport. Now a days the volume and geography of worldwide travel are expanding. Progress in air transport is, however, attended by escalation of negative social and environmental factors that could reach critical levels unless an alternative is found to traditional airplane technologies. The problem requires development of new take-off and landing devices and methods to make flying safer and the airplane more friendly to the environment.

Airplane is an accepted name for a flying vehicle provided with an engine and a lifting wing. Modem airplanes, in particular, airliners that carry the bulk of air traffic worldwide, have a high cruising speed, large seating capacity, and a long range. They are equipped with reversible engines of high take-off and braking power, and complex take-off and landing high-lift devices, but the long landing strips of airfields is the only place where they realize the required lifting force capacities, at high airspeeds, and at significant angles of attack.

Generally, there are largest number of air accidents are caused due to intense takeoff and landing conditions. Many of them are related to loss of control upon engine failure, or failure of aerodynamic and mechanical take-off and landing devices under the effect of high operating strains imposed by conventional take- off and landing methods involving take-off and landing runs on the ground. A majority of accidents are traceable to human error. The accident rate and, still more important, the severity of catastrophes depend mostly on the high speeds of airplanes moving near or on the ground during take-off and landing by traditional methods. Without enough altitude or time to make decisions, especially in bad weather, the speed of required actions and workloads on pilots and ground operators reach critical levels, becoming the chief causes of human errors.

Due to high demand in transportation the seating capacities growing and range of airliners require higher take-off and landing speeds and greater take-off power of airliner engines. Accordingly, there is an increase in control degradation rates and severity of catastrophes occurring upon failure of engines, and elements of takeoff and landing high-lift devices, and aerodynamic stabilization devices. An estimated shortage of landing lifting force of long-range airliners requires dumping excess fuel in emergency situations so as to avoid complications of an accident. Greater take-off power of engines causes high noise levels and greater emissions. These high-power engines also require more fuel to produce high power. Therefore, there is a need to save more fuel and consequently high number of financial resources. To overcome these various problems enormous amounts of time and funds are spent on shuttling passengers between cities and airports. Considerable land areas and resources are withdrawn from other social needs to build and expand airports and numerous transport and supporting infrastructure facilities associated with airports. The population, nature, and structures in large districts of cities, suburbs, coastal areas, and water expanses are constantly exposed to the threat of air accidents.

The trend to build up engine take-off power, therefore, makes harder the efforts to deal with airliner safety and compatibility with the environment. In general practice take-off and landing techniques are based on methods for generating a lifting force and airplane stabilization forces and moments. Normally, there are three methods are used in aviation to produce a lifting force - aerodynamic, aerostatic, and fluid-dynamic. An aerodynamic method used in traditional airplanes to generate a lifting force consists in reducing pressure in the air flowing around the top wing surface relative to the pressure applied to the under surface. The engine thrust is smaller than the weight force of the airplane. A sufficient lifting force and sufficient velocity head of currents flowing around the surfaces of controlled aerodynamic surfaces are only produced when a certain airspeed (stalling speed) is exceeded.

In working principle of this jet engines, a lot of oxygen is supplied in a cylindrical turbine by sucking air from the front with high speed and after that this sucked air is delivered towards the other end of the turbine. In between in the path kerosene or jet fuel is sprinkled or showered heavily by using hydraulic pump with pressure. This said air is sucked from the atmosphere of the earth. This air comes from the front side of the engine which can be called as the nose of the cylinder. This air is then pushed through the turbine to the other end which the rear end of the cylinder.

By action of turbines when this air is pushed in from the nose of the cylinder it provides more and more oxygen resulting into heavy expansion of the burning gases. In general formulation the more air provides more oxygen and this more oxygen implies more efficient burning of fuel which results more heat is produced in the engine that provides more power and thrust to give motion. This results into extremely hot gases rushing out forcefully from the other end of the turbine giving thrust to the cylinder body as a 'reaction vector'.

In standard conditions jet airplanes are normally operated at high altitudes where cruise speed is dictated equivalent to the revolutions per minute (rpm) or Exhaust Gas Temperature (EGT) limits. Jet engines are more efficient at higher altitudes because the cold and less dense air at this altitude efficiently maximizes fuel bum.

