WO2023075537A1

WO2023075537A1 - Positive displacement turbine engine and positive displacement turbine engine system comprising same

Info

Publication number: WO2023075537A1
Application number: PCT/KR2022/016794
Authority: WO
Inventors: 김관현
Original assignee: 김관현
Priority date: 2021-11-01
Filing date: 2022-10-31
Publication date: 2023-05-04
Also published as: KR20230062987A; KR102545051B1

Abstract

The present invention relates to a positive displacement turbine engine and a positive displacement turbine engine system comprising same. The positive displacement turbine engine comprises: a rotary-type positive displacement compressor which performs the function of suctioning and discharging external air; a combustor in which fuel is mixed with air and combusted; and a rotary-type positive displacement turbine which obtains rotational power from the positive change in volume caused by the combustion in the combustor, wherein the positive displacement turbine is configured to produce a greater change in volume than the positive displacement compressor.

Description

Displacement type turbine engine and displacement type turbine engine system including the same

The present invention relates to an engine that obtains rotational power from internal energy expanded by burning air and a technology for the application system.

BACKGROUND ART In general, an engine is an engine that receives rotational power from internal energy that is sucked in, compressed, and then combusted and expanded in a defined system, and has been widely used as a power source throughout the industry.

Such an engine is divided into a volumetric type that transmits and receives power while seeking a volume change and a turbo type that transmits and receives power during an expansion process of internal energy without volume change according to a method of transmitting and receiving power from internal energy.

However, in the piston-type engine, which is the most widely used volumetric engine in the industry, the piston, which is structurally a power source, inevitably stops at the top dead center and bottom dead center every revolution, so the inertia according to the mass of the piston cannot be converted into energy. There are fatal flaws.

On the other hand, a rotor with triangular sides, which was devised to solve the fatal problem of not being able to continue inertia in the same volumetric upper piston method, rotates eccentrically along the epitoid curve in the shape of a cocoon, sucking in each side, The Wankel engine was created that transmits rotational power by sequentially performing 4 strokes of compression, expansion, and exhaust.

However, such a Wankel engine always has limitations in maintaining internal confidentiality due to loss due to eccentric rotation of the rotor and wear of the tip of the rotor, and the internal energy in the expansion section acts on the cross section of the rotor with the center of rotation of the rotor as a feather point. Since the reaction and the reaction act simultaneously, if the reaction is subtracted, the cross section acting purely as work is relatively small, resulting in a problem in energy efficiency, so it is currently discouraged.

On the other hand, in the axial jet engine, which is widely used in aircraft, etc., the rotating blades of the rotor and the stator blades, which are fixed, are arranged at the front and rear ends, so they do not interfere with each other and have inertia. While there is an advantage in high-speed rotation, the blades of the rotor and the blades of the stator arranged in front and back are always open to each other from the front and back, so when the internal energy expands between the blades and cannot overcome the load on the rotor, no work is done and the external There has been a problem in that it expands and is discarded and lost.

In order to solve this problem, the present applicant has applied for a volumetric turbine engine as Patent Application No. 10-2020-0038688 (2020.03.31, application).

However, in that application, in coupling the rotary type displacement type compressor and the displacement type turbine to different rotation shafts, a speed change means is provided between them so that the displacement type compressor rotates 2 to 3 times faster than the displacement type turbine. Even if the displacement type compressor and displacement type turbine have the same volume, the displacement type compressor supplies 2 to 3 times as much air to the displacement type turbine, mixes fuel with the air, and burns it to expand the displacement type turbine with internal energy. It was to provide a displacement type turbine engine that rotates and continuously rotates by forming a cycle of rotating the displacement type compressor with the rotational force.

However, as such, the displacement type compressor and the displacement type turbine have the same volume, and the displacement type compressor rotates 2 to 3 times faster than the displacement type turbine as a transmission means, so that the displacement type turbine has 2 to 3 times more internal volume than the displacement type turbine. Even if a positive amount of air is supplied, the internal energy obtained by mixing fuel with the supplied air and combusting it is 2 to 3 times larger than that of a positive displacement turbine according to Pascal's principle and gearwheel principle. As it acts as a force, the displacement type compressor has no choice but to perform the function of a turbine, not a compressor, unlike intended. There is a fatal error that is completely opposite to the above, so we want to correct it and apply for an improved technology.

