WO2020204568A1

WO2020204568A1 - Positive displacement turbine engine

Info

Publication number: WO2020204568A1
Application number: PCT/KR2020/004391
Authority: WO
Inventors: 김관현
Original assignee: 김관현
Priority date: 2019-04-01
Filing date: 2020-03-31
Publication date: 2020-10-08

Abstract

The present invention relates to a positive displacement turbine engine. The positive displacement turbine engine comprises: a rotary type positive displacement compressor that suctions air by means of rotational power to increase pressure through volume reduction; a rotary type positive displacement turbine that obtains rotational power by burning fuel mixed with air; and a transmission that accelerates the rotational power input from an output shaft of the rotary type positive displacement turbine and outputs same to an input shaft of the rotary type positive displacement compressor.

Description

Positive displacement turbine engine

The present invention relates to an engine, that is, a prime mover, which compresses air and then burns it to obtain rotational power from the expanding internal energy.

In general, an engine is an engine that receives and compresses air in a predetermined system, then receives rotational power from internal energy that expands by combustion, and has been widely used as a power source throughout the industry.

Such engines are divided into a volume type that receives power while attempting a volume change according to a method of receiving power from internal energy, and a turbo type that receives power during expansion of internal energy without volume change.

However, in the piston type engine, which is the most widely located in the industry as a positive displacement type, structurally, the piston as a power source inevitably stops at the top and bottom dead centers at every rotation, so the inertia according to the mass of the piston cannot be transferred to energy. There are always fatal disadvantages.

On the other hand, a rotor with triangular sides, devised to solve the fatal problem of not connecting inertia in the above piston method with the same volume type, rotates eccentrically along the epitoid curved surface of the cocoon shape and sucks each side. A Bankel engine was created that receives rotational power by sequentially performing four strokes of compression, expansion and exhaust.

However, such a Bankel engine has limitations in maintaining internal airtightness due to the loss due to the eccentric rotation of the rotor and wear of the end of the rotor, and the internal energy in the expansion section acts on the cross section of the rotor as the flag point of the rotation center of the rotor. If the reaction and reaction work at the same time, and if the reaction is deducted, the section that acts purely as work is relatively small, resulting in energy efficiency, which is currently being rejected.

On the other hand, in the axial jet engine, which is widely used in aircraft, the blade of the rotor and the blade of the stator, which is a rotating chain, are arranged at the front and rear ends of each other, so that there is no interference with each other, so it has inertia. While there is an advantage in high-speed rotation, the blades of the rotor and the blades of the stator arranged in the front and rear are always open to each other, so if 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 lost.

An object of the present invention is to provide a positive displacement turbine engine capable of solving the problem of loss due to the inertia due to the vertical reciprocating movement of the piston at every rotation in light of the conventional piston type engine.

Another object of the present invention is that the internal energy obtained from the conventional jet engine, which is largely divided into a compressor and a turbine in a rotary system, is structurally in the system. It is to provide a completely new type of displacement turbine engine that can eliminate the losses flowing between the blades of the machine.

The positive displacement turbine engine according to the present invention for achieving the above object is a rotary positive displacement compressor that increases pressure through volume reduction by inhaling air by rotational power, and rotational power by burning fuel mixed with air. It includes a rotary-type positive displacement turbine to obtain the output, and a transmission for accelerating rotational power input from the output shaft of the positive displacement turbine and outputting it to the input shaft of the positive displacement compressor.

In view of the configuration of the conventional jet engine, which is roughly divided into compressor, combustor and turbine, the positive displacement turbine engine moves the compressor and the turbine at different shafts to make the central rotational circular motion while changing the air volume within the system. A positive displacement compressor that sucks and compresses the compressed air and a positive displacement turbine capable of receiving and receiving rotational power while changing the volume by internal energy that expands by burning by adding fuel in the system specified in the compressed air. It is completed by providing a transmission between the positive displacement compressor and the positive displacement turbine that can increase the compression ratio by mechanically accelerating the rotational speed of the positive displacement compressor with the rotational power of the positive displacement turbine.