The primary reason for operating jet engines in the high-altitude environment is because it is most efficient in that environment. At this position the thermal efficiency cycle of a jet engine is very high and can be determined by the temperatures of the incoming air and the outgoing air. The lower the temperature of the incoming air, the higher the efficiency. Normally, air at a high altitude has a lower density and lower temperature. The cold air at this altitude improves the thermal efficiency of the engine because less work is required to compress the incoming air as the volume of cold air is comparatively lower than the volume of the hot air. In high altitudes the incoming air towards the engine is also less dense due to which it enters at a faster rate into the compressor and it is led into the combustion chamber where it is mixed with fuel. In the combustion chamber, the fuel-air mixture bums at nearly constant pressure and in a restricted volume, causing the compressed gas to expand. The density of the air decreases as it is heated up because it is subjected to constant pressure. The density ratio between the burnt gas in the combustion chamber and the unbumt gas at the intake is proportional to its temperature ratio, measured in absolute temperature. Thermal efficiency increases with the lower temperature of the intake air and an increased difference between ambient (atmospheric) temperature and temperature of the engine gases.

In fact, the gravitational force acting on the plane becomes so less that at the high- altitude level of above the earth many thousand feet the mass remains same but its weight becomes less. The weight starts decreasing as it goes higher, the gravitational force starts decreasing as it goes higher and higher means in this scenario higher force 'g' starts reducing and the retardation decreases by square root as it is opposite of acceleration which increases in multiplication of force 'g'. Therefore, it requires very less energy on force to go to further heights and to be in space. However, it fails on account of lack of oxygen. At this level these regular jet engines stops working. As the jet engine flies at a higher altitude the atmospheric air starts getting thinner and thinner, resulting into lack of oxygen required for burning the fuel. In fact, because of continuous falling of the gravitation and in retardation it required very less energy to go to further heights. But since there is lack of oxygen at that level the fuel stops burning and then regular jet engine stops working and due to which airplane cannot fly further at higher level. The present invention has been made in consideration of the above-described problems, and it is an object of the present invention to provide internal combustion jet engine, which is simple in structure and fuel efficient over the conventional jet engines. Due to specific design and internal structure of the engine, it produces high amount of exhaust gases by consuming less fuel. It provides mechanically controlled fuel injection conical valve system which can perform stable fuel injection while securing overall operation performance. Henceforth, for solving the abovementioned problems, the internal combustion jet engine is provided.

OBJECT OF THE INVENTION

The objective of the invention is to provide an internal combustion engine which can be used for any type of fluid systems which can work on high pressure or ultrahigh pressure with more efficient manner.

Another object of the invention is to provide an internal combustion engine wherein fuel injection device with conical valve system is used to control the flow of fuel. Due to which speed and power of the engine can be controlled.

Yet another object of the invention is to provide an internal combustion engine which can operate in efficient manner for any type of fuel system.

Yet another object of the invention is to provide an internal combustion engine which is more reliable over a conventional jet engine.

Yet another object of the invention is to provide an internal combustion engine which can become an alternative option for regular jet engine

SUMMARY OF THE INVENTION

Accordingly, the present invention provides internal combustion engine for jet engine. The disclosed system comprises cylindrical housing, top flange, bottom flange, converging and diverging combustion chamber, plurality of nozzles, piping network, plurality of conical valves, first storage tank for storing pure liquid oxygen, second storage tank for storing gaseous fuel, third storage tank for storing liquid fuel, plurality of control valve for controlling the flow of fuel into the combustion chamber.