One object of the present invention is to provide a displacement type turbine engine and a displacement type turbine engine system including the same that can solve the problem of loss due to the inability of the piston to continue the inertia according to the up and down reciprocation of each revolution in light of the conventional piston type engine. are doing

Another problem of the present invention is that the internal energy obtained from the conventional jet engine, which is roughly divided into a compressor and a turbine in a rotary method, structurally in the system does not work, and the internal energy corresponding to the load loaded on the turbine does not work, and the rotor and stator provided back and forth The internal energy to expand by replacing the conventional turbo type compressor and turbine with a rotary type displacement type compressor and a displacement type turbine, which is a completely new type displacement turbine engine that can solve the loss flowing between each blade of It is an object of the present invention to provide a volumetric turbine engine and a volumetric turbine engine system including the same, which are exhausted after completing their work by necessarily pushing the displacement turbine.

Displacement type turbine engine according to the present invention for achieving the above object is a rotary type displacement type compressor that performs a function of inhaling and discharging external air, a combustor mixing fuel with air for combustion, and combustion by the combustor. It includes a rotary type displacement turbine that obtains rotational power from the volume change that expands, and the displacement type turbine is configured to cause a larger volume change than the displacement type compressor.

Here, the combustor may be installed in at least one of a displacement type compressor and a displacement type turbine. The rotational shaft of the displacement type turbine is connected to the rotational shaft of the displacement type compressor by a speed changer, and the speed of the rotational shaft of the displacement type turbine can be set higher than the speed of the rotational shaft of the displacement type compressor by the speed changer.

The displacement type turbine engine system according to the present invention includes the displacement type turbine engine, a load connected to the displacement type compressor and rotating, and water vapor discharged by heat exchange with gas exhausted from the displacement type turbine by receiving water supplied from the outside. It includes a heat exchange means for supplying to the positive displacement turbine.

The positive displacement turbine engine according to the present invention can theoretically transfer all of the laboriously obtained internal energy into work (power) except for mechanical loss, so a new type of engine with high energy efficiency is expected.

The displacement type turbine engine system according to the present invention can be used to provide rotational power with high energy efficiency to various loads such as generators.

1 is a perspective view of a positive displacement turbine engine according to an embodiment of the present invention.

FIG. 2 is an exploded perspective view of FIG. 1 .

FIG. 3 is an example for explaining the principle of operation of the displacement type compressor and the displacement type turbine shown in FIG. 2, in which the displacement type compressor starts suction and expansion at the same time, and the corresponding displacement type turbine starts expansion and exhaust at the same time. It is a cross-sectional view showing the state.

FIG. 4 is a front cross-sectional view showing a state in which the displacement compressor of FIG. 3 completes suction and expansion at the same time, and the corresponding displacement turbine completes expansion and exhaust at the same time.

5 is a cross-sectional front view of another exemplary displacement compressor or displacement turbine.

6 is a perspective view showing an example in which a displacement type turbine is connected to a displacement type compressor as a gear shifting means.

FIG. 7 is an exploded perspective view of FIG. 6 .

8 is a configuration diagram of a positive displacement turbine engine system according to an embodiment of the present invention.

The present invention will be described in detail with reference to the accompanying drawings. Here, the same reference numerals are used for the same components, and repeated descriptions and detailed descriptions of well-known functions and configurations that may unnecessarily obscure the gist of the present invention are omitted. Embodiments of the present invention are provided to more completely explain the present invention to those skilled in the art. Accordingly, the shapes and sizes of elements in the drawings may be exaggerated for clarity.