That is, the positive displacement turbine engine of the present invention primarily sucks and compresses external air with a positive displacement compressor, and secondarily sends the compressed air to the combustion chamber and adds fuel such as gasoline to the compressed air therein and burns it, Thirdly, the internal energy to be expanded causes the positive displacement turbine engine to rotate, and fourthly, the rotary power is accelerated by increasing the rotational speed with the transmission, and fifthly, the positive displacement compressor is rotated at the accelerated transmission. Eventually, the positive displacement turbine receives the flow rate corresponding to the transmission ratio from the positive displacement compressor, and receives compressed air at a compression ratio corresponding to the transmission ratio every unit time and burns it to perform a cycle that rotates the positive displacement turbine. It can be viewed as composed of.

Therefore, even if the positive displacement compressor and the positive displacement turbine have the same internal volume, the positive displacement turbine is connected to one system if the positive displacement turbine rotates the positive displacement compressor by shifting the rotational power received by the positive displacement turbine to triple speed through the above transmission. By supplying 3 times more flow rate to the air, it is possible to supply air with a compression ratio of 3:1 every unit time. By adding fuel to the compressed air and burning it, the expansion force of internal energy is relatively increased as the compression ratio is increased. Eventually, it provides a positive displacement turbine engine that can increase the efficiency of the engine.

In the configuration of the positive displacement turbine engine of the present invention, the positive displacement compressor suctions and compresses external air, and the positive displacement turbine receives and discharges rotational power from internal energy that expands by burning the compressed air above. The role played by each other is different, but structurally, it may be composed of a rotary type fluid machine having the same structure.

In addition, the positive displacement compressor and the positive displacement turbine used in the present invention are not limited to the volume change method, and any method is sufficient as long as a rotary method in which the rotor sucks and compresses fluid while changing the volume during the rotational circular motion process.

The positive displacement turbine engine according to the present invention uses only a simple transmission without increasing the internal volume of the positive displacement compressor, and the positive displacement turbine continuously receives compressed air at a rate corresponding to the transmission ratio for each revolution and expands by combustion, The internal energy to expand is configured to push the displacement turbine in the rotational direction within the closed system and then exhaust it to the outside.

Therefore, the positive displacement turbine engine of the present invention can theoretically receive all of the work (power) from the hard-earned internal energy except for mechanical losses, and a new type of engine having high energy efficiency is expected.

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

2 is a side cross-sectional view of the positive displacement turbine engine shown in FIG. 1.

3 is an exploded perspective view of FIG. 2.

4 is a front cross-sectional view of the positive displacement compressor in FIG. 3.

5 is a front cross-sectional view for explaining the operation of the positive displacement compressor shown in FIG. 4.

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

7 is a side cross-sectional view of FIG. 6.

8 is an exploded perspective view of FIG. 6.

9 is a front cross-sectional view of the positive displacement compressor in FIG. 6.

10 is a front cross-sectional view for explaining the operation of the positive displacement compressor shown in FIG.

The present invention will be described in detail with reference to the accompanying drawings as follows. Here, the same reference numerals are used for the same configuration, and repeated descriptions and detailed descriptions of known functions and configurations that may unnecessarily obscure the subject matter of the present invention will be omitted. Embodiments of the present invention are provided in order to more completely describe the present invention to those of ordinary skill in the art. Accordingly, the shapes and sizes of elements in the drawings may be exaggerated for clearer explanation.

As shown in FIG. 1, the positive displacement turbine engine 1000 according to the present invention includes a positive displacement compressor 1100 and a positive displacement turbine 1200 for rotating circular motions with different rotation axes on the left and right sides of the drawing. Is provided, and a transmission 1300 and a combustion chamber are provided therebetween.

That is, the positive displacement compressor 1100 configured as above primarily inhales and compresses air by force while rotating, and secondaryly sends the compressed air to the combustion chamber through a closed section and sends the compressed air to fuel such as gasoline. In addition, the internal energy to be expanded due to combustion is forced to rotate by pushing the displacement turbine 1200, and fourthly, the rotational power of the turbine is accelerated by increasing the rotational speed to the transmission 1300. And, by rotating the positive displacement compressor 1100 at the accelerated speed fifthly, in the end, when the displacement turbine 1200 rotates once, the displacement compressor 1100 passes through the transmission 1300 to the transmission ratio. As it rotates at a corresponding high speed, the positive displacement turbine 1200 receives a large flow rate corresponding to the transmission ratio from the positive displacement compressor 1100 every unit time, and eventually receives compressed air corresponding to the transmission ratio. It is composed of one system that performs a cycle that rotates the positive displacement turbine 1200 by combustion.