The source of pure liquid oxygen which is referred as Fl is connected to the converging and diverging combustion chamber by using oxygen supply pipeline. The flow of pure liquid oxygen is supplied into converging and conversion combustion chamber by using oxygen supply pipe line. One end of oxygen supply line is connected to the source of pure liquid oxygen tank and other end of the oxygen fuel supply line is connected to the converging and diverging combustion chamber. The converging and diverging combustion chamber is connected to the cylinder housing. In cylinder housing the top flange and bottom flange are arranged wherein plurality of nozzles are arranged on the flat surface of the top flange and bottom flange. The provided nozzles are directly connected to the oxygen supply pipeline in the direction towards the convergent and divergent combustion chamber. To control the appropriate flow of pure liquid oxygen into the converging and diverging chamber there is a liquid oxygen flow control valve is provided on oxygen fuel supply line. The liquid oxygen flow adjustment control valve regulates and control the flow of pure liquid oxygen supply entering in to the converging and diverging combustion chamber. To obtain a high pressure with a zero-leakage flow of pure liquid oxygen there is a conical piston valve is provided in oxygen fuel supply line. The controlled flow of pure liquid oxygen is entering into the conical piston valve from one side and at the other side of a conical piston valve pressurised flow of pure liquid oxygen is obtained which is discharged into the converging and diverging combustion chamber through cylinder housing wherein top flange and bottom flange are mounted for supporting the plurality of the nozzles. In converging and diverging combustion chamber the high pressurised pure liquid oxygen supplied through the nozzle for the combustion which helps to bum the fuel for clean combustion and provide high amount of exhaust gases to thrust the jet engine. The source of gaseous fuel which is referred as F2 is connected to the converging and diverging combustion chamber by using gaseous fuel supply pipeline. The flow of gaseous fuel is supplied into converging and diverging combustion chamber by using gaseous fuel supply line. One end of gaseous fuel supply line is connected to the storage tank of gaseous fuel and other end of the gaseous supply line is connected to the converging and diverging combustion chamber. The converging and diverging combustion chamber is connected to the cylinder housing. In cylinder housing the top flange and bottom flange are arranged wherein plurality of nozzles are arranged on the flat surface of the top flange and bottom flange. The provided nozzles are directly connected to the gaseous fuel supply pipeline in the direction towards the convergent and divergent combustion chamber. To control the appropriate flow of gaseous fuel into the converging and diverging chamber there is a gaseous flow control valve is provided on gaseous fuel supply line. The gaseous flow control valve regulates and control the flow of gaseous fuel supply entering in to the converging and diverging combustion chamber. To obtain a high pressure with a zero-leakage flow of gaseous fuel there is a conical piston valve is provided in gaseous fuel supply line. The controlled flow of gaseous fuel is entering into the conical piston valve from one side and at the other side of a conical piston valve pressurised flow of gaseous fuel is obtained which is discharged into the converging and diverging combustion chamber through cylinder housing wherein top flange and bottom flange are mounted for supporting the plurality of the nozzles. In converging and diverging combustion chamber the high pressurised gaseous fuel supplied through the nozzle for the combustion. The atomised gaseous flow of fuel helps to bum the fuel for completely in combustion chamber and provide high amount of exhaust gases to thrust the jet engine.

The source of liquid fuel which is referred as F3 is connected to the converging and diverging combustion chamber by using liquid fuel supply pipeline. The flow of liquid fuel is supplied into converging and conversion combustion chamber by using liquid fuel supply line. One end of liquid fuel supply line is connected to the storage tank of liquid fuel and other end of the liquid fuel supply line is connected to the converging and diverging combustion chamber. The converging and diverging combustion chamber is connected to the cylinder housing. In cylinder housing the top flange and bottom flange are arranged wherein plurality of nozzles are arranged in this top flange and bottom flange. The provided nozzles are directly connected to the gaseous fuel supply pipeline. To control the appropriate flow of gaseous fuel into the converging and diverging chamber there is a flow control valve is provided on gaseous fuel supply line. The gaseous flow adjustment control valve regulates and control the flow of gaseous fuel supply entering in to the converging and diverging combustion chamber. To obtain a high pressure with a zero-leakage flow of gaseous fuel there is a conical piston valve is provided in gaseous fuel supply line. The controlled flow of gaseous fuel is entering into the conical piston valve from one side and at the other side of a conical piston valve pressurised flow of gaseous fuel is obtained which is discharged into the converging and diverging combustion chamber through cylinder housing wherein top flange and bottom flange are mounted for supporting the plurality of the nozzles. In converging and diverging combustion chamber the high pressurised liquid fuel supplied through the nozzle for the combustion. The atomised liquid flow of fuel helps to bum the fuel for completely in combustion chamber and provide high amount of exhaust gases to thrust the jet engine.

