JP5336671B2 - Distributed injection engine - Google Patents

Description

The marine engine of the present invention relates to a distributed injection engine that injects exhaust gas of a gas turbine from a small diameter pipe and increases thrust through seawater .

  Conventional turbojets are now used only by fighters. An aircraft that employs an afterburner is a fighter afterburner, which temporarily increases the thrust of the turbojet engine. It is a device that temporarily increases the thrust by increasing the speed of the gas ejected from the exhaust nozzle by additionally injecting fuel into the exhaust gas and combusting it at the tail tube portion after the normal turbine.

In general, turbofan engines are used in general passenger aircraft. In order to improve the propulsion efficiency at low speed, a fan is provided in front of the air compressor or behind the turbine, and the air flow obtained by driving the fan is left as a part of the exhaust energy of the fuel gas. This was a gas turbine engine of a type that obtains thrust by separating or mixing with a jet stream generated with the energy of In the turbofan engine, the noise of the exhaust energy of the fuel gas was surrounded by a fan attached to the front, making the overall noise quieter.

  An engine that flies at a lower speed is a turbo-pop engine, which is essentially the same as a turboshaft engine, and is a type of turbine engine that obtains thrust by using most of the exhaust gas energy for propeller rotation. It is attached to the domestic transport aircraft YS-11.

Japanese Patent Application No. 2007-525573 Japanese Patent Publication 3-51899

  The aircraft that used the conventional turbojet was a fighter, and there was a fighter afterburner. In order to temporarily increase the thrust of the turbo jet, usually in the tail pipe part after the turbine, additional fuel is injected into the exhaust gas and burned, and the speed of the gas ejected from the exhaust nozzle is increased, Although it was a device that temporarily increased thrust, it was noisy and fuel efficiency was poor.

  In general, turbofan engines are used in general passenger aircraft. In order to improve the propulsion efficiency at low speed, a fan is provided in front of the air compressor or at the rear of the turbine, and the air flow obtained by driving the fan with a part of the exhaust energy of the combustion gas It is a type of gas turbine engine that obtains thrust by separating or mixing with a jet stream generated by energy, but its structure is complicated.

  The engine that flies at a lower speed is a turbo-pop engine, which is essentially the same as a turbo-shaft engine, and is a type of turbine engine that obtains thrust by using most of the exhaust gas energy to rotate the propeller. However, the noise of the propeller was loud and the structure was complicated.

  Therefore, the distributed injection type engine of the present invention has a turbine (3) from the compressor (1) through the combustor (2), and the exhaust gas (5c) is provided with a small diameter pipe (5) attached to both blades. The distributed injection type engine which flies at low speed by injecting through.

  In order to achieve the above object, a distributed injection engine of an aircraft engine has a turbine (3) from a compressor (1) through a combustor (2), and the exhaust gas (5c) is attached to both wings. Moreover, the objective was achieved by injecting from several small diameter pipes (5) and making it into a thrust.

In order to achieve the above object , a distributed injection engine of an aircraft engine has a turbine (3) from a compressor (1) through a combustor (2), and the exhaust gas (5c) is attached to both wings. The objective was achieved by injecting from the small-diameter pipe (5) through the afterburner (4) in the pipe (5a) and using it as thrust.

In order to achieve the object of the present invention, a distributed engine of a marine engine has a turbine (3) from a compressor (1) through a combustor (2), and the exhaust gas (5c) is supplied to the stern. The objective was achieved by using propulsive force through a small diameter pipe (5) attached to the pipe.

In order to achieve the above object , a counter-injection engine of a counter-rotating engine includes a shaft blade (9) provided with a shaft turbine (9b) via a shaft (9a), and a tube blade (10) A pipe turbine (10b) is provided via the pipe body (10a). And a casing (11) attaches a combustor (2) between a tube blade (10) and a tube turbine (10b). And the casing (11) achieved the objective by injecting from a plurality of small diameter pipes (5) through the pipe (5a).

The distributed injection engine of the present invention has the following effects.
(B) By injecting from a small diameter, an aircraft engine flying at a low speed with a high specific thrust is obtained.
(B) Noise is reduced by spraying from a small diameter.
(C) Thrust is increased by injecting a small-diameter afterburner.
(D) By taking out the injection of the present invention from a small diameter pipe, it can be used for ships.
(E) The aircraft engine is a counter-rotating gas turbine and has high efficiency.
(F) When flying at high speed like a ramjet, there will be no resistance because there is no stationary blade.