Here, the positive displacement compressor 1100 and the positive displacement turbine 1200 provided in the present invention as above perform a compressor function of forcibly inhaling air and compressing it, and adding fuel to the above compressed air to combust There is no problem in the implementation of the present invention even though the components are the same but the functions performed by each other by performing the function as a turbine that is forcibly pushed from the internal energy are the same.

In addition, the positive displacement compressor 1100 and the positive displacement turbine 1200, which are constituent elements of the present invention, stick to the volume change method, even for the vane type fluid machine that changes the volume while the vane changes as the rotor rotates. It is not enough if it is a volumetric type with a rotary method.

In addition, in the positive displacement turbine engine 1000 according to the present invention, the positive displacement compressor 1100 and the positive displacement turbine 1200 may be implemented in various aspects according to a volume change method and a reaction blocking method within a predetermined system, as well as a combustion chamber. It goes without saying that it can be implemented in various ways depending on the configuration and combustion method of the device, means for preventing backflow of internal energy, and a transmission.

That is, the positive displacement turbine engine 1000 according to the first embodiment of the present invention includes a rotary positive displacement compressor 1100, a rotary positive displacement turbine 1200, and a transmission 1300.

The rotary type positive displacement compressor 1100 sucks air by rotational power and increases the pressure through volume reduction. The rotary type positive displacement turbine 1200 obtains rotational power by burning fuel mixed with air. The transmission 1300 accelerates rotational power input from the output shaft of the positive displacement turbine 1200 and outputs it to the input shaft of the positive displacement compressor 1100.

As described above, according to the positive displacement turbine engine 1000 according to the first embodiment, the positive displacement compressor 1100 is accelerated and driven by the transmission 1300 rather than the positive displacement turbine 1200. Therefore, the positive displacement turbine 1200 continuously receives compressed air from the positive displacement compressor 1100 at a rate corresponding to the transmission ratio of the transmission 1300 at each rotation and burns it, so it is more efficient than driving each other at a constant speed. Can be further increased.

2 is a side cross-sectional view of the positive displacement turbine engine shown in FIG. 1. 3 is an exploded perspective view of FIG. 2. 4 is a front cross-sectional view of the positive displacement compressor in FIG. 3. 5 is a front cross-sectional view for explaining the operation of the positive displacement compressor shown in FIG. 4.

2 to 5, for example, the positive displacement compressor 1100 includes a casing 110, a main rotor 120, a blade 130, a satellite rotor 140, and a suction port. It may include 150s, and discharge ports 160.

For example, the positive displacement compressor 1100 includes a casing 110, a main rotor 120, a blade 130, a satellite rotor 140, and a suction port 150. ), and discharge ports 160.

The casing 110 has a cylindrical inner space. The main rotor 120 is disposed in the center of the casing 110 and rotates by rotational power. The main rotor 120 is disposed coaxially with the casing 110. The main rotor 120 may rotate by receiving the rotational power of an external driving source, that is, the positive displacement turbine 1200 through a rotation shaft 120a coaxially coupled to the center.

The main rotor 120 forms an inner flow path 111 between the outer diameter portion and the inner diameter portion of the casing 110. The axial length of the main rotor 120 may be set such that the front and rear surfaces of the main rotor 120 maintain airtightness with the front and rear inner walls of the casing 110. The main rotor 120 is formed in a cylindrical shape except for the satellite rotor chambers 121 of the outer diameter. Accordingly, the inner flow path 111 may be formed in a donut shape having a uniform width in the radial direction except for the blades 130 and the satellite rotor 140.

The blades 130 divide the inner flow path 111 of the casing 110 into a plurality of

closed sections

111a, 111b, and 111c at equal intervals along the rotation direction of the main rotor 120. The blades 130 are formed to protrude from the inner diameter portion of the casing 110, respectively. The blades 130 are formed so that each protruding end maintains airtightness with the outer diameter portion of the main rotor 120.