In an operating state of internal combustion jet engine, the pure liquid oxygen, gaseous fuel and liquid fuel which is stored in separate storage units or containers. The flow of the pure liquid oxygen, gaseous fuel and liquid fuel is controlled by sperate control valves and conical piston valves which are mounted over a separated fuel and oxygen supply line. The supply of gaseous and liquid fuel with pure liquid oxygen is entered into converging and diverging combustion chamber through cylinder housing. In cylinder housing top flange and bottom flange are arranged wherein plurality of nozzles are mounted over a flat surface of the flange. The provided nozzles are directly connected to the supply lines which supplies fuel and oxygen into the convergent and divergent combustion chamber. In an enclosed convergent and divergent combustion chamber when these fuels are fused with the electric spark in the presence of cryogenic oxygen there is huge amount of exhaust gases are created with high temperature. Due to high temperature of gases, it is creating tremendous pressure on the exhaust resulting into the thrust provided by the engine. The clean burning of fuel gets converted into gases causing combustion in an enclosed area which creates tremendous pressure inside the chamber. These hot gases rush out through the jet hole of the system and provide thrust for the movement of aeroplane.

BRIEF DESCRIPTION OF THE DRAWINGS

The embodiments can be better understood with reference to the following drawings and description. The components in the figures are not necessarily to scale, the emphasis instead being placed upon illustrating the principles of the embodiments. Moreover, the figures, like reference numerals designate corresponding parts throughout the different views.

Reference will be made to embodiments of the invention, examples of which may be illustrated in the accompanying figures. These figures are intended to be illustrative, not limiting. Although the invention is generally described in the context of these embodiments, it should be understood that it is not intended to limit the scope of the invention to these particular embodiments.

The above and other objects, features, and advantages of the present invention will be more clearly understood from the following detailed description taken in conjunction with the accompanying drawings, in which:

Figure 1 illustrates constructional arrangement of the of internal combustion of jet engine according to an exemplary implementation of one of the embodiments of the present invention.

DETAILED DESCRIPTION OF THE INVENTION The present invention is an internal combustion engine which is a completely mechanical system consisting of a mechanical assembly constituting operative mechanism and pathways for passage of exhaust gases which are produced by combustion of mixture of fuels. The combustion of fuel is produced in presence of additional oxygen which is supplied by the separate nozzle and delivery systems. Due to high temperature of gases, it is creating tremendous pressure on the exhaust resulting into the thrust of the body as a reaction. The burning of fuel gets converted into gases causing combustion in an enclosed area which creates tremendous pressure inside the converging and diverging combustion chamber. In this engine specially designed conical valves are used to control the flow of fuels as results by using this valve system it is easy to control the speed and power of the engine. This engine having various mechanical components constituting the different elements which are actuating and controlling the components of the engine. Thus, internal combustion engine can perform their associative function for executing the method steps thereof of the system for accommodating varied size and specification of its components for producing thrust which is used for the movement of the aeroplanes.

In the following description of this application, it should be noted that the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate the orientation of the device. The positional relationship is based on the position or positional relationship shown in the drawings, or the position or positional relationship that the product of this application is usually placed in use, only for the convenience of describing the application and simplifying the description and does not indicate or imply the device referred to the element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the application. In addition, the terms "first", "second", "third", etc. are only used for distinguishing description, and cannot be understood as indicating or implying relative importance. In the description of this application, unless otherwise specified, "plurality" means two or more. In the following description of this application, it should also be noted that, unless otherwise clearly defined and limited, the terms "set" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection, or integrally connected; it can be a mechanical connection or an electrical connection. For those of ordinary skill in the art, the specific meanings of the above-mentioned terms in this application can be understood under specific circumstances.

In the following description, for the purpose of explanation, specific details are set forth in order to provide an understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these details. One skilled in the art will recognize that embodiments of the present invention, some of which are described below, may be incorporated into a number of systems.

The various embodiments of the present invention provide a system of conical valve which are comes under the precision flow system of the any fluid. The disclosed conical valve system is designed to use in the fuel injection system for pressurized fuels of various engine systems. The disclosed conical valve system is inexpensive, robust, and simple in operation and can control or monitor fluid flow without leakage.

Furthermore, connections between components within the figures are not intended to be limited to direct connections. Rather, these components may be modified, re-formatted or otherwise changed by intermediary components.

The systems/devices described herein are explained using examples with specific details for better understanding. However, the disclosed embodiments can be worked on by a person skilled in the art without the use of these specific details.

Throughout this application, with respect to all reasonable derivatives of such terms, and unless otherwise specified (and/or unless the particular context clearly dictates otherwise), each usage of: “a” or “an” is meant to read as “at least one.”

“the” is meant to be read as “the at least one.”