1 is a perspective view of a positive displacement turbine engine according to an embodiment of the present invention. FIG. 2 is an exploded perspective view of FIG. 1 . FIG. 3 is an example for explaining the principle of operation of the displacement type compressor and the displacement type turbine shown in FIG. 2, in which the displacement type compressor starts suction and expansion at the same time, and the corresponding displacement type turbine starts expansion and exhaust at the same time. It is a cross-sectional view showing the state. FIG. 4 is a front cross-sectional view showing a state in which the displacement compressor of FIG. 3 completes suction and expansion at the same time, and the corresponding displacement turbine completes expansion and exhaust at the same time.

1 to 4, a displacement turbine engine according to an embodiment of the present invention includes a rotary displacement compressor 100, a combustor 200, and a rotary displacement turbine 300. do.

The positive displacement compressor 100 performs functions of sucking in and discharging external air. The combustor 200 mixes fuel with air and burns it. The combustor 200 may be installed on at least one of the displacement compressor 100 and the displacement turbine 300 . The combustor 200 may provide (expand) internal energy to the displacement turbine 300 by continuously combusting fuel by mixing fuel with air sucked into the displacement compressor 100 and/or the displacement turbine 300. .

The volumetric turbine 300 obtains rotational power through a volume change that is combusted and expanded by the combustor 200 . Here, the displacement type turbine 300 is configured to generate a larger volume change than the displacement type compressor 100 . Accordingly, the displacement type turbine 300 diffuses the combustion gas with a larger volume change than the displacement type compressor 100, so that rotational power can be obtained without reverse flow.

The displacement type turbine 300 passively rotates the displacement type compressor 100 provided on the same rotation shaft with modest rotational power, so that the displacement type compressor 100 and the displacement type turbine 300 form a rotation cycle that is repeated with each other. Rotational power can be obtained continuously.

As described above, the displacement type turbine engine of the present invention can theoretically transfer all of the laboriously obtained internal energy into work (power) except for mechanical loss, and thus can have high energy efficiency.

On the other hand, the positive displacement compressor 100 includes a casing 110, a main rotor 120, blades 130, satellite rotors 140, and a suction port 150. ), and discharge ports 160.

The casing 110 has a cylindrical inner surface therein. The main rotor 120 has a cylindrical cross section and is disposed in the center of the casing 110 . The main rotor 120 is coupled to the rotating shaft 101 to perform a rotational motion. The main rotor 120 may rotate only through initial ignition through the rotation shaft 101 . The main rotor 120 forms an internal passage 111 between the outer diameter portion and the inner diameter portion of the casing 110 . The internal passage 111 may be formed in a donut shape having a uniform width in a radial direction.

The blades 130 are arranged at regular intervals along the outer diameter of the main rotor 120 . The blades 130 orbitally move according to the rotation of the main rotor 120 while maintaining airtightness with the inner diameter of the casing 110 while protruding from the outer diameter of the main rotor 120 . As the main rotor 120 rotates, the blades 130 simultaneously decrease and increase in volume independently for each

closed section

111a, 111b, and 111c.

For example, the blades 130 may be provided in three pieces and arranged at intervals of 120 degrees on the outer diameter of the main rotor 120 . As another example, two or more blades 130 may be provided and arranged at equal intervals on the outer diameter of the main rotor 120 .

The satellite rotors 140 rotate the internal flow path 111 of the casing 110 along the rotational direction of the main rotor 120 at equal intervals in the same number of

closed sections

111a, 111b, and 111c as the number of blades 130. partitioned into The satellite rotors 140 are partially accommodated in the satellite rotor chambers 112 formed on the inner circumference of the casing 110 and are supported so as to be able to rotate while maintaining airtightness.

A portion of the satellite rotor 140 excluding the passage groove 141 may be formed in a cylindrical shape. Each passage groove 141 may be formed on an outer circumference of the corresponding satellite rotor 140 . The satellite rotors 140 pass the blades 130 through each of the passage grooves 141 while rotating by the linkage mechanism 170 when the blades 130 orbit. The passage groove 141 protrudes into the internal passage 111 to avoid collision or interference with the orbiting blade 130 .