In addition, the blades 130 have the same length as the axial length of the inner space of the casing 110 and are formed to maintain airtightness with the front and rear inner walls of the casing 110. All of the blades 130 have the same shape. The blades 130 may be manufactured integrally with the casing 110.

As an example, the blades 130 are provided in three and are arranged at intervals of 120 degrees on the inner diameter of the casing 110 so that the inner flow path 111 of the casing 110 is three independent

closed sections

111a, 111b, and 111c. It can be divided into equal intervals. As another example, the blade 130 may be provided in two or four or more to divide the inner flow path 111 of the casing 110 into two or four or more independent closed sections at equal intervals.

The satellite rotors 140 are arranged at equal intervals with the number of

closed sections

111a, 111b, and 111c along the outer diameter of the main rotor 120. The satellite rotors 140 are supported to be rotated while maintaining airtightness with the inner diameter of the casing 110 while being partially accommodated in the outer diameter of the main rotor 120 and rotating according to the rotation of the main rotor 120 do.

All of the satellite rotors 140 may have the same shape. The satellite rotor 140 may be formed to have a cylindrical shape except for the passage groove 141. The satellite rotor 140 may be set to rotate in the inner space of the casing 110 while maintaining airtightness with the front and rear inner walls of the casing 110 in the front and rear surfaces based on the axial direction. The satellite rotor 140 may be rotatably supported on the casing 110 by a central shaft.

The main rotor 120 may include satellite rotor chambers 121 in an outer diameter portion. The satellite rotor chambers 121 are arranged at equal intervals along the outer diameter of the main rotor 120 with the same number as the number of the satellite rotors 140. All of the satellite rotor chambers 121 have the same shape. The satellite rotor chambers 121 are respectively formed on the outer diameter of the main rotor 120.

The satellite rotor chambers 121 support each rotational motion of the satellite rotors 140 in a state in which the satellite rotors 140 are partially accommodated. In addition, the satellite rotor chambers 121 allow the orbital movement of the satellite rotors 140 according to the rotation of the main rotor 120 while partially accommodating the satellite rotors 140. The satellite rotor chamber 140 may be formed in the outer diameter of the main rotor 120 as a semi-pillar groove.

The satellite rotors 140 pass the blades 130 through each of the passage grooves 141 while rotating by the linkage mechanism 170 during orbiting motion. Each of the through grooves 141 may be formed on the outer diameter of the satellite rotor 140. The passage groove 141 is made of a size that can completely accommodate the blade 130 and allow it to pass through.

The linkage mechanism 170 may include satellite rotor gears 171 and a casing gear 172. The satellite rotor gears 171 are formed on the outer diameter portions of the satellite rotors 140, respectively. The casing gear 172 is formed in 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 engaged with the satellite rotor gears 171 according to the revolution of the satellite rotors 140 The satellite rotors 140 are rotated. Accordingly, the satellite rotors 140 rotate without colliding with the blades 130 according to the rotation of the main rotor 120 and compress the air in the

closed sections

111a, 111b, and 111c.

The casing gear 172 is formed in the inner diameter of the casing 110 in the form of an internal gear. Assuming that the number of satellite rotors 140 is N, the casing gear 172 and the satellite rotor gear 171 have a gear ratio of N:1 between each other. For example, when the number of satellite rotors 140 is three, the casing gear 172 and the satellite rotor gear 171 have a gear ratio of 3:1 to each other.

As another example, the satellite rotor gear 171 may be formed in a portion other than the outer diameter portion of the satellite rotor 140, and the casing gear 172 is also formed in a portion other than the inner diameter portion of the casing 110, the above-described function You can also do

The suction ports 150 are formed in the casing 110 to correspond to the starting points of the

closed sections

111a, 111b, and 111c to communicate with 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 are formed in the casing 110 to correspond to each end point of the

closed sections

111a, 111b, and 111c to communicate with the

closed sections

111a, 111b, and 111c. The discharge ports 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 may be formed through the casing 110 from both sides of the blade 130.

An example of the operation of the positive displacement compressor 1100 will be described below.

First, when the main rotor 120 rotates in the direction for air compression by rotational power in the inner space of the casing 110, the satellite rotors 140 rotate according to the rotation of the main rotor 120 and at the same time Due to the action between the rotor gears 171 and the casing gear 172, it rotates in a direction opposite to the rotational direction of the main rotor 120. At this time, the satellite rotors 140 continuously move through the three

closed sections

111a, 111b, and 111c while sequentially passing the blades 130 through the respective passage grooves 141 according to the orbital and rotational motion. .

In this process, the volume on the front end side of the satellite rotor 140 is narrowed for each closed section (111a, 111b, 111c), and the volume on the rear end side of the satellite rotor 140 is increased, so that air intake and discharge are independently performed, The air can be compressed accordingly. As a result, since the main rotor 120 rotates with inertia and achieves a volume change corresponding to three times the internal volume per rotation, a considerable amount of compressed air can be transferred even with a relatively small standard.

Meanwhile, the above-described positive displacement compressor 1100 may be applied in a manner in which air is compressed while rotating the casing 110 while the main rotor 120 is fixed in a position so as not to rotate.

The rotary type positive displacement turbine 1200 may be configured similarly to the rotary type positive displacement compressor 1100. Accordingly, the positive displacement turbine 1200 includes the casing 110 constituting the positive displacement compressor 1100, the main rotor 120, the blades 130, the satellite rotors 140, and the suction port 150. And discharge ports 160 may be included.

Here, the suction port 150 and the discharge port 160 of the positive displacement turbine 1200 may be positioned opposite to each other from the suction port 150 and the discharge port 160 of the positive displacement compressor 1100. Meanwhile, the positive displacement compressor 1100 may be configured as a general rotary type positive displacement compressor, and the positive displacement turbine 1200 may be configured as a general rotary positive displacement turbine.

The positive displacement turbine 1200 may include combustion chambers 1210 in the

closed sections

111a, 111b, and 111c, respectively. The combustion chamber 1210 may be formed in the casing 110 to communicate with the suction port 150. The combustion chamber 1210 may include a combustor 1220 such as a burner or an ignition plug therein. The combustor 1220 burns fuel mixed with compressed air.

The transmission 1300 may be configured as a planetary gear train. For example, the transmission 1300 may include an internal gear (1310), planet gear (planet gear, 1320), a carrier (carrier, 1330), and a sun gear (sun gear, 1340).

The internal gear 1310 is connected to the output shaft of the positive displacement turbine 1200. The internal gear 1310 is coupled coaxially with the main rotor 120 of the positive displacement turbine 1200 by a spline method, etc., so that the rotational power input from the main rotor 120 of the positive displacement turbine 1200 is transmitted. I can.

The planetary gears 1320 are arranged around the internal gear 1310 in a state of being engaged with the internal gear 1310, respectively. The planetary gears 1320 may be arranged at equal intervals around the internal gear 1310. The planetary gears 1320 are illustrated as three, but are not limited thereto.

The carrier 1330 supports each of the planetary gears 1320 so as to rotate. In addition, the carrier 1330 supports the planetary gears 1320 so that they can orbit around the internal gear 1310 while maintaining a distance from each other.

The sun gear 1340 is connected to the input shaft of the positive displacement compressor 1100 in a state engaged with the planetary gears 1320 at the center of the internal gear 1310. The sun gear 1340 is coaxially coupled with the main rotor 120 of the positive displacement compressor 1100 by a spline method, etc., so that the changed rotational power is output to the main rotor 120 of the positive displacement compressor 1100. I can.

When the positive displacement compressor 1100 and the positive displacement turbine 1200 each have three closed

sections

111a, 111b, and 111c, the sun gear 1340 has an internal gear 1310 and a gear ratio of 3:1. However, it is not limited to what is illustrated.

According to the transmission 1300, as the main rotor 120 of the positive displacement turbine 1200 rotates, the internal gear 1310 rotates in the same direction as the rotation direction of the main rotor 120. Accordingly, the planetary gears 1320 rotate in the same direction as the rotation direction of the main rotor 120 while being supported by the carrier 1330