KR102617459B1 - Jet engine using exhaust gas - Google Patents

Abstract

An injection propulsion engine using discharged exhaust is disclosed. An injection propulsion engine using exhaust discharge according to an embodiment of the present invention includes a body; A combustion chamber installed within the body and injecting fuel into compressed air for combustion; A guide member that guides exhaust gas discharged from the combustion chamber in a preset direction; and a propulsion providing means that provides propulsion by hitting exhaust gas guided from the guide member, and one propulsion providing means is provided at the rear of the guide member.

Description

Injection propulsion engine using discharge exhaust {JET ENGINE USING EXHAUST GAS}

The present invention relates to an injection propulsion engine using exhaust exhaust. More specifically, although the specific operation method and operating form are somewhat different in injection propulsion engines such as turbojets, turbofans, and ramjets, they are common in propulsion by injection and achieve supersonic speeds. It relates to an injection propulsion engine using exhaust gases that can obtain high thrust even at supersonic speeds by rotating the fan blades or hitting fixed blades with the exhaust gases injected into the engine.

In general, an injection propulsion engine refers to a heat engine that obtains propulsion from the recoil force by ejecting high-temperature exhaust gas combusted inside the engine through a jet nozzle. These injection propulsion engines are commonly called jet engines. Jet engines are mostly used as prime movers for aircraft and are roughly classified into four types depending on their structure and function.

First, a turbojet compresses air sucked from the atmosphere with an axial or centrifugal compressor, sends this compressed air into a combustion chamber, injects fuel to combust it, and then creates high-temperature, high-pressure combustion gas that is used to drive a turbine. It is sprayed into the stage to drive the turbine stage. In this way, a self-driving propulsion engine is formed, and the exhaust gas that has passed through the turbine stage is ejected to the outside through a nozzle to create propulsion.

This organization accepts a large amount of air to increase the durability of the turbine material. Naturally, residual oxygen remains in the combustion gas, so installing a long tail pipe and injecting secondary fuel into it causes an after-burning effect, resulting in simple combustion. There are also ways to obtain additional thrust. However, this method consumes a lot of fuel and is noisy, so it is not used except for supersonic military aircraft.

Next, there is a turboprop, which has a structure in which a large propeller is mounted on a turbojet. This turboprop is similar to a turbojet, but most of the combustion gas energy is used to drive the propeller, and the exhaust gas energy is released as is, so no separate thrust is obtained.

Next, there is a turbo fan, which is a structure in which a fan is mounted on a turbojet. A turbofan is similar to a turbojet, but it converts most of the combustion gas into the driving force of the fan and uses both the thrust from the fan and the jet thrust from the core engine. Its performance is somewhere between that of a turboprop and a turbojet, and it is used as an engine for medium-sized passenger and transport aircraft that do not require high-speed flight.

Another type of injection propulsion engine is the Ram Jet. When the flight speed increases, the atmospheric air relatively flowing into the engine is compressed by the forward force of the engine, which is called the ram effect. A ramjet sends the compressed air obtained through this ram effect into the combustion chamber and injects fuel to explode. Next, it is ejected through the nozzle and thrust is obtained from the recoil force.

The currently known ramjet only has an empty space-shaped compression chamber and combustion chamber injection nozzle, and does not have a rotating body such as a turbine or compressor. This engine has a simple structure and its performance improves at higher speeds, so it is used as a prime mover for supersonic passenger aircraft or missiles that are 2 to 4 times the speed of sound. However, ramjets have the disadvantage of requiring external help when starting and consuming a lot of fuel.

Republic of Korea Patent Publication No.: 10-2003-0009113 (Publication Date: January 29, 2003)

Therefore, the technical problem to be achieved by the present invention is to minimize losses that may occur when the fan blade rotates, reduce resistance due to air friction, and increase engine efficiency by using exhaust exhaust that can save fuel and improve speed. It provides an injection propulsion engine.

According to one aspect of the invention, a body; a combustion chamber installed within the body and injecting fuel into compressed air for combustion; A guide member that guides the exhaust gas discharged from the combustion chamber in a preset direction; and a propulsion providing means for providing propulsion by hitting exhaust gas guided from the guide member, wherein one propulsion providing means is provided at the rear of the guide member. An injection propulsion engine using discharged exhaust is provided. It can be.

In addition, the propulsion providing means includes: a rotating shaft; And it may include a fan blade that is coupled to the rotation shaft and rotates.

In addition, the guide member is curved toward the side of the body so that the exhaust gas is directed toward the side of the body, and the fan blade is formed so that the exhaust gas guided by the guide member hits the fan blade. A bend may be formed in a direction opposite to the bend of the guide member so that it faces the rear of the body.

Additionally, the fan blade may be formed parallel to the rotation axis toward the rear of the body.

Additionally, the fan blade may be formed to increase in width toward the rear of the body.

In addition, it may further include a counterweight coupled to the rotation shaft and rotating at a position opposite the fan blade.

And, the propulsion providing means includes an inner cylinder installed inside the body; And it may include a fixing collar fixed to the inner tube.

In addition, the guide member is curved toward the side of the body so that the exhaust gas is directed toward the side of the body, and the fixed blade is formed when the exhaust gas guided by the guide member hits the fixed blade. A bend may be formed in a direction opposite to the bend of the guide member so that it faces the rear of the body.

Additionally, the fixing feathers may be formed parallel to the inner tube toward the rear of the body.

Additionally, the fixed collar may be formed to increase in width toward the rear of the body.

In addition, it may further include a turbine stage disposed behind the combustion chamber and rotating.

In addition, the turbine stage includes a high-pressure turbine stage rotated by exhaust gas discharged from the combustion chamber; and a low-pressure turbine stage that is rotated by exhaust gas passing through the high-pressure turbine stage and is coupled to the rotation shaft.

In addition, it may further include a compressor disposed in front of the combustion chamber to forcibly compress atmospheric air supplied to the combustion chamber.

In addition, it may further include a compression chamber that naturally compresses the air flowing into the body by the forward force of the body.

And, it may include a speed increaser provided on the guide member.

Additionally, it may include a cover surrounding the speedometer.

Accordingly, embodiments of the present invention have the effect of minimizing losses that may occur when the fan blade rotates, reducing resistance due to air friction, and increasing engine efficiency, enabling fuel savings and speed improvement.