The linkage mechanism 170 may include satellite rotor gears 171 and a main rotor gear 172 . The satellite rotor gears 171 are formed on outer diameter portions of the satellite rotors 140, respectively. The main rotor gear 172 is formed on the outer diameter of the main rotor 120 with the same number of teeth as the total number of teeth of the satellite rotor gears 171, and is engaged with the satellite rotor gears 171 to rotate the blades 130. The satellite rotors 140 are rotated accordingly. Meanwhile, the satellite rotor gear 171 and the main rotor gear 172, which are linkage mechanisms 170, may be provided on one end surface.

The suction ports 150 correspond to the starting points of the

closed sections

111a, 111b, and 111c and are formed in the casing 110 through the

closed sections

111a, 111b, and 111c. The suction ports 150 allow air to be sucked into the

closed sections

111a, 111b, and 111c, respectively.

The discharge ports 160 correspond to the end points of the

closed sections

111a, 111b, and 111c and are formed in the casing 110 through the

closed sections

111a, 111b, and 111c. The outlets 160 allow air to be discharged from the

closed sections

111a, 111b, and 111c, respectively. The discharge port 160 may form a pair with the suction port 150 and pass through the casing 110 on both sides of the corresponding satellite rotor 140 .

Displacement turbine 300 may also be configured similarly to displacement compressor 100 . Therefore, the displacement turbine 300 includes the casing 110 constituting the displacement compressor 100, the main rotor 120, the blades 130, the satellite rotors 140, and the inlet 150. s, and discharge ports (exhaust ports, 160). The main rotor 120 of the displacement type turbine 300 may be coupled to the same rotating shaft 101 as the main rotor 120 of the displacement type compressor 100 .

However, the displacement type turbine 300 is configured to have an internal flow path 111 having a large volume by being longer in the axial direction and/or radial direction than the internal flow path 111 of the displacement type compressor 100, It can cause a larger volume change than the compressor 100. In addition, each discharge port 160 provided in the displacement type compressor 100 is connected to each suction port 150 provided in the displacement type turbine 300 through a closed passage.

For example, as shown in FIG. 3 , the combustor 200 includes the front end surface (or front end) of the blade 130 protruding from the main rotor 120 of the displacement type compressor 100 and the displacement type turbine 300. It may be installed between the rear end surface (or rear end) of the blade 130 protruding from the main rotor 120 of the.

The combustor 200 may be combusted on the front surface of the blade 130 of the displacement type compressor 100 through the main rotor 120 of the displacement type compressor 100 . Although not shown, the combustor 200 may be combusted at the rear end surface of the blade 130 of the displacement type turbine 300 through the main rotor 120 of the displacement type turbine 300 . In addition, the combustor 200 performs primary combustion on the front surface of the blades 130 of the displacement type compressor 100 through the main rotor 120 of the displacement type compressor 100, and then the main rotor of the displacement type turbine 300 Through 120, secondary combustion may be performed at the rear end of the blade 130 of the positive displacement turbine 300.

The displacement compressor 100 and displacement turbine 300 may act as follows.

First, in the positive displacement compressor 100, when the main rotor 120 rotates in the direction for air intake by rotational power in the inner space of the casing 110, the blades 130 rotate according to the rotation of the main rotor 120. do orbital exercise At the same time, the satellite rotors 140 rotate in a direction opposite to the rotational direction of the main rotor 120 by the action between the satellite rotor gears 171 and the casing gear 172 .

At this time, the blades 130 sequentially pass through the satellite rotors 140 through the respective passage grooves 141 of the satellite rotors 140 according to their own orbital motion and the rotational motion of the satellite rotors 140 while passing through three closed sections. s (111a, 111b, 111c) moves continuously.

In this process, the volume of the front end of the blade 130 is narrowed and the volume of the rear end of the blade 130 is widened at each closed section (111a, 111b, 111c), so that air is sucked and discharged independently. The air sucked in by the compressor 100 goes through the inlet 150 provided in the displacement type turbine 300 and exits through the discharge port (exhaust port 160) of the displacement type turbine 300.

Here, as shown in FIG. 3, when each blade 130 of the positive displacement compressor 100 is located at the starting point of suction, each rear end of each blade 130 moves from the already passed

closed sections

111a, 111b, and 111c. Each suction is completed, and at the same time, each front end passes through each closed section (111a, 111b, 111c) and completes expansion (see FIG. 4), and enters each new closed section (111a, 111b, 111c) to achieve new suction and expansion is in the starting position.