References in the present invention to “one embodiment” or “an embodiment” mean that a particular feature, structure, characteristic, or function described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase “in one embodiment” in various places in the specification are not necessarily all referring to the same embodiment.

Embodiments of the present invention include various steps, which will be described below. The steps may be performed by mechanical components or may be embodied in machine operated instructions, which may be used to cause a general-purpose with the instructions to perform the steps. Alternatively, steps may be performed by a combination of various elements of the system and/or by human operators and the method steps of the invention could be accomplished by mechanical systems of device or subparts of it.

If the specification states a component or feature "may¹ can", "could", or "might" be included or have a characteristic, that particular component or feature is not required to be included or have the characteristic.

As used in the description herein and throughout the claims that follow, the meaning of "a, an," and "the" includes plural reference unless the context clearly dictates otherwise. Also, as used in the description herein, the meaning of "in" includes "in" and "on" unless the context clearly dictates otherwise.

Exemplary embodiments will now be described more fully hereinafter with reference to the accompanying drawings, in which exemplary embodiments are shown. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. These embodiments are provided so that this invention will be thorough and complete and will fully convey the scope of the invention to those of ordinary skill in the art. Moreover, all statements herein reciting embodiments of the invention, as well as specific examples thereof are intended to encompass both structural and functional equivalents thereof. Additionally, it is intended that such equivalents include both currently known equivalents as well as equivalents developed in the future (i.e., any elements developed that perform the same function, regardless of structure).

Hereinafter, embodiments will be described in detail. For clarity of the description, known constructions and functions will be omitted. Parts of the description may be presented in terms of operations performed by a mechanical system, using terms such as shaft, spring and the like, consistent with the manner commonly employed by those skilled in the art to convey the substance of their work to others skilled in the art.

While embodiments of the present invention have been illustrated and described, it will be clear that the invention is not limited to these embodiments only. Numerous modifications, changes, variations, substitutions, and equivalents will be apparent to those skilled in the art, without departing from the spirit and scope of the invention, as described in the claim.

The disclosed utility model is configured with different components, consists of one cylindrical chamber as housing. This housing is purposefully fabricated in better shape so that it can achieve more better results in combustion efficiency of the engine. At one end of it is provided with venturi so that it is on the facing with convergent and divergent angles on the chambers which acts as a jet hole of the engine.

In an embodiment of the construction of this engine the other side of the cylindrical housing there is an internal threading is provided on the internal diameter of it where there is place provided for fitting a set of two threaded flanges to fix with each other. There are two flanges are provided in which one flange is considered as a top flange and other one flange is considered as a bottom flange. These two flanges are provided in circular shape and the size of both the flanges are identical in nature so that it can connect with each other. Refereeing to Fig 1. In an embodiment of the construction of this engine the top flange is provided with threaded pattern on its periphery so that in cylindrical housing the it can fix with the internal diameter of the cylindrical chamber of housing. On the flat surface of the flange there are number of connecting joints are provided in between the path which are called 'connectors 'and they are connected to the fuel injection system.

There are number of nipples provided on the flat surface of the flange with suitable nozzles which are selected according to the type of fuel. These nozzles are placed throughout the plate and fixed on the surface as shown in the figure.

In top flange and bottom flange there are two half round circular grooves are provided which are facing to each other and purposefully made a shape of grooves as shown in the figure. In both the flange at the centre there is a cup like arrangement is provided which form pocket like structure as it is look like a bathroom shower which as shown in the figure. There are throughout number of holes provided from the other side which is open to the other side and positioned inside the groove and pocket at the centre as shown in the figure. Then fuel pipe connectors are fitted on the facing of it. This is an entry passage for fuel passing the bottom flange

In an embodiment of the assembly of this engine different components or part of the engine are assembled together with threaded or welded or by using press fit techniques. In an assembly of the engine firstly bottom flange is fitted inside the chamber housing on internal threading in such a way that extended the nozzles side goes inside the chamber and the grooved side facing remains on the top side of the flange facing outward direction which as shown in the figure. The threads which are provided on periphery of the flange are fitted with internal threads of the housing to form a fixed joint. In next step the top flange is fitted and fixed on the top of the bottom flange in such a way that the facing grooves on both flanges comes into the contact to each other and form a hollow pipe structure which at one end gets connected to the fuel entry path and other side gets opened inside the chamber. In further step different fuel entry points or connecting joints which are also known as connectors are connected to the fuel injection system which is consist of conical slice valve accelerator which is as shown in the figure. Furthermore, there are different inlet fuel pipes are provided which are connected to the of the injection system. The entry point or connector of the 'injection system' is connected to the pressurized fuel tanks as cryogenic liquid fuels like oxygen, hydrogen etc which are always stored in tank with under pressurized conditions.