The following drawings attached to this specification illustrate preferred embodiments of the present invention, and serve to further understand the technical idea of the present invention together with the detailed description of the invention described later. Therefore, the present invention includes the matters described in such drawings. It should not be interpreted as limited to only .
Figure 1(a) is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the first embodiment of the present invention, and Figure 1(b) shows the turbine stage, guide member, fan blade, and counterweight in Figure 1(a). This is a drawing schematically showing.
Figure 2(a) is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the second embodiment of the present invention, and Figure 2(b) shows the turbine stage, guide member, fan blade, and counterweight in Figure 2(a). This is a drawing schematically showing.
Figure 3(a) is a cross-sectional view of an injection propulsion engine using discharge exhaust according to a third embodiment of the present invention, and Figure 3(b) schematically shows the turbine stage, guide member, and fixed blade in Figure 3(a). This is a drawing.
Figure 4(a) is a cross-sectional view of an injection propulsion engine using discharge exhaust according to a fourth embodiment of the present invention, and Figure 4(b) is a diagram schematically showing the guide member and the fixed blade in Figure 4(a). am.
Figure 5 is a diagram showing the fan blades and balance weights provided in Figures 1 and 2 installed.
Figure 6 is a view showing the fixing blade provided in Figures 3 and 4 installed on the inner cylinder.
Figure 7(a) is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the fifth embodiment of the present invention, and Figure 7(b) shows the turbine stage, guide member, gearbox, and fan blade in Figure 7(a). Wow, this is a diagram schematically showing the balance weight.
Figure 8(a) is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the sixth embodiment of the present invention, and Figure 8(b) shows the turbine stage, guide member, gearbox, and fan blade in Figure 8(a). Wow, this is a diagram schematically showing the balance weight.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. Terms or words used in this specification and claims should not be construed as limited to their common or dictionary meanings, and the inventor may appropriately define the concept of terms in order to explain his or her invention in the best way. It must be interpreted with meaning and concept consistent with the technical idea of the present invention based on the principle that it is. Therefore, the embodiments described in this specification and the configurations shown in the drawings are only one of the most preferred embodiments of the present invention and do not represent the entire technical idea of the present invention, so at the time of filing the present application, various alternatives may be used to replace them. It should be understood that equivalents and variations may exist.

In the drawings, the size of each component or specific part constituting the component is exaggerated, omitted, or schematically shown for convenience and clarity of explanation. Therefore, the size of each component does not entirely reflect the actual size. If it is determined that specific descriptions of related known functions or configurations may unnecessarily obscure the gist of the present invention, such descriptions will be omitted.

The term 'coupling' or 'connection' used in this specification refers not only to the case where one member and another member are directly coupled or directly connected, but also when one member is indirectly coupled to another member through a joint member, or indirectly connected to another member. Also includes cases where it is connected to .

The present invention was created to solve the problems and shortcomings described above, and includes an embodiment in which a fan blade obtains thrust through rotation in lateral exhaust gas injected at supersonic speed, and a lateral exhaust gas injected at supersonic speed. The purpose is to provide an injection propulsion engine using another embodiment of the discharge exhaust, which obtains thrust by installing fixed blades like the sail of a sailboat in the gas.

An injection propulsion engine, commonly called a jet engine, refers to a heat engine that ejects high-temperature, high-pressure exhaust gas combusted inside the engine from a jet nozzle and uses the recoil force as a driving force. The principles and features of the present invention described below are the turbo engine. It should be understood that it can be applied to various heat engines such as jets, turbofans, and ramjets.

Figure 1(a) is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the first embodiment of the present invention, and Figure 1(b) shows the turbine stage, guide member, fan blade, and counterweight in Figure 1(a). is a diagram schematically showing, and Figure 2(a) is a cross-sectional view of an injection propulsion engine using discharge exhaust according to the second embodiment of the present invention, and Figure 2(b) is a turbine stage and a guide in Figure 2(a). It is a drawing schematically showing a member, a fan blade, and a counterweight. FIG. 3(a) is a cross-sectional view of an injection propulsion engine using discharge exhaust according to a third embodiment of the present invention, and FIG. 3(b) is a view of FIG. (a) is a diagram schematically showing the turbine stage, the guide member, and the fixed blade, and Figure 4(a) is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the fourth embodiment of the present invention, and Figure 4(a) is a schematic diagram showing the turbine stage, guide member, and fixed blade. b) is a diagram schematically showing the guide member and the fixed blade in Figure 4(a), Figure 5 is a diagram showing the fan blades and counterweights provided in Figures 1 and 2 installed, and Figure 6 is a diagram showing the fan blades and counterweights provided in Figures 1 and 2 It is a view showing the fixed blade provided in Figures 3 and 4 installed in the inner cylinder, Figure 7(a) is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the fifth embodiment of the present invention, and Figure 7 ( b) is a diagram schematically showing the turbine stage, guide member, gearbox, fan blade, and counterweight in Figure 7(a), and Figure 8(a) shows the discharge exhaust according to the sixth embodiment of the present invention. It is a cross-sectional view of the injection propulsion engine used, and FIG. 8(b) is a diagram schematically showing the turbine stage, guide member, gearbox, fan blade, and counterweight in FIG. 8(a).

The injection propulsion engine 10 using discharged exhaust according to an embodiment of the present invention provides injection propulsion that can maximize engine efficiency through a propulsion providing means 400 equipped with a fan blade 420 or a fixed blade 460. Regarding the engine 10, hereinafter, the injection propulsion engine 10 using the exhaust exhaust according to an embodiment of the present invention will first be described, and the injection propulsion engine 10 using the exhaust exhaust according to an embodiment of the present invention ( 10) Describes each embodiment of the form combined with the existing engine.

Referring to the drawings, the injection propulsion engine 10 using discharged exhaust according to an embodiment of the present invention includes a body 100, a combustion chamber 200, a guide member 300, and a propulsion providing means 400. Includes.

The body 100 is protected by installing a combustion chamber 200, a guide member 300, and a propulsion providing means 400. The shape of the body 100 can be modified into various forms depending on the type of engine and required parts, and is approximately cylindrical, with external atmosphere flowing in through the front and exhaust gas being discharged from the rear. However, the shape of the body 100 is not limited to this.

The body 100 may include a casing 110 and an outer frame 130. A propulsion providing means 400, which will be described later, may be installed on the casing 110, and the outer frame 130 may include the casing 110. Can be connected to the rear of.

The combustion chamber 200 is installed within the body 100. The combustion chamber 200 provides a space for combustion by mixing fuel with compressed air. Additionally, the air and fuel burned in the combustion chamber 200 are ejected toward the rear as high-temperature, high-pressure exhaust gas.

The guide member 300 is provided to guide the exhaust gas discharged from the combustion chamber 200 in a preset direction. Referring to FIGS. 1 to 4 , the guide member 300 may be provided with a curve 310 formed toward the side of the body 100 so that exhaust gas is directed toward the side of the body 100 .

The propulsion providing means 400 is provided to provide propulsion by hitting the exhaust gas (see G in FIGS. 1 to 4) guided from the guide member 300. Here, referring to FIGS. 1 to 4, one propulsion providing means 400 may be provided at the rear of the guide member 300.