On the other hand, the volumetric turbine 300 completes the expansion of the rear end of each blade 130 in the preceding

closed sections

111a, 111b, and 111c, and at the same time the front end finishes each exhaust, and in the new

closed sections

111a, 111b, and 111c. It is in a position to start exhausting at the same time as expansion, and in each closed section (111a, 111b, 111c) between each blade 130 of the displacement type compressor 100 and the blade 130 of the displacement type turbine 300, the preceding blades (130) is full of uncombusted air that each inhaled.

When fuel is mixed with the combustor 200 to the inhaled air and combusted, the internal energy is the same on the front surface of the blade 130 of the displacement type compressor 100 and the rear surface of the blade 130 of the displacement type turbine 300. The pressure simultaneously acts. As the cross-sectional area of the blade 130 provided in the displacement turbine 300 is large or the volume change is large, the displacement turbine 300 receives relatively more internal energy, The turbine 300 rotates and the positive displacement compressor 100 passively rotates accordingly.

At this time, the displacement compressor 100 expands and simultaneously performs suction on the other side, and the displacement turbine 300 expands and simultaneously pushes and exhausts the combustion gas that has completed work on the other side to the discharge port (exhaust port 160) and exhausts it. The cycle of is repeated to achieve continuous rotation.

For reference, as shown in FIG. 4 , the displacement compressor 100 completes suction and expansion simultaneously, and the corresponding displacement turbine 300 completes expansion and exhaust simultaneously.

As shown in FIG. 5, the positive displacement compressor 100' includes a casing 110', a main rotor 120', blades 130', satellite rotors 140', and a suction port ( 150'), and discharge ports 160'.

The casing 110' has a cylindrical inner surface therein. The main rotor 120' has a cylindrical cross section and is disposed centrally in the casing 110'. The main rotor 120' forms an internal passage 111' between the outer diameter portion and the inner diameter portion of the casing 110'. The internal passage 111' may be formed in a donut shape having a uniform width in a radial direction.

The blades 130' each protrude from the inner diameter of the casing 110' to form the inner passage 111' of the casing 110' along the rotational direction of the main rotor 120' and form a plurality of closed sections 111a'. , 111b', 111c') at equal intervals. The protruding ends of the blades 130' are formed to maintain airtightness with the outer diameter of the main rotor 120'.

The satellite rotors 140' are arranged at equal intervals along the outer diameter of the main rotor 120' with the same number as the closed sections 111a', 111b', and 111c'. The satellite rotors 140' are partially accommodated in the satellite rotor chambers 121' formed on the outer diameter of the main rotor 120', and are supported to rotate while maintaining airtightness with the inner diameter of the casing 110'. In addition, it orbits according to the rotation of the main rotor 120 '. The satellite rotor 140' may be formed in a cylindrical shape except for the passage groove 141' for avoiding collision or interference with the blades 130'.

The linkage mechanism 170' may include satellite rotor gears 171' and a casing gear 172'. The satellite rotor gears 171' are formed on outer diameter portions of the satellite rotors 140', respectively. The casing gear 172' is formed on the inner diameter of the casing 110' with the same number of teeth as the total number of teeth of the satellite rotor gears 171', and is engaged with the satellite rotor gears 171' to the satellite rotor 140'. ) rotates the satellite rotors 140'.

The intake ports 150' correspond to the starting points of the closed sections 111a', 111b', and 111c' and are formed in the casing 110' through the closed sections 111a', 111b', and 111c'. The suction ports 150' allow air to be sucked into the closed sections 111a', 111b', and 111c', respectively.

The outlets 160' correspond to the end points of the closed sections 111a', 111b', and 111c' and are formed in the casing 110' through the closed sections 111a', 111b', and 111c'. The outlets 160' allow air to be discharged from the closed sections 111a', 111b', and 111c', respectively. The discharge port 160' may form a pair with the suction port 150' and pass through the casing 110' on both sides of the corresponding blade 130'.