In an embodiment of the working principle of this engine the liquid fuels like petrol, kerosene, alcohol etc. are injected with pressure by hydraulic pump.

The pathway between pressurized tank to a 'fuel injection system' is kept naturally under pressure. There is a pressure adjusting valve connected to the gas cylinder Where required predetermined pressure is adjusted once in for all. If required there could be different pressure required for different fuels and their mixture combinations according to which it can be adjusted according to requirement. By using fuel injection system these highly inflammable fuels are sprinkled or showered in an 'enclosed chamber' which has only one venturi as an exhaust with abundant of oxygen when given an electric spark, fuel starts burning vigorously in a fashion of combustion. Due to sudden expansion of fuel by multiple times it produces high volume exhaust gases because of heat. Therefore, while accelerating high amount of ratio of the mixtures of fuel and oxygen is maintained continuously in the converging and diverging combustion chamber and feeding the fuels and oxygen is controlled by using conical valves. Therefore, it is easy to control the feeding of fuels in critical manner so that the control and the speed of the engine can be achieved like throttling of internal combustion engine.

In this engine there are three entry holes are provided with three joints which are connected with different fuel pipes from where the fuels are injected with pressure inside the grooves formed between flanges. These grooves have opening holes across the facing of the flange where nipples with suitable nozzles are fitted on threading which is shown in the figure. When there are different fuels under pressure are fire through this injection system, through these entry hole pipes, they open to the other side of the bottom flange inside the enclosed chamber which is shown in the figure. This chamber has only one outlet as exhaust in a form which has convergent and divergent angles for the holes which is shown in the figure.

In this system there are three fuels. There is Fuel no. 1- that is Flwhich is nothing but the oxygen which helps to bum the hydrocarbons. There is another Fuel no 2- that is F2 which is nothing but a gaseous fuel like LPG or CNG gas which is stored in the cylinder. Then there is another fuel which is fuel no 3 that is F3. It is liquid fuel which is kerosene or petrol. In an enclosed chamber when these fuels are fused with the electric spark in the presence of cryogenic oxygen then huge amount of exhaust gases are created with high temperature. Due to high temperature of gases, it is creating tremendous pressure on the exhaust resulting into the thrust of the body as a reaction. The burning of fuel gets converted into gases causing combustion in an enclosed area which creates tremendous pressure inside the chamber. These hot gases rush out through the jet hole of the system and provide thrust for the movement of aeroplane. In this engine specially designed conical valves are used to control the flow of fuels as results by using this valve system it is easy to control the speed and power of the engine. Therefore, when there is huge amount of power is required then this can be beneficial over the conventional system.

Working example

When an airplane goes higher and higher the gravitational force starts reducing and it reduces so much at one level of height the gravitational force becomes zero. At this level if this disclosed internal combustion jet engines can be used as spare or extra engine on wings of regular jet planes. When regular jet planes attain a certain height then regular engine stops it working due to some unavoidable reasons then these disclosed engines can work without failure because in this disclosed engine there is a provision of an inbuilt oxygen supply for combustion of the engine which requires requires very less amount of fuel to reach further heights within few minutes therefore it can reach to zero gravitation limit in less amount of fuel than normal jet engine. Henceforth, it can save a lot of fuel.

Advantages of the invention

1. The disclosed engine provides a multifuel fuel ignition system which can be operable in a high pressure or ultrahigh pressure. By using this system user can achieve excellent thermal and fuel efficiency and reduce the working cost of the aero plane.

2. The disclosed engine having a Low maintenance

3. This disclosed engine can be beneficial for multiple application.

4. This disclosed engine can be operated in efficient manner for any type of fuel system.

5. The disclosed engine is more reliable than any other regular jet engine.

6. The disclosed engine can become an alternative for regular jet engine.

From the above description, it can be seen that device of the present invention is to provide an internal combustion jet engine for an aeroplane which can be used as spare or extra engine on wings of regular jet planes. When regular jet planes attain a certain height then regular engine stops then this engine can work at this situation without a failure. According to present invention the disclosed engine can be used for any fuel. This internal combustion jet engine is simple in structure and more fuel efficient over a regular jet engine.