The figure is a schematic diagram showing the plane of an airplane. The figure is a sectional view of a wing showing a small diameter nozzle. The figure is a sectional view of a wing showing a small-diameter afterburner. The figure is a schematic diagram comparing a turbojet and a distributed injection engine. The figure is a cross-sectional view of a ship showing a small-diameter nozzle. The figure is a schematic view of a jet boat. The figure is a half sectional view of a counter-rotating gas turbine.

An aircraft engine of a distributed injection type engine has a turbine (3) from a compressor (1) through a combustor (2), and a large number of exhaust gases (5c) attached to both wings through pipes (5a). The small diameter pipe (5) is used as a thrust.

  Many of the small-diameter pipes (5) attached to both wings have a high friction with air, and thus become a low-speed aircraft engine. The conventional principle is the law of action and reaction, and since fighter aircraft and the like have exhaust gas as a thrust, they exhausted the exhaust gas vigorously and became a thrust.

  However, the present invention is not a law of action and reaction, and the exhaust gas (5c) that exits is a small diameter pipe (5) as shown in FIG. A turbo jet of A and a distributed injection type engine of B of the present invention will be described by comparing schematic diagrams.

  A in FIG. 4 is a turbojet, an engine having a thrust of 10 tons, and the injection port has a diameter of φ1000. Since the turbojet uses the law of action and reaction, it is usually 200 meters because the thrust increases when the jet flows without resistance. And since the injection port exhausts at a speed higher than the sound velocity, waves with different air densities are generated at the exhaust port. If the injection of the exhaust gas (5c) is completely suppressed by pushing the injection port, for example, there is a pressure of 2 Pascals, so the area of the diameter φ1000 is 7,850 square centimeters and a thrust of 157 tons is produced. The present invention is to inject from the small diameter pipe (5) in order to approach the state where the partition is always present.

  The distributed injection type engine of FIG. 4B showing the small-diameter pipe (5) is the same as the pressure when the liquid in the sealed container applies pressure according to Pascal's principle, not the law of action and reaction. A large amount of pressure is transmitted to every part of the liquid. The theory is that when a hole is made in the container, the pressure will drop, so if the pressure leaked from the hole is replenished and the same pressure is maintained, the thickness of the hole becomes the thrust. And if you make one large hole at that time, even if the hole area is the same, if you make many small holes, the amount of water will decrease.

  Therefore, the injection port of the distributed injection type engine has a diameter of φ1 and is injected with 2 Pascals from 1,000,000 small-diameter pipes (5). 200 tons. And the exhaust gas (5c) coming out of the hole entrains the atmosphere (5d) and guides the atmosphere (5d) in the direction of the exhaust gas (5c). Therefore, the distributed injection engine does not exhaust as much as expected. If the exhaust port is large, the exhaust gas (5c) that comes out has less friction in the atmosphere (5d), so the rate of friction is reduced, and therefore the amount of exhaust is increased.

  And it is the same as a pump that sucks up liquid by a jet like a jet pump. If the resistance becomes so as to obstruct the exhaust gas (5c) to be discharged, the amount to be ejected is reduced. Therefore, if the engine having a thrust of 10 tons is ejected from a large nozzle and that from a small diameter pipe (5) with a distributed injection engine is compared with the thrust of 200 tons, the distributed injection engine is better. However, the speed will be slower than the propeller aircraft, about 200 km / h.

  If the air from the small-diameter pipe (5) converts pressure energy into velocity energy and releases it into the air, the surrounding air is entrained into a large air flow, and instead air that is ejected from the nozzle The amount of is reduced. In other words, the distributed injection type engine is not a turbojet (7) injection, but compresses a large amount of air at a high pressure and is used as a light compressor with a small capacity. Moreover, no matter how much noise is emitted from the small-diameter pipe (5), the small-diameter pipe (5) has a small energy level, so the noise is small. Is not annoying.

  However, if 1,000,000 small-diameter pipes (5) are installed, the length of the wings (5b) is 1 kilometer and cannot be installed. Can be attached to the wing (5b) of a large airplane. Then, since φ20 has less resistance than φ1, a large amount of exhaust gas (5c) is emitted and injected for about 70 meters. Then, the specific thrust of the airplane will deteriorate, but the speed will be about 700 km / h. If φ100 is used, 100 small diameter tubes (5) may be used. Furthermore, the injection port of the small diameter pipe (5) may be not only a round shape but also a long and narrow one.