Meanwhile, the displacement turbine 300 may also be configured similarly to the displacement compressor 100' of the present example. The displacement type compressor 100' and the displacement turbine of this example may act in the same way as the displacement type compressor 100 and displacement type turbine 300 of the above-described example.

6 is a perspective view showing an example in which a displacement type turbine is connected to a displacement type compressor as a gear shifting means. FIG. 7 is an exploded perspective view of FIG. 6 .

Referring to FIGS. 6 and 7 , the rotational shaft 301 of the displacement type turbine 300 may be connected to the rotational shaft 101 of the displacement type compressor 100 by means of a shift unit 400 . Here, the rotating shaft speed of the displacement type turbine 300 is set faster than the rotating shaft speed of the displacement type compressor 100 by the transmission unit 400 .

In this way, when the displacement type turbine 300 has a rotational shaft speed faster than the displacement type compressor 100 by the transmission means 400, the internal flow path having the same volume as the internal flow path 111 of the displacement type compressor 100 ( 111), it is possible to generate a larger volume change than the positive displacement compressor (100). In addition, when the displacement type turbine 300 has an internal flow path 111 with a larger volume than the internal flow path 111 of the displacement type compressor 100, the rotational shaft is faster than the displacement type compressor 100 by the speed change means 400. It can cause a larger volume change with velocity.

The shift unit 400 may be configured as a planetary gear train. For example, the transmission unit 400 may include an internal gear 410, a planet gear 420, a carrier 430, and a sun gear 440. .

The internal gear 410 is connected to the rotary shaft 101 of the positive displacement compressor 100 . The internal gear 410 is input from the main rotor 120 of the displacement type compressor 100 by binding the central portion to the center of the main rotor 120 of the displacement type compressor 100 through the rotating shaft 101 by a spline method or the like. rotational power can be transmitted.

The planetary gears 420 are arranged around the internal gear 410 in a state of meshing with the internal gear 410 , respectively. The planetary gears 420 may be arranged at regular intervals around the internal gear 410 . The planetary gears 420 are illustrated as three, but are not limited thereto.

The carrier 430 supports the planetary gears 420 so as to be able to rotate each other. In addition, the carrier 430 supports the planetary gears 420 to revolve around the internal gear 410 while maintaining a distance from each other.

The sun gear 440 is connected to the rotating shaft 301 of the positive displacement turbine 300 in a state of meshing with the planetary gears 420 at the center of the internal gear 410 . The center of the sun gear 440 is coupled to the center of the main rotor 120 of the displacement type turbine 300 by a spline method, etc., so that the shifted rotational power can be output to the main rotor 120 of the displacement type turbine 300. there is.

When the positive displacement compressor 100 and the displacement turbine 300 each have three closed

sections

111a, 111b, and 111c, the sun gear 440 and the internal gear 410 have a gear ratio of 3:1. It can be, but is not limited to the exemplified bar.

According to the shift unit 400, as the main rotor 120 of the displacement type compressor 100 rotates, the internal gear 410 rotates in the same direction as the rotation direction of the main rotor 120. Accordingly, the planetary gears 420 rotate in the same direction as the rotational direction of the main rotor 120 while being supported by the carrier 430 . Then, the sun gear 440 is accelerated and rotated in the opposite direction to the rotational direction of the main rotor 120 at a speed change ratio, thereby moving the main rotor 120 of the displacement type turbine 300 to the main rotor of the displacement type compressor 100 ( 120) and rotate in the opposite direction.

Here, in the displacement type turbine 300, the suction ports 150 are formed in the casing 110 to correspond to the starting points of the

closed sections

111a, 111b, and 111c based on the rotation direction of the displacement type compressor 100. It is connected to the discharge port 160, and the discharge port 160 is formed in the casing 110 to correspond to each end point of the

closed sections

111a, 111b, and 111c to exhaust.

In this way, since the main rotor 120 of the displacement type turbine 300 is accelerated and rotates faster than the main rotor 120 of the displacement type compressor 100 at the speed ratio of the transmission unit 400, the displacement type turbine 300 It can cause a larger volume change than the type compressor (100).

Referring to FIG. 8 , a displacement turbine engine system 10 according to an embodiment of the present invention includes the aforementioned displacement turbine engine, a load 500, and a heat exchanging means 600.

The displacement type turbine engine is illustrated as having the configuration shown in FIG. 1, but may also be configured with the configuration shown in FIG. 6. The displacement type compressor 100 may mount an intake duct 700 on a side of the intake 150 . The intake duct 700 sucks in air through the intake port 710 and delivers it to the intake port 150 of the displacement type compressor 100 . The positive displacement compressor 100 receives fuel from the combustor 200 and allows it to be mixed into intake air.

The displacement type turbine 300 may be equipped with an exhaust duct 800 on the discharge port 160 side. The exhaust duct 800 receives the gas discharged from the discharge port 160 of the displacement type turbine 300 and discharges it to the outside through the exhaust port 810 .

The load machine 500 is connected to the displacement type compressor 100 through a rotating shaft 101 to perform a rotational motion. The load machine 500 may correspond to various loads that require rotational motion, such as a generator generating electricity through rotational motion.

The heat exchanging means 600 receives water supplied from the outside, heat-exchanges it with gas exhausted from the displacement type turbine 300, and supplies the discharged water vapor into the displacement type turbine 300. The water vapor supplied into the displacement turbine 300 is heated again as combustion gas together with air within the displacement turbine 300 to amplify internal energy, thereby further increasing the power transmission efficiency of the displacement turbine 300. .

The heat exchange means 600 may include a heat exchange unit 610, a supply pipe 620, a discharge pipe 630, and a pump 640. The heat exchanger 610 is disposed in the exhaust duct 800 and changes the phase of the water flowing through the internal passage to water vapor by exchanging heat with the gas exhausted from the positive displacement turbine 300 . The heat exchange unit 610 may be configured in various configurations in a category capable of phase-changing water into steam by heat-exchanging water.

The supply pipe 620 supplies water from an external water supply source to the heat exchange unit 610 . The discharge pipe 630 discharges water vapor phase-changed in the heat exchanger 610 into the positive displacement turbine 300 . The pump 640 is installed in the supply pipe 620 and pumps water to the heat exchanger 610 and pumps water vapor from the heat exchanger 610 through the discharge pipe 630 into the positive displacement turbine 300.

As such, the displacement type turbine engine system 10 according to the present embodiment can be utilized to provide rotational power with high energy efficiency to various loads 500 such as generators.

To elaborate on the displacement type turbine engine according to the present embodiment, the displacement type turbine engine includes a rotary type displacement type compressor having a suction port and a discharge port on one rotating shaft, and a rotary type having a suction port and a discharge port (exhaust port) corresponding thereto. It is configured by combining the displacement type turbine of the method, and the discharge port of the displacement type compressor is configured to be coupled with the inlet of the displacement type turbine as a closed passage, and a combustor is provided at an appropriate part between the displacement type compressor and the displacement type turbine. .

At this time, the displacement type turbine is configured to have a relatively large volume change compared to the displacement type compressor, so that the internal energy combusted and expanded between the displacement type compressor and the displacement type turbine is always transferred between the displacement type compressor and the displacement type turbine simultaneously on both sides. Although it acts with the same pressure, the volumetric turbine receives a large force corresponding to the large volume change due to the large cross-sectional area to which the volumetric turbine is relatively acted, and the volumetric turbine performs a rotational circular motion, and the volumetric turbine is constrained on the same axis of rotation. The compressor passively performs rotational circular motion, and the displacement type turbine and the displacement type compressor repeat one cycle and continuously rotate circular motion.

In addition, the displacement type compressor and the displacement type turbine may be provided on one rotation axis, or the rotation axis is different from each other and a speed change means is provided between them so that the displacement type turbine rotates at a relatively high speed compared to the displacement type compressor. Even if it has an internal volume, the displacement turbine always has a relatively larger volume change, so the internal energy burned between the displacement compressor and the displacement turbine is always relatively greater in the displacement turbine according to the gearwheel principle. As a result, the volumetric turbine rotates in a circular motion, and at the same time, the combustion gas that has completed the work is exhausted to atmospheric pressure through the discharge port that is always open.