The foregoing descriptions of specific embodiments of the present invention have been presented for purposes of illustration and description. They are not intended to be exhaustive or to limit the present invention to the precise forms disclosed, and obviously many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the present invention and its practical application, to thereby enable others skilled in the art to best utilize the present invention and various embodiments with various modifications as are suited to the particular use contemplated. It is understood that various omission and substitutions of equivalents are contemplated as circumstance may suggest or render expedient, but such are intended to cover the application or implementation without departing from the scope of the present invention.

Further, while one or more operations have been described as being performed by or otherwise related to certain components, devices or entities, the operations may be performed by or otherwise related to any component, device or entity.

Further, the operations need not be performed in the disclosed order, although in some examples, an order may be preferred. Also, not all functions need to be performed to achieve the desired advantages of the disclosed device, therefore it’s all functions are not required.

While select examples of the disclosed device have been described, alterations and permutations of these examples will be apparent to those of ordinary skill in the art. Other changes, substitutions, and alterations are also possible without departing from the disclosed device in its broader aspects.

Claims

I Claim

1. An internal combustion engine for jet engine (1000) comprising a converging and diverging combustion chamber (10), a cylindrical housing (20), a top flange(30), a bottom flange (40), plurality of nozzles, piping network includes oxygen supply line(210) gaseous fuel supply pipeline (220) , liquid fuel supply line (230), plurality of conical piston valves (50,60,70), first storage tank(HO) for storing pure liquid oxygen, second storage tank (120) for storing gaseous fuel, third storage tank (130) for storing liquid fuel, plurality of control valve (80, 90,100) for controlling the flow of fuel into the combustion chamber wherein the first storage tank of pure liquid oxygen (110) operably connected to the converging and diverging combustion chamber (10) with pure oxygen supply pipeline (210); the second storage tank of gaseous fuel (120) operably connected to the converging and diverging combustion chamber (10) with gaseous fuel supply pipeline (220); the third storage tank of liquid fuel (130) operably connected to the converging and diverging combustion chamber (10) with liquid fuel supply pipeline (230); wherein one end of pure oxygen supply line (210) connected to the storage tank (110) of pure liquid oxygen (110) and other end of the oxygen supply line (210) connected to the converging and diverging combustion chamber (10) through the control valve (80) and conical valve (50) for controlling the flow of pure liquid oxygen into the converging and diverging combustion chamber (10); one end of gaseous fuel supply line (220) connected to the storage tank (120) of gaseous fuel and other end of the gaseous fuel supply line (210) connected to the converging and diverging combustion chamber (10) through the control valve (90) and conical piston valve (60) for controlling the flow of gaseous fuel supply into the converging and diverging combustion chamber(lO); one end of liquid fuel supply line (230) connected to the storage tank (130) of liquid fuel and other end of the liquid fuel supply line (230) connected to the converging and diverging combustion chamber (10) through the control valve (100) and conical piston valve (70) for controlling the flow of liquid fuel supply into converging and diverging combustion chamber (10); a cylindrical housing (20) includes a top flange (30) and bottom flange (40) wherein plurality of nozzles arranged on flat surface of the top flange (30) and bottom flange (40) towards the direction of converging and diverging combustion chamber (10); wherein one end of cylindrical housing (20) connected to the one end of converging and diverging combustion chamber (10) and another end connected to pure oxygen supply line (210), gaseous fuel supply line (220), liquid fuel supply line (230) respectively attached to plurality of nozzles; thereby facilitating high pressurised supply of fuel through plurality of nozzles with a spark completely burned combustion chamber (10) and provide high amount of exhaust gases to thrust the jet engine.

2. The internal combustion jet engine of claim 1, wherein said top flange (30) and bottom flange (40) flanges adapted to expand under the action of the centrifugal force.

3) The internal combustion jet engine of claim 1, wherein said multiple nozzles are arranged diametrically opposite tangentially of the combustion chamber (10), each nozzle being provided with a calibrated conical valve (80,90,100) to permit the passage of the fuel only when a predetermined fuel pressure has been reached.