  Therefore, the pressure of the small-diameter pipe (5) becomes a thrust, and the exhaust gas (5c) is injected into the surrounding atmosphere (5d) when the exhaust gas (5c) is injected. It has the same effect as a jet pump that allows air to flow in the direction.

  Moreover, by attaching the small-diameter pipe (5) on the wing (5b), the flow velocity of the lower atmosphere and the upper atmosphere (5d) of the wing (5b) is different. The wing (5b) increases the lift.

An aircraft engine of a distributed injection type engine has a turbine (3) from a compressor (1) through a combustor (2), and its exhaust gas (5c) is passed through an afterburner (4) attached to both wings. It is ejected from the small diameter pipe (5) to enhance the thrust.

  The thrust was reduced by the exhaust gas (5c) being cooled. In order to solve the problem, the exhaust gas (5c) is again burned by the afterburner (4) attached to the pipe (5a) before being ejected from the small diameter pipe (5), the temperature is increased, and the thrust is increased. It is. Therefore, when the afterburner (4) is not used, the one with the afterburner (4) attached is designed so that the thrust is inferior.

In the distributed injection type engine of the present invention , the ship (6) engine has a turbine (3) from a compressor (1) through a combustor (2), and its exhaust gas (5c) is attached to the stern. The small diameter pipe (5) is used for thrust.

  The small-diameter pipe (5) is ejected in seawater (6b), the outlet of the exhaust gas (5c) is surrounded by a cylinder (6a), and the seawater (6b) is discharged by injection of the exhaust gas (5c). The discharged seawater (6b) has a negative pressure in front of the cylinder (6a). And it suck | inhales from a front pipe | tube (6a), becomes an ejection fluid with which exhaust gas (5c) and seawater (6b) were mixed in the back, and a ship (6) advances.

  Therefore, the principle is the same as that for operating a jet pump using the exhaust gas (5c) of a huge gas turbine. To explain the principle in an easy-to-understand manner, it is the same as a water rocket. The density is different between air and water when it is compressed and blown only by air and when it is blown through water. It is the same as the reaction becomes larger because 1 ton of water is 1.29 kilograms of air per cubic meter.

The counter-inverted gas turbine is a distributed injection type engine. The shaft blade (9) is provided with the shaft turbine (9b) via the shaft (9a), and the tube blade (10) is the tube body (10a). A pipe turbine (10b) is provided via And a casing (11) attaches a combustor (2) to the position between a pipe blade (10) and a pipe turbine (10b).

  The casing (11) is rotatably attached to the shaft (9a) via a bearing. A pipe body (10a) is attached to the shaft (9a) via a bearing so as to be rotatable. The shaft blade (9) and the tube blade (10) rotate in the opposite directions to send air to the combustor (2).

  Explaining the flow of air, the air entering the casing (11) enters the first stage blade (10), and the air leaving the tube (10) is the first stage shaft (9). The air that enters and exits the tube blade (10) is converted by the tube blade (10) into the circumferential velocity energy by the tube blade (10), and the axial blade (9) changes to the opposite circumferential velocity energy. The air that has exited enters the second stage of the blade (10) and changes the circumferential velocity energy to the opposite circumferential velocity energy. By repeating such operations, air is compressed.

  The air coming to the combustor (2) burns in the combustor (2) and enters the first stage pipe turbine (10b), and the exhaust gas (5c) gives rotation to the pipe turbine (10b), Directional velocity energy is applied to the first stage axial turbine (9b) to obtain rotational force. Further, the opposite circumferential velocity energy is applied to the second stage tube turbine (10b). By repeating such operations, the ejection pressure of the exhaust gas (5c) changes to rotational energy, and becomes a rotational force that compresses air between the tube blade (10) and the shaft blade (9).

  When flying with this counter-rotating gas turbine, both the shaft blade (9) and the tube blade (10) are made of moving blades, so that the atmosphere (5d) naturally comes from the compressor ( 1) Because it falls within, it does not become resistance. Conventionally, since a stationary blade has been used, air that has been given circumferential velocity energy by the moving blade enters the stationary blade, and the stationary blade is attached to exchange circumferential velocity energy with pressure energy. Therefore, even if wind pressure is applied from the front of the gas turbine, there is no change. However, the counter-rotating gas turbine does not require energy for rotating the engine. The exhaust gas (5c) emitted from the casing (11) is injected from a plurality of small diameter pipes (5) through the pipe (5a), so that a distributed injection engine is obtained.