Here, in combining the displacement type compressor and the displacement type turbine, as a method to increase the volume change of the displacement type turbine relatively, either increase the displacement type turbine in the circumferential direction or increase the horizontal length compared to the displacement type compressor, or There are several methods, such as increasing the volume change by increasing the rotational speed of the displacement type turbine compared to the displacement type compressor using .

In addition, the positive displacement turbine engine according to the present invention configured as described above has several peculiarities that have not been seen so far as follows.

One of them is the displacement type compressor provided in the displacement type turbine engine of the present invention, as the rotor rotates, the rear end of the protruding blade expands the volume and performs a function of sucking in external air, but at the same time, the front end divides the compression function, It performs the function of mixing and burning fuel with already inhaled air and pushing the internal energy that expands to the inlet of the volumetric turbine to expand in the volumetric turbine.

The other is the function of the volumetric turbine. The turbine protrudes from the rotor to the internal volume, and the rear end of the blade, which actually seeks a volume change, is pushed under the action of internal energy to expand the volume and rotates the rotor. At the same time, the front end It simultaneously performs the function of exhausting the exhaust gas left after the preceding blade has already finished its work by pushing it through the open discharge port.

Another is that since the displacement type compressor and the displacement type turbine are constrained to one shaft and rotate together, the distance between the blades of the displacement type compressor and the blades of the displacement type turbine is always constant and does not change. Even if the energy acts on the displacement type compressor and the displacement type turbine at the same time, the internal energy expands while pushing the displacement type turbine side blade because the cross-sectional area of the displacement type turbine side blade is relatively large among both blades directly affected by the internal energy. It is exhausted only after work is completed, and the displacement type turbine rotates under the action of internal energy, and the displacement type compressor, which is constrained to the same axis, also passively rotates and cycles to continuously rotate. A turbine engine is provided, which is also a strange rotation principle that has never been seen before.

In addition, the internal energy generated by combustion between the displacement type compressor and the displacement type turbine cannot be exhausted to the outside without completing the task of pushing the displacement type turbine while expanding.

Here, the work done by the displacement type turbine engine of the present invention in one rotation is that when the displacement type turbine is at the starting point of expansion, the internal energy is originally confined in the internal volume of the displacement type compressor, but when the expansion is completed, it is converted to the internal volume of the displacement type turbine. Therefore, the amount of work is the amount obtained by subtracting the internal volume of the positive displacement turbine from the internal volume of the positive displacement turbine, which is also a strange rotation principle that has never been seen before.

The present invention has been described with reference to an embodiment shown in the accompanying drawings, but this is only exemplary, and those skilled in the art will understand that various modifications and equivalent other embodiments are possible therefrom. You will be able to. Therefore, the true protection scope of the present invention should be defined only by the appended claims.

Claims

A rotary volume type compressor that sucks in and discharges external air, a combustor that mixes and burns fuel with air, and a rotary volume type that obtains rotational power from the volume change that is combusted and expanded by the combustor. In the volumetric turbine engine comprising a turbine,

The displacement type turbine engine, characterized in that the displacement type turbine is configured to cause a larger volume change than the displacement type compressor.
According to claim 1,

The combustor is a displacement type turbine engine, characterized in that installed in at least one of the displacement type compressor and the displacement type turbine.
According to claim 1,

The rotation shaft of the displacement type turbine is connected to the rotation shaft of the displacement type compressor by a gear shifting means,

The rotational shaft speed of the displacement type turbine is higher than the rotational shaft speed of the displacement type compressor by the transmission means.
The displacement type turbine engine according to any one of claims 1 to 3;

a load that is connected to the positive displacement compressor and rotates; and

a heat exchanging means for receiving water supplied from the outside and exchanging heat with gas exhausted from the displacement type turbine to supply water vapor discharged to the displacement type turbine;

Displacement type turbine engine system comprising a.