The propulsion providing means 400 may vary, and may include rotating fan blades 420 (see FIGS. 1 and 2) in one embodiment, and fixed blades 460 (FIG. 3) in another embodiment. and (see FIG. 4). Here, the basic shape of the fan blade 420 and the fixed blade 460 may be common, but is not limited thereto. The fan blade 420 is coupled to the rotation shaft 410 and rotates, but the difference is that the fixed blade 460 is coupled to the inner cylinder 450 and fixed.

First, with reference to FIGS. 1 and 2 , a case in which the propulsion providing means 400 includes a fan blade 420 will be described as an embodiment.

The propulsion providing means 400 may include a rotating shaft 410 and a fan blade 420.

The rotation shaft 410 is rotatably installed inside the torso. Additionally, the fan blade 420 is coupled to the rotation shaft 410 and rotates. Here, the rotation shaft 410 and the fan blade 420 may be provided to rotate by the turbine stage 600, for example, the low pressure turbine stage 620.

Meanwhile, referring to FIGS. 1(b) and 2(b), as described above, a bend 310 may be formed in the guide member 300 toward the side direction of the body 100. In this case, In the fan blade 420, the exhaust gas (G) guided by the guide member 300 hits the fan blade 420 and is directed toward the rear of the body 100, opposing the bend 310 of the guide member 300. A bend 421 may be formed in this direction.

Additionally, the fan blades 420 may be formed parallel to the rotation axis 410 toward the rear of the body 100. That is, the fan blade 420 may have a curve 421 formed in a direction opposite to the curve 310 of the guide member 300 and may be formed parallel to the rotation axis 410 toward the rear of the body 100. Additionally, the fan blade 420 may be formed to have a vertical width that increases toward the rear of the body 100.

Due to this type, the exhaust gas sprayed from the combustion chamber 200 is refracted toward the side of the body 100 by the guide member 300, and its speed increases to efficiently hit the fan blade 420. Here, there is an effect of obtaining additional thrust by the fan blade 420 in addition to the basic injection propulsion force due to the impact force hitting the fan blade 420.

Referring to FIGS. 1, 2, and 5, the balance weight 500 is coupled to the rotation shaft 410 at a position opposite to the fan blade 420 and rotates. When one fan blade rotates alone, vibration is generated due to weight imbalance, so to prevent such vibration, a counterweight 500 is provided at an opposing position of the fan blade 420 to rotate by being coupled to the rotation shaft 410. You can.

Here, referring to FIG. 5 , a fan blade 420 may be installed on the outer surface of the rotor 120, and a counterweight 500 may be installed on the inner surface of the rotor 120 on the opposite side of the fan blade 420.

Referring to FIGS. 7 and 8 in another embodiment, a speed increaser 910 may be provided on the guide member 300. Here, the cover 920 is formed to surround the gearbox 910 to protect the gearbox 910. For example, a cover 920 in the form of an empty space may be provided at the center of the guide member 300, and a speed increaser 910 may be installed inside the cover 920.

Additionally, the gearbox 910 may be installed between the turbine stage 600 and the propulsion providing means 400, thereby increasing the rotational speed of the propulsion providing means 400.

Here, one side of the gearbox 910 is connected to the first rotation shaft 411 coupled to the turbine end 600, and the other side of the gearbox 910 is connected to the second rotation shaft 412 coupled to the propulsion providing means 400. ) can be connected to.

That is, the first rotation shaft 411 connects the turbine stage 600 and the gearbox 910, and the second rotation shaft 412 connects the propulsion providing means 400 and the gearbox 910. .

Next, with reference to FIGS. 3 and 4 , a case in which the propulsion providing means 400 includes a fixed blade 460 will be described in another embodiment.

The propulsion providing means 400 may include an inner tube 450 and a fixed blade 460.

The inner cylinder 450 is fixedly installed inside the body 100. And, the fixing collar 460 is coupled to and fixed to the inner tube 450.

Meanwhile, referring to FIGS. 3 and 4, as described above, a bend 310 may be formed in the guide member 300 toward the side direction of the body 100, and in this case, the fixing blade 460 The exhaust gas (G) guided by the guide member 300 hits the fixed blade 460 and is bent (461) in the opposite direction to the bend (310) of the guide member (300) so that it faces the rear of the body (100). This can be formed.

Additionally, the fixing collar 460 may be formed parallel to the inner tube 450 toward the rear of the body 100. That is, the fixing blade 460 may be formed with a curve 461 in a direction opposite to the curve 310 of the guide member 300, and may be formed parallel to the inner tube 450 toward the rear of the body 100. Additionally, the fixed collar 460 may be formed to have a width in the vertical direction that increases toward the rear of the body 100.

Due to this type, the exhaust gas sprayed from the combustion chamber 200 is refracted toward the side of the body 100 by the guide member 300, and its speed increases to efficiently hit the fixed blade 460. Here, there is an effect of obtaining additional thrust by the fixed blades 460 in addition to the basic injection propulsion force due to the impact force hitting the fixed blades 460.

Hereinafter, each embodiment in which the injection propulsion engine 10 using discharged exhaust according to an embodiment of the present invention is combined with an existing engine will be described.

Figure 1(a) is a cross-sectional view of the injection propulsion engine 10 using discharged exhaust according to the first embodiment of the present invention, showing the flow path of the exhaust gas. According to this, high thrust can be obtained even in the supersonic speed range through the rotation of the fan blade 420 in the exhaust gas injected at supersonic speed from the downstream injection nozzle at the very end of the engine.

The first embodiment of Figure 1(a) takes the most common form of a turbofan engine modified according to the principles of the present invention. That is, the guide member 300, the rotating shaft 410, and the fan blade 420 are combined with a general turbofan engine.

Referring to FIG. 1(a), the turbofan 1 according to an embodiment of the present invention has an approximate appearance similar to a general turbofan, with external atmosphere flowing in through the front and exhaust gas flowing through the rear. It is formed in a cylindrical shape from which is released.

As shown in Figure 1 (a), the turbofan 1 according to an embodiment of the present invention includes a body 100, a combustion chamber 200, a high pressure turbine stage 610, and a low pressure turbine stage 620. ), a guide member 300, a rotation shaft 410, and a fan blade 420. Detailed descriptions of each configuration are replaced with the above description.

Here, in the case of the turbofan 1 of this embodiment, the compressor 700 is disposed in front of the combustion chamber 200 to forcibly compress the atmospheric air supplied to the combustion chamber 200. The compressor 700 consists of a plurality of rotating blades and a guide stage, and rotates by the rotational force of the turbine stage 600.

A rotatable turbine stage 600 is disposed at the rear of the combustion chamber 200. The turbine stage 600 may include a high pressure turbine stage 610 and a low pressure turbine stage 620. In FIG. 1(a), the high pressure turbine stage 610 is shown in three stages, but the type and number of turbines are not limited to this and can be modified into various forms.

The high-pressure turbine stage 610 has a plurality of blades installed on the circumference of the rotating body, and rotates at high speed by high-temperature, high-pressure exhaust gas discharged from the combustion chamber 200. The high pressure turbine stage 610 converts the linear kinetic energy of the fluid into useful mechanical rotational energy and operates the compressor 700 through the compressor rotation shaft 710.

The low-pressure turbine stage 620 is located at the rear of the high-pressure turbine stage 610, and the exhaust gas passing through the high-pressure turbine stage 610 rotates the low-pressure turbine stage 620 located at the rear in a reduced speed and pressure state. I order it. The low pressure turbine stage 620 is coupled to the rotating shaft 410. Here, when the low pressure turbine stage 620 coupled to one side of the rotating shaft 410 rotates, the fan blade 420 coupled to the other side of the rotating shaft 410 also rotates.

Exhaust gas leaving the low-pressure turbine stage 620 passes through the guide member 300, where a curve 310 is formed in a similar shape to that of the low-pressure turbine stage 620 and is arranged in a common direction. do.

The guide member 300 not only supports the center so that the low-pressure turbine stage 620 can rotate, but, unlike the prior art, each frame is curved 310 so that it faces the side rather than the axial flow. The shape of the bend 310 has the function of deflecting the exhaust gas deviating from the low-pressure turbine stage 620 toward the side again, and increases the injection speed to supersonic speed, effectively creating a strong vortex state and blowing the fan blade. (420) to hit it effectively and shockingly.

That is, referring to FIG. 1(b), the exhaust gas leaving the low-pressure turbine stage 620 is injected at an angle of approximately -30° to -50° with respect to the horizontal direction, and the guide member 300 rotates this at an angle of -40° to -40°. It is deflected to -70° and the speed is increased to hit the fan blade 420 most efficiently and impactfully.

At this time, the side exhaust gas of Mach 2 to 3, which escapes the guide member 300, is trapped in the casing 110 provided in the body 100, virtually forming a vortex, and collides with the fan blade 420 rotating forward on the way out. , the impact force is very high, and therefore, in addition to the basic injection propulsion force, a significant amount of additional propulsion force can be obtained by the fan blade 420, and the speed is also accelerated by about twice according to the shape of the fan blade 420, reaching Mach 4 to Mach 6. You can.

The fan blade 420 is curved 421 so that the front portion is generally in the same direction as the rear portion of the guide member 300, but as it moves toward the rear end of the fan blade 420, it bends in the same direction as the rotation axis 410. It is structured like this. As a result, when the side exhaust gas that escapes the guide member 300 flows into the front of the fan blade 420, it naturally flows in with low friction, but as it goes toward the rear, the friction increases and the speed increases, increasing the driving force and the injection speed. It also has the effect of speeding up.

In order to accelerate the side exhaust gas discharged through the guide member 300 rearward as quickly as possible, the fan blade 420 is formed with a curve 461 in a direction opposite to the shape of the curve 310 of the guide member 300. , the front part of the fan blade 420 is generally in the same direction as the rear part of the guide member 300, and toward the rear end, it is in the same direction as the axial flow, so that the side exhaust gas that escapes forming a vortex is at its best. It is allowed to hit the fan blade 420 in this state.

It is desirable to limit the number of fan blades 420 to one, but if there are many, the efficiency is reduced due to the shock wave generated when the front part collides with the side exhaust gases flowing in at supersonic speeds of Mach 2 to 3. Since energy loss occurs, it is desirable to configure it alone to reduce the loss.

In addition, when the exhaust gas, which is laid down at -40° to -70°, forms a vortex and escapes, it is blocked by the front element and cannot sufficiently reach the entire surface of the rear element. Therefore, the fan blade is composed of a single fan blade 420. (420) It is desirable to limit it to one so that the exhaust gas can reach the entire surface evenly.

And, the width becomes wider towards the rear, which has the effect of allowing a large amount of exhaust gas to escape smoothly.

When the present invention is implemented as a rotating body in which the fan blade 420 is rotated by the rotational force of the low-pressure turbine stage 620, the single fan blade 420 is vibrated due to weight imbalance, so the fan blade 420 on the opposite side A counterweight 500 is installed on the inner surface of the rotor 120 to prevent vibration.

The exhaust gas flow path and the single fan blade 420 shown in FIG. 1 are shown to be the best choice derived from the above description.

In this way, the fan blade 420 installed at the rear end of the engine generates an enormous impact force because the side exhaust gases of Mach 2 to 3 collide, and as a result, high thrust can be obtained even at supersonic speeds and a lot of thrust can be obtained even within a narrow space. There is a possible effect.

Therefore, this propulsion method of the fan blade 420 can replace a conventional turbofan or a large turboprop fan. In addition, in the case of a reburn turbojet with a high fuel consumption rate, there is an advantage in that it can be designed to be modified into a propulsion engine with a low fuel consumption rate.

Figure 2(a) is a cross-sectional view of the injection propulsion engine 10 using discharged exhaust according to the second embodiment of the present invention, showing the cross-sectional view of the ramjet and the flow path of the exhaust gas. That is, the guide member 300, the rotation shaft 410, and the fan blade 420 are combined with a general ramjet.

As shown in Figure 2 (a), the ramjet 2 according to an embodiment of the present invention includes a body 100, a combustion chamber 200, a turbine stage 600, for example, a high pressure turbine stage, and a guide. It includes a member 300, a rotating shaft 410, and a fan blade 420. Detailed descriptions of each configuration are replaced with the above description. And, it includes a compression chamber 800.

Referring to FIG. 2(a), the ramjet (2) engine according to an embodiment of the present invention has a form similar to that of a typical turbojet engine with the forced compressor installed at the front removed.

Since a general ramjet is used in high-speed aviation, a ram effect occurs when the air flowing in through the intake is naturally compressed, and a turbojet engine can also obtain the same ram effect as a ramjet engine by removing the front compressor at high speed, so the present invention uses these contents.

Referring to FIG. 2(a), a compression chamber 800 is installed in front of the body 100 to naturally compress the air introduced by the forward force of the body 100.

Natural compressed air introduced through the compression chamber 800 is mixed with fuel and burned in the combustion chamber 200. Combustion gas rotates the turbine stage 600 installed at the rear. Here, the turbine stage 600 may be a high pressure turbine stage. At this time, since the rotation axis 410 of the turbine stage 600 must be located at the center of the body 100, the combustion chambers 200 are distributed around the rotation axis 410 like a turbo fan.

A guide member 300 is installed at the rear of the turbine stage 600. The guide member 300 has a curve 310 similar to the shape of the turbine stage 600 and is installed in the same direction.

In addition to supporting the center of the turbine stage 600 so that it can rotate, the guide member 300 is curved 310 so that, unlike the prior art, each frame faces the side rather than the axial flow. Due to the shape of the bend 310, the exhaust gas on the side that leaves the turbine stage 600 is once again deflected in the side direction and its speed is increased to effectively and shockingly hit the fan blade 420.

In other words, a strong vortex state is created to effectively and shockingly hit the fan blade 420. A fan blade 420 is installed at the rear of the guide member 300. The fan blade 420 is connected to the turbine stage 600 through the rotation shaft 410, and when the turbine stage 600 rotates, the fan blade 420 also rotates.

In addition, as described above, the fan blade 420 serves to quickly push the supersonic side exhaust gas discharged through the guide member 300 rearward, so in the ramjet 2 engine as in the present embodiment, the exhaust gas In addition to the basic thrust, additional thrust can be obtained by the fan blades 420.

At this time, the side exhaust gas of Mach 2.5 to 3.5, which escapes from the guide member 300, is trapped in the casing 110 provided in the body 100, virtually forming a vortex, and collides with the fan blade 420 rotating forward on the way out. The impact force is very high, so in addition to the basic injection propulsion force, a significant amount of additional propulsion force can be obtained by the fan blade 420, and the speed can also be accelerated by about twice according to the shape of the fan blade 420, reaching Mach 5 to Mach 7. there is.

Referring to FIG. 2(b), the front portion of the fan blade 420 is formed with a curve 421 so that the front portion is generally in the same direction as the rear portion of the guide member 300, but the bend 421 is formed at the rear end of the fan blade 420. Increasingly, it is configured to be in the same direction as the axial flow of the engine. As a result, when the side exhaust gas that escapes the guide member 300 flows into the front of the fan blade 420, it naturally flows in with low friction, but as it goes toward the rear, the friction increases and the speed increases, increasing the driving force and the injection speed. It also has the effect of speeding up.

It is desirable to limit the number of fan blades 420 to one. If there are multiple fan blades, the efficiency decreases due to the shock wave generated when the front part collides with the side exhaust gas flowing in at supersonic speed, and the fan blade 420 is reduced from -40° to -70°. When the exhaust gas laid down at ° exits forming a vortex, it is blocked by the front element and cannot sufficiently reach the rear element. Therefore, it is composed of a single fan blade (420) so that the exhaust gas is evenly distributed over the entire surface of the fan blade (420). It is desirable to be able to reach it.

In addition, when the side exhaust gas of Mach 3 to 4 hits the front of the fan blade 420, a shock wave is generated, which not only reduces efficiency but also causes a large amount of energy loss, so to reduce the energy loss, a shock wave is generated. It is desirable.

In order to accelerate the side exhaust gas discharged through the guide member 300 rearward as quickly as possible, the fan blade 420 is formed with a curve 421 in a direction opposite to the shape of the curve 310 of the guide member 300. , the front part of the fan blade 420 is generally in the same direction as the rear part of the guide member 300, and toward the rear end, it is in the same direction as the axial flow, so that the side exhaust gas that escapes forming a vortex is at its best. It is allowed to hit the fan blade 420 in this state.

And, the width becomes wider towards the rear, which has the effect of allowing a large amount of exhaust gas to escape smoothly.

When the present invention is implemented as a rotating body in which the fan blade 420 rotates by the rotational force of the turbine stage 600, the single fan blade 420 generates vibration due to weight imbalance, so the rotor opposite to the fan blade 420 (120) A counterweight 500 is installed on the inner surface to prevent vibration.

The exhaust gas flow path and the single fan blade 420 shown in FIG. 2 are shown to be the best choice derived from the above description.

In this way, the fan blade 420 installed at the rear end of the engine generates an enormous impact force because the side exhaust gases of Mach 2.5 to 3.5 collide. As a result, high thrust can be obtained even at supersonic speeds and a lot of thrust can be obtained even within a narrow space. There is a possible effect.

Therefore, this propulsion method of the fan blade 420 has the advantage of being able to be designed into a propulsion engine superior in thrust and speed compared to a ramjet with a simple structure and a high fuel consumption rate.

Figure 3(a) is a cross-sectional view of the injection propulsion engine 10 using discharged exhaust according to the third embodiment of the present invention, showing the flow path of the exhaust gas.

Referring to FIG. 3(a), the turbojet 3 of the present invention has an approximate appearance similar to a general reburn turbojet structure. That is, the guide member 300 and the fixed blade 460 are coupled to a general afterburning turbojet engine.

Here, the shape of the body 100 can be modified into various forms depending on the type of engine and required parts, and is roughly cylindrical, with external air flowing in through the front and exhaust gas being discharged from the rear.

As shown in Figure 3 (a), the turbojet 3 according to an embodiment of the present invention includes a body 100, a combustion chamber 200, a turbine stage 600, for example, a high pressure turbine stage, It includes a guide member 300 and a fixing blade 460. Detailed descriptions of each configuration are replaced with the above description. And, it includes a compressor 700.

A combustion chamber 200 is installed within the body 100. The combustion chamber 200 provides a space for combustion by injecting fuel into compressed air. Additionally, the air and fuel burned in the combustion chamber 200 are ejected rearward as high-temperature, high-pressure, fast exhaust gas.

At this time, in the case of the turbojet 3 of this embodiment, the compressor 700 is disposed in front of the combustion chamber 200 to forcibly compress the atmospheric air supplied to the combustion chamber 200. The compressor 700 consists of a plurality of rotating blades and a guide stage, and rotates by the rotational force of the turbine stage 600.

A rotatable turbine stage 600 is disposed at the rear of the combustion chamber 200. In FIG. 3(a), the turbine stage 600 is shown in three stages, but the type and number of turbines are not limited to this and can be modified into various forms.

The turbine stage 600 has a plurality of blades installed on the circumference of the rotating body, and rotates at high speed by high-temperature, high-pressure exhaust gas discharged from the combustion chamber 200. The turbine stage 600 converts the linear kinetic energy of the fluid into useful mechanical rotational energy and operates the compressor 700 through the compressor rotation shaft 710.

The exhaust gas exiting the turbine stage 600 passes through the guide member 300 located at the rear. The guide member 300 has the function of supporting the center so that the turbine stage 600 can rotate, and each frame has the function of supporting the turbine stage 600. Like the wings of stage 600, a curve 310 is formed to face the side rather than axial flow. The shape of the bend 310 has the function of bending the lateral exhaust gas that has escaped the turbine stage 600 in the lateral direction once again and increases the injection speed so that it hits the fixed blade 460 effectively and shockingly. .

That is, referring to FIG. 3(b), the side exhaust gas leaving the turbine stage 600 is injected at an angle of approximately -30° to -50° with respect to the horizontal direction, and the guide member 300 rotates this at an angle of -40° to -40°. By deflecting it to -70° and increasing the spray speed to Mach 3 to 4, the casing (110) traps and collects the natural discharge into the atmospheric air, effectively creating a vortex state, so that it hits the fixed blade (460) most effectively and shockingly. .

At the rear of the guide member 300, a fixed blade 460 is fixed to the inner cylinder 450 installed inside the body 100, and the exhaust gas in the side direction discharged through the guide member 300 is fixed at a supersonic speed. It collides with the blade 460, thereby providing a high driving force in the shape of the fixed blade 460.

In other words, although it is a collision of only one side of the exhaust gas, the impact force is very high, and therefore, a lot of thrust can be obtained even at supersonic speeds and a lot of thrust can be obtained even within a narrow space.

The fixed blade 460 is curved 461 so that the front portion is generally in the same direction as the rear portion of the guide member 300, but as it moves toward the rear end of the fixed blade 460, it moves in the same direction as the axial flow of the engine. It is composed. As a result, when the side exhaust gas leaving the guide member 300 flows into the front of the fixed blade 460, it naturally flows in with little friction, but then as it moves toward the rear, shock increases and speed increases, causing the fixed blade 460 It has the effect of obtaining a large amount of forward propulsion without rotating like the sail of a sailboat.

At this time, the side exhaust gas of Mach 2.5 to 3.5 discharged from the guide member 300 is trapped in the casing 110 provided in the body 100, virtually forming a vortex, and hits the fixed blade 460 on the way out, so the exhaust gas Although it is only a collision on one side, the impact force is significant, and like the sail of a sailboat, there is an effect of obtaining a significant amount of additional propulsion from the fixed blades 460 in addition to the basic injection propulsion force without the fixed blades 460 rotating.

It is desirable to limit the number of fixed blades 460 to one. If there are multiple blades, the efficiency is reduced due to the shock wave generated when the front part collides with the side exhaust gas rushing in at supersonic speed, and the range is -40° to -70°. When the exhaust gas laid down at ° exits forming a vortex, it is blocked by the front element and cannot sufficiently reach the rear element. Therefore, by installing a single fixed blade (460), the exhaust gas is evenly distributed over the entire surface of the fixed blade (460). It is advisable to limit it to one so that it can be reached.

In addition, when the side exhaust gas of Mach 2 to 3 hits the front of the fixed blade 460, a shock wave is generated. At this time, a large amount of energy is lost, so it is preferable to configure it alone to reduce the energy loss.

The exhaust gas flow path and the single fixed blade 460 shown in FIG. 3 are shown to be the best choice derived from the above description.

In this way, the fixed blade 460 installed at the rear end of the engine collides with the side exhaust gases of Mach 2.5 to 3.5 while escaping, forming a vortex, so although it is a collision of only one side of the exhaust gases, a tremendous impact force is generated, and as a result, even in the supersonic speed range, It is possible to obtain high thrust and has the effect of obtaining a lot of thrust even within a narrow space.

These fixed blades 460 are curved 461 in a direction opposite to the curved shape 310 of the guide member 300 in order to obtain additional thrust in the side exhaust gas discharged through the guide member 300. The front part of the fixed blade 460 is generally in the same direction as the rear part of the guide member 300, and towards the rear end, it is in the same direction as the axial flow, so that the side exhaust gas that escapes forming a vortex is in the best condition. It causes it to hit the fixed collar (460).

And, the width becomes wider towards the rear, which has the effect of allowing a large amount of exhaust gas to escape smoothly.

Therefore, the propulsion method of this fixed blade 460 has the advantage of being able to transform a conventional reburn turbojet with a high fuel consumption rate into a propulsion engine with a low fuel consumption rate by a simple method.

Figure 4(a) is a cross-sectional view of the injection propulsion engine 10 using discharged exhaust according to the fourth embodiment of the present invention, showing the cross-sectional view of the ramjet and the flow path of the exhaust gas. That is, the guide member 300 and the fixed blade 460 are coupled to a general ramjet.

The ramjet 4 according to an embodiment of the present invention has a shape similar to that of a general turbojet with the front compressor and rear turbine stage removed.

As shown in Figure 4 (a), the ramjet 4 according to an embodiment of the present invention includes a body 100, a combustion chamber 200, a guide member 300, and a fixed blade 460. do. Detailed descriptions of each configuration are replaced with the above description. And, it includes a compression chamber 800.

As described above, a general ramjet utilizes the ram effect, in which air is naturally compressed by the forward force of the engine, and does not require a separate compressor 700.

Referring to FIG. 4(a), a compression chamber 800 is installed in front of the body 100 to naturally compress the air introduced by the forward force of the body 100.

Natural compressed air introduced through the compression chamber 800 is mixed with fuel and burned in the combustion chamber 200. A guide member 300 is installed at the rear of the combustion chamber 200. The guide member 300 in contact with the combustion chamber 200 has a shape similar to the blade of a typical turbine stage, and the latter half of the blade is laid on the side, so that the high-temperature and high-pressure combustion gas just discharged from the combustion chamber 200 is deflected to the side. , made at supersonic speed to hit the fixed blade 460 most effectively and shockingly.

That is, the high-temperature and high-pressure combustion gas just created in the combustion chamber 200 is deflected to -40° to -70° and converted into supersonic exhaust gas of Mach 3 to 4, which is naturally discharged into the atmospheric air. The casing 110 traps this. Gathered, it actually creates a strong vortex state and causes it to hit the fixed blade 460 effectively and shockingly.

At the rear of the guide member 300, a fixed blade 460 is fixed to the inner cylinder 450 installed inside the body 100, and the exhaust gas in the side direction discharged through the guide member 300 is fixed at a supersonic speed. It is provided to collide with the blade 460, thereby obtaining a high driving force in the shape of the fixed blade 460.

At this time, the side exhaust gas of Mach 3 to 4 discharged from the guide member 300 is trapped in the casing 110 provided in the body 100 while being naturally discharged into the atmospheric air, virtually forming a vortex state and being fixed on the way out. Because it hits the blade 460, it is only a collision of one side of the exhaust gas, but the impact force is significant, and a significant amount of additional propulsion can be obtained from the fixed blade 460 in addition to the basic injection propulsion force without the fixed blade 460 rotating like the sail of a sailboat. There is an effect.

Referring to FIG. 4(b), the front portion of the fixing blade 460 is formed with a curve 461 so that the front portion is generally in the same direction as the rear portion of the guide member 300, but the rear end of the fixing blade 460 Increasingly, it is configured to be in the same direction as the axial flow of the engine. As a result, when the side exhaust gas leaving the guide member 300 flows into the front of the fixed blade 460, it naturally flows in with little friction, but then as it moves toward the rear, shock increases and speed increases, causing the fixed blade 460 It has the effect of gaining a significant amount of additional propulsion without rotating like the sail of a sailboat.

It is desirable to limit the number of fixed blades 460 to one. If there are multiple blades, the efficiency decreases due to the shock wave in the front part, and the exhaust gas tilted at -40° to -70° escapes forming a vortex. In the exiting state, since it is blocked by the front element and cannot sufficiently reach the rear element, it is desirable to install a single fixed blade 460 and limit it to one so that the exhaust gas can evenly reach the entire surface of the fixed blade 460.

In addition, when the side exhaust gas of Mach 3 to 4 hits the front of the fixed blade 460, a shock wave is generated, resulting in a large amount of energy loss due to reduced efficiency, so it is preferable to configure it alone to reduce the energy loss. do.

These fixed blades 460 are curved 461 in a direction opposite to the curved shape 310 of the guide member 300 in order to accelerate the side exhaust gas discharged through the guide member 300 rearward as quickly as possible. , the front part of the fixed blade 460 is generally in the same direction as the rear part of the guide member 300, and toward the rear end, it is in the same direction as the axial flow, so that the side exhaust gas that escapes forming a vortex is at its best. It is allowed to hit the fixed collar (460).

And, the width becomes wider towards the rear, which has the effect of allowing a large amount of exhaust gas to escape smoothly.

The exhaust gas flow path and the single fixed blade 460 shown in FIG. 4 are shown to be the best choice derived from the above description.

In this way, the fixed blades 460 installed inside the ramjet (4) engine collide with the side exhaust gases of Mach 3 to 4 while escaping forming a vortex, so although it is a collision of only one side of the exhaust gases, a tremendous impact force is generated, thereby The best thrust can be obtained even at very high supersonic speeds, and a lot of thrust can be obtained even within a narrow space.

Therefore, the propulsion method of this fixed blade 460 has the advantage of being able to transform a conventional simple ramjet with high fuel consumption into a propulsion engine with low fuel consumption by adding simple equipment.

Meanwhile, Figure 5 shows the fan blade 420 of Figures 1 and 2 together with the rotor 120. Referring to Figure 5, the fan blade 420 is installed on the outer surface of the rotor 120 and vibrates. The counterweight 500 to prevent may be installed on the opposite inner surface of the fan blade 420.

As shown in FIG. 5, while the fan blade 420 is mounted on the outer surface of the rotor 120, a vortex is formed by the lateral exhaust gas discharged from the guide member 300, and the incoming supersonic exhaust gas is Since it is pushed forward and discharged backwards in forward rotation, a large amount of forward thrust is generated on the body surface of the fan blade 420 by the fan blade 420, and the speed is also accelerated by about twice according to the shape of the fan blade 420. This has the effect of achieving high supersonic speeds.

Here, if the fan blade 420 is installed alone, it is deflected to one side and vibration occurs when the fan blade 420 rotates, so the fan blade 420 is formed on the inner surface of the rotor 120 without affecting the flow of exhaust gas. Vibration caused by the separately installed fan blade 420 can be prevented by installing a counterweight 500 on the opposite side.

And, Figure 6 shows a state in which the fixing blade 460 of Figs. 3 and 4 is mounted on the inner cylinder 450. In a state where the fixing blade 460 is fixedly mounted on the outer surface of the inner cylinder 450, the guide member When a vortex is formed by the lateral exhaust gas discharged from (300), the exhaust gas hits the fixed blade 460 while escaping and the impact force generated causes the effect of obtaining significant forward thrust without the rotation of the fixed blade 460. there is.

Accordingly, embodiments of the present invention have the effect of minimizing losses that may occur during rotation of a fan of the prior art because they produce additional forward thrust using supersonic exhaust exhaust as a propulsion medium.

In addition, since the fan blade 420 can be installed in the body 100 without installing a large fan used in an existing turbofan or turboprop, the weight burden caused by the large fan is reduced and the front area of the engine is reduced. Therefore, it has the effect of significantly reducing resistance caused by air friction when operating an aircraft.

In addition, this principle is also applied to ramjets, not only by simply propulsion from exhaust gas ejection, but also by obtaining additional propulsion by fan blades (420) rotating in the exhaust gas or by adding propulsion by fixed blades (460). This can be achieved by increasing engine efficiency, which has the effect of not only saving fuel but also improving speed.

Figure 7(a) is a cross-sectional view of an injection propulsion engine using discharge exhaust according to a fifth embodiment of the present invention, which is further provided with a speed increaser compared to the first embodiment of Figure 1(a), and Figure 8(a) is a This is a cross-sectional view of the injection propulsion engine using discharge exhaust according to the sixth embodiment of the present invention, and is further provided with a speed increaser compared to the second embodiment of FIG. 2(a).

In the above-described first and second embodiments, the turbine stage 600 and the propulsion providing means 400 are connected to one rotation shaft 410. Accordingly, the rotational speed of the turbine stage 600 and the rotational speed of the propulsion providing means 400 are the same, and thereby the effects described in the first and second embodiments are recognized.

However, in the fifth and sixth embodiments, the accelerator 910 is provided so that the rotational speed of the propulsion providing means 400 is much faster than the rotational speed of the turbine stage 600, so hypersonic exhaust gas can be produced. This has the effect of being able to be used in hypersonic propulsion engines.

Referring to FIG. 7 regarding the fifth embodiment, when the turbine stage 600, for example, the low-pressure turbine stage 620 rotates, the gearbox 910 rotates the low-pressure turbine stage 620 according to a preset gear ratio. The speed is increased 2 to 3 times more than that, and as a result, the propulsion providing means 400 connected to the speed increaser 910 rotates faster.

Here, referring to FIGS. 7(a) and 7(b), the fan blade 420 of the propulsion providing means 400 may be formed in a shape that accelerates the fluid approximately twice. Accordingly, the fan blade 420 accelerates the exhaust gas, which has a speed of Mach 2 to 3, which is naturally discharged into the atmosphere through the guide member 300 by about twice, to a speed of Mach 4 to 6 by the above-described shape and generates it in the atmosphere. It can be arranged to be released naturally.

In addition, as described above, the fan blade 420 is set to rotate about 2 to 3 times faster than the rotation speed of the low pressure turbine stage 620 by the gearbox 910 provided at the center of the guide member 300, resulting in As a result, the impact force with the exhaust gas is amplified by 2 to 3 times and the exhaust gas speed is increased by 2 to 3 times, creating a hypersonic exhaust speed of Mach 8 to 18.

In other words, if you calculate this arithmetically, an exhaust speed of Mach 2 to 3 (exhaust gas speed) In other words, multiplying the exhaust gas speed Mach 2 to Mach 3 by the multiplier 2 of the fan blade 420 and multiplying this by the rotational speed multiplier 2 to 3 of the accelerator 910 gives an exhaust speed of Mach 8 to Mach 18. can be made

Therefore, even if less fuel is used than the fuel normally used, a much higher exhaust speed can be produced. It creates exhaust gas in the hypersonic range, which cannot be obtained with current technological means, and can be used for efficient hypersonic propulsion engines. There is a possible effect.

In another embodiment, referring to FIG. 8 of the sixth embodiment, when the turbine stage 600, for example, the high pressure turbine stage, rotates, the propulsion providing means 400 is rotated by the speedometer 910. The speed is increased three times and rotates at a much faster speed.

Here, referring to FIGS. 8(a) and 8(b), the fan blade 420 of the propulsion providing means 400 may be formed in a shape that accelerates the fluid approximately twice. Accordingly, the fan blade 420 accelerates the exhaust gas, which has a speed of Mach 2 to 3, which is naturally discharged into the atmosphere through the guide member 300 by about twice, to a speed of Mach 4 to 6 by the above-described shape and generates it in the atmosphere. It can be arranged to be released naturally.

In addition, as described above, the fan blade 420 is set to rotate about 2 to 3 times faster than the rotation speed of the turbine stage 600 by the gearbox 910 provided at the center of the guide member 300, resulting in The impact force with the exhaust gas is amplified by 2 to 3 times and the exhaust gas speed is also increased by 2 to 3 times, creating a hypersonic exhaust speed of Mach 8 to 18.

In other words, if you calculate this arithmetically, an exhaust speed of Mach 2 to 3 (exhaust gas speed) In other words, multiplying the exhaust gas speed Mach 2 to Mach 3 by the multiplier 2 of the fan blade 420 and multiplying this by the rotational speed multiplier 2 to 3 of the accelerator 910 gives an exhaust speed of Mach 8 to Mach 18. can be made

Therefore, even if less fuel is used than the fuel normally used, a much higher exhaust speed can be produced. It creates exhaust gas in the hypersonic range, which cannot be obtained with current technological means, and can be used for efficient hypersonic propulsion engines. There is a possible effect.

It should be noted that descriptions of common configurations, operations, and effects in each embodiment can be applied to other embodiments even if omitted.

Although the present invention has been described above with limited examples and drawings, the present invention is not limited thereto, and the technical idea of the present invention and the description below will be understood by those skilled in the art to which the present invention pertains. Of course, various modifications and variations are possible within the scope of equivalence of the patent claims.

10: Injection propulsion engine using discharge exhaust 100: Body
110: Casing 120: Rotor
130: Outer frame 200: Combustion chamber
300: Guide member 310: Bend
400: Propulsion providing means 410: Rotating shaft
411: first rotation axis 412: second rotation axis
420: fan blade 421: bent
450: inner tube 460: fixed collar
461: bend 500: counterweight
600: Turbine stage 610: High pressure turbine stage
620: Low pressure turbine stage 700: Compressor
710: Compressor rotation shaft 800: Compression chamber
910: Increaser 920: Cover

Claims (17)

body (100);
A combustion chamber 200 installed within the body 100 and injecting fuel into compressed air for combustion;
A turbine stage 600 disposed at the rear of the combustion chamber 200 and configured to rotate;
The center of the turbine stage 600 is supported so that it can rotate, and the exhaust gases escaping from the turbine stage 600 in the side direction are once again in a state in which the turbine stage 600 is laid down at -30° to -50° relative to the horizontal direction. A guide member 300 configured to increase the jet speed to Mach 2 to Mach 3 and create a vortex state by deflecting it to -40° to -70° in the lateral direction; and
It includes a propulsion providing means (400) that provides propulsion by hitting the exhaust gas guided from the guide member (300),
An injection propulsion engine using discharge exhaust, characterized in that one propulsion providing means is provided at the rear of the guide member (300). According to paragraph 1,
The means for providing propulsion is,
Rotation axis 410; and
An injection propulsion engine using exhaust discharge, characterized in that it includes a fan blade (420) that is coupled to the rotation shaft (410) and rotates. According to paragraph 2,
The fan blade 420 is curved 310 of the guide member 300 so that the exhaust gas guided by the guide member 300 hits the fan blade 420 and heads toward the rear of the body 100. An injection propulsion engine using discharge exhaust, characterized by a bend in the opposite direction. According to paragraph 3,
The fan blade (420) is an injection propulsion engine using discharge exhaust, characterized in that it is formed in parallel with the rotation axis (410) toward the rear of the body (100). According to paragraph 4,
The fan blade (420) is an injection propulsion engine using discharge exhaust, characterized in that the width increases toward the rear of the body (100). According to paragraph 2,
An injection propulsion engine using exhaust discharge, characterized in that it further includes a counterweight (500) coupled to the rotation shaft (410) and rotating at a position opposite to the fan blade (420). According to paragraph 1,
The means for providing propulsion is,
An inner cylinder 450 installed inside the body 100; and
An injection propulsion engine using discharge exhaust, characterized in that it includes a fixed blade (460) fixed to the inner cylinder (450). In clause 7,
The fixed blade 460 is characterized in that it is curved in a direction opposite to the bend of the guide member so that the exhaust gas guided by the guide member 300 hits the fixed blade 460 and heads toward the rear of the body. An injection propulsion engine using discharged exhaust. According to clause 8,
An injection propulsion engine using discharge exhaust, characterized in that the fixed blades (460) are formed parallel to the inner cylinder (450) toward the rear of the body (100). According to clause 9,
An injection propulsion engine using discharge exhaust, characterized in that the fixed blades (460) are formed to increase in width toward the rear of the body (100). In clause 7,
The guide member 300 is an injection propulsion engine using discharge exhaust, characterized in that it is configured to create a vortex state by increasing the injection speed to Mach 3 to Mach 4. According to paragraph 1,
The turbine stage 600 is,
A high-pressure turbine stage 610 rotated by exhaust gas discharged from the combustion chamber 200; and
An injection propulsion engine using discharged exhaust, characterized in that it includes a low-pressure turbine stage (620) that is rotated by exhaust gas passing through the high-pressure turbine stage (610) and is coupled to the rotation shaft of the propulsion providing means (400). According to paragraph 1,
An injection propulsion engine using discharge exhaust, characterized in that it further includes a compressor (700) disposed in front of the combustion chamber (200) to forcibly compress the atmospheric air supplied to the combustion chamber (200). According to paragraph 1,
An injection propulsion engine using discharge exhaust, characterized in that it further comprises a compression chamber (800) that naturally compresses the air flowing into the body by the forward force of the body (100). delete According to paragraph 1,
An injection propulsion engine using exhaust discharge, characterized in that it includes a speedometer (910) provided on the guide member (300). According to clause 16,
An injection propulsion engine using discharge exhaust, characterized in that it includes a cover (920) surrounding the speedometer (910).