Embodiments of the present invention will be described with reference to the drawings.
(A) FIG. 1 is a schematic diagram showing a plane of a small airplane (8) by a dotted line. The figure shows a two-stage centrifugal compressor (1), and the impeller of the compressor (1) has a diameter of φ600. The centrifugal compressor (1) rotates at 30,000 revolutions per minute, and the air compressed by centrifugal force enters the second stage rear wheel through the inducer. Furthermore, the compressed air pressure becomes 2 Pascals. The air flow is 200 cubic meters per minute.

  The compressed air is combusted in the combustor (2), the volume is increased by a factor of 5, and sent to the turbine (3) to rotate the two-stage axial turbine (3). The rotation of the turbine (3) obtains power for rotating the centrifugal compressor (1). If the exhaust gas (5c) produced at this time is directly injected as in the prior art, the thrust becomes 700 kg.

  As shown in the cross-sectional view of the blade (5b) in FIG. 2, the exhaust gas (5c) emitted from the turbine (3) is exhausted from the small diameter tube (5) of the blade (5b) through the tube (5a). (5c) is issued. At that time, the temperature of the exhaust gas (5c) exiting from the small diameter pipe (5) is lowered to 500 degrees, so the volume is about three times. However, the pressure of the exhaust gas (5c) that exits is 2 Pascals, and the air sucked at 200 cubic meters per minute is exhausted at 600 cubic meters per minute, and 7,000 small-diameter tubes (5) in φ1 of the small-diameter tube (5) 2 Pascal exhaust gas (5c) is ejected.

  FIG. 2 shows a schematic view of the exhaust gas (5c) coming out of the small diameter pipe (5). The wing (5b) has a trailing edge flap and a small diameter tube (5) on top of the trailing edge flap. The small diameter pipe (5) emits the exhaust gas (5c) compressed in the pipe (5a) from the outlet of the small diameter pipe (5), receives the force of the exhaust gas (5c), 5d) is a diagram that flows in the same direction. Conventionally, in the law of action and reaction, there is a thrust of about 700 km, assuming that the exhaust gas (5c) is injected near the speed of sound, but in a distributed injection engine, the small diameter pipe (5) is φ1, There are 7000 spouts and a thrust of about 14 tons.

  That is, this engine is not used as the thrust of the gas turbine, but utilizes the capacity of the compressor (1) of the gas turbine. A distributed injection engine can also be attached to the vertical and horizontal tails. In addition, the shape of the injection port is not round but can be long or rectangular.

  Moreover, since the small diameter pipe (5) of this method induces the atmosphere (5d) only in the upper part of the wing (5b), buoyancy is generated in the wing (5b). Therefore, if the front edge flap and the rear edge flap are lowered to increase buoyancy, the aircraft will take off at a speed of 100 km / h or less. On this wing (5b), there is Asuka who experimented on short-range take-off and landing with an FJR engine and four thrusts of 4,290 km. Since the airplane achieved a landing distance of 480 meters, the distributed injection engine is aimed at a shorter landing distance.

FIG. 3 is a schematic view of the wing (5b) using the afterburner (4) . The aircraft engine of a distributed injection type engine has a turbine (3) from a compressor (1) through a combustor (2). The exhaust gas (5c) is ejected from the small-diameter pipe (5) through an afterburner (4) attached to both wings and used as thrust.

  The thrust of the exhaust gas (5c) is 1000 degrees Celsius, and the exhaust gas (5c) exiting from the turbine (3) is cooled to about 500 degrees Celsius when exiting the small diameter pipe (5) through the pipe (5a). It will be about. And the volume was about half, so the thrust was inferior. In order to solve the problem, the exhaust gas (5c) is burned in the afterburner (4) to about 1700 degrees Celsius in the pipe (5a) before being ejected from the small diameter pipe (5) to increase the thrust. It is. Therefore, since the volume becomes seven times, it is necessary to double the size of the jet port of the small diameter pipe (5).

  However, if the injection port is doubled, the output is inferior when the afterburner (4) is not used. Therefore, when the afterburner (4) is not used, it is a movable type that can restrict the jet nozzle, and the same one as that generally called an acceleration nozzle is attached.

FIG. 5 is a schematic diagram of a ship (6) engine, which is a distributed injection engine of the present invention . The ship (6) is a ship with a displacement of 100 tons. The blades of the compressor (1) have a diameter of 600, and the centrifugal compressor (1) has two stages and increases the pressure to 2 Pascals. And there is a turbine (3) through a combustor (2). When passing through the turbine (3), the volume of about 1000 degrees Celsius increased 5 times, but when the exhaust gas (5c) was ejected from the small diameter pipe (5) attached to the stern Is in contact with seawater (6b), so it falls to about 50 degrees Celsius or less, and thermal expansion due to temperature disappears. However, since the sucked air remains, the pressure of 2 Pascals remains, and seawater (6b) is entrained by the injection of the 2 Pascals, and is used as a driving force.

  The plurality of small-diameter pipes (5) are φ30, and 100 small-diameter pipes (5) are arranged on the stern boat and injected in seawater (6b), which is indicated by solid arrows. Since the number of the small diameter pipes (5) is 100, the ship (6) is fully expanded. A cylinder (6a) surrounds the outlet of the exhaust gas (5c), and seawater (6b) is discharged by the jet of the exhaust gas (5c), as indicated by a dotted arrow. The propulsive force is a mixture of seawater (6b) and exhaust gas (5c). Since seawater (6b) is heavier than air, the exhaust gas (5c) is ejected from the small diameter pipe (5). The propulsive force is increased to 60 tons than the distributed injection engine used for the airplane (8).

  The discharged seawater (6b) has a negative pressure in the front of the cylinder (6a), and the seawater (6b) sucked from the front cylinder (6a) is indicated by a dotted line. And it becomes the jet fluid which exhaust gas (5c) and seawater (6b) mixed behind, and a ship (6) advances. Therefore, since it is mixed with seawater (6b), the exhaust gas (5c) is lowered to 50 degrees or less, and is the same as the intake volume. Therefore, the ejection amount of the exhaust gas (5c) is 200 cubic meters per minute.

  FIG. 6 is a schematic view of the jet boat (6c). The jet boat (6c) moves where the exhaust gas (5c) exits above the engine for the vessel (6) and sucks the seawater (6b) into the vessel (6). In this way, a propulsive force is produced, and the appearance is the same as that of a conventional jet boat.

  The compressor (1) of the gas turbine has one stage, the blade diameter is φ120, the maximum rotation is 80,000 rotations per minute, the injection port is φ50, the injection pressure is 1 Pascal, the thrust is 8 km is there. The conventional jet boat is a 2-meter long engine with a weight of 130 kg, an output of 48 horsepower, and an engine weighing 60 kg. However, since the weight of the gas turbine of the jet boat (6c) of the present invention is 5 kilograms, the weight of the jet boat (6c) is 75 kilograms because the weight can be reduced by 55 kilograms.

  And, the thrust of 8 km is 200 km by using a distributed injection engine. In the distributed injection type engine, the small diameter pipe (5) is set to φ10 and the seawater (6b) is used as a jet pump. Therefore, the seawater (6b) is heavier than air, and thus has a larger diameter than the airplane (8). And the small diameter pipe | tube (5) is made of 20 jet nozzles. Further, when the jet boat (6c) jumps off the surface of the water and floats in the air, the seawater (6b) is not replenished and the propulsive force is reduced.

The half sectional view of FIG. 7 is a counter- rotating gas turbine of a distributed injection type engine . The engine has a compressor (1), the compressor (1) is composed of a shaft blade (9) and a tube blade (10), and the turbine (3) is composed of a shaft turbine (9b) and a tube turbine (10b). ). The shaft (9a) includes a shaft blade (9) and a shaft turbine (9b), and the shaft blade (9) is made up of four stages of moving blades. The shaft turbine (9b) is a two-stage turbine. The shaft blade (9) and the shaft turbine (9b) are inclined in the same direction, and the shaft blade (9) has a gentle inclination, and the shaft turbine (9b) has a tighter gradient, so the exhaust gas (5c) Flows towards the rear axial turbine (9b).

  The shaft (9a) is provided with a tube blade (10) and a tube turbine (10b) through a bearing, and the tube body (10a) is provided on the outside, and the tube blade (10) is a five-stage moving blade. Thus, it rotates in the direction opposite to that of the shaft blade (9).

  The pipe turbine (10b) is made of a three-stage turbine and rotates in the reverse direction to the axial turbine (9b). The pipe blade (10) and the pipe turbine (10b) are inclined in the same direction, the inclination of the pipe blade (10) is gentle, and the inclination of the pipe turbine (10b) is tighter, so that the exhaust gas (5c) Flows towards the rear pipe turbine (10b).

  The tube blade (10) is provided with a tube turbine (10b) through a tube body (10a), and the tube body (10a) is substantially concave so as to avoid the combustor (2) attached to the casing (11). ) Is.

  Since the casing (11) supports the shaft (9a) at both ends, the casing (11) is shaped like a guide vane (11a). Since the guide vane (11a) is a counter-rotating gas turbine, circumferential velocity energy does not remain, so an object that is not inclined to either is attached.

  The casing (11) is rotatably attached to the shaft (9a) via a bearing. A pipe body (10a) is attached to the shaft (9a) via a bearing so as to be rotatable. Then, the shaft blade (9) and the tube blade (10) rotate in opposite directions to send air to the combustor (2).

  Therefore, since the shaft (9a) and the tube (10a) are rotatably attached, the cell motor cannot be used at the time of starting, so the pressure at which the compressed air is sent to the combustor (2) and the fuel is burned. Is used to rotate the turbine (3), and the compressor (1) is rotated by the rotation of the turbine (3). Therefore, it can be restarted when flying or when there is an inflow of air from the front.

  Explaining the flow of air, the air entering the casing (11) enters the first stage blade (10), and the air leaving the tube (10) is the first stage shaft (9). The air that enters and exits the tube blade (10) is converted by the tube blade (10) into the circumferential velocity energy by the tube blade (10), and the axial blade (9) changes to the opposite circumferential velocity energy. The air that has exited enters the second stage of the blade (10) and changes the circumferential velocity energy to the opposite circumferential velocity energy. The air is compressed by repeating such operations.

  The air that has reached the combustor (2) is combusted to 1000 degrees in the combustor (2), the volume is increased fivefold, enters the first stage pipe turbine (10b), and the exhaust gas (5c) is piped. A rotation is given to the turbine (10b). Then, the circumferential velocity energy is applied to the first stage shaft turbine (9b) to obtain a rotational force. Further, the opposite circumferential velocity energy is applied to the second stage tube turbine (10b). By repeating such an operation, the discharge pressure of the exhaust gas (5c) changes to rotational energy, resulting in a rotational force that compresses the air of the tube blade (10) and the shaft blade (9). And the surplus energy becomes the thrust.

  The exhaust gas (5c) emitted from the casing (11) is injected from a plurality of small diameter pipes (5) through the pipe (5a), so that a distributed injection engine is obtained. Further, when the counter-rotating gas turbine is in a ramjet state where air is sent from the front of the gas turbine engine, the resistance between the shaft blade (9) and the tube blade (10) is almost added. Because there is no, the moving blade does not become resistance like a ramjet.

  When the ramjet is used, the blades of the tube (10) and the shaft blade (9) of the compressor (1) and the blades of the tube turbine (10b) and the shaft turbine (9b) of the turbine (3) are used. Therefore, the air that has passed through the compressor (1) is slightly burned by the combustor (2). Then, the volume is increased and the blades of the turbine (3) are burned in the combustor (2) to such an extent that they do not resist, the temperature is increased to 1700 Celsius using the afterburner (4), and the volume is increased 7 times. Spray. Therefore, the ramjet according to the present invention can be operated with a single counter-rotating gas turbine even at a low speed or a high speed ramjet flight of 1600 km / h or more.

  The structure of this distributed injection engine is simple and lightweight, so it can be used for motor gliders. In addition, the compressor (1) has one stage of impeller and one Pascal can weigh 10 kilograms. If a distributed injection type engine is used, it can be used for a motor paraglider. In addition, a distributed injection engine can be used as a paraplane engine, and various designs can be imagined because there is no propeller part.

DESCRIPTION OF SYMBOLS 1 Compressor 2 Combustor 3 Turbine 4 Afterburner 5 Small diameter pipe 5a Pipe 5b Wing 5c Exhaust gas 5d Atmosphere 6 Ship 6a Tube 6b Seawater 6c Jet boat 7 Turbojet 8 Airplane 9 Shaft 9a Shaft 9b Shaft Turbine 10 Tube 10 10b Pipe turbine 11 Casing 11a Guide vane

Claims (1)

There is a turbine (3) through the combustor (2) from the compressor (1) of the marine engine,
The exhaust gas (5c) emitted from the turbine (3) is injected from a plurality of small diameter pipes (5) attached to the stern ,
The plurality of small-diameter pipes (5) extend to the full width of the ship (6),
A cylinder (6a) surrounds the spout of the small diameter pipe (5),
The distributed exhaust type engine characterized in that the injected exhaust gas (5c) and seawater (6b) are mixed in the cylinder (6a) to become an ejected fluid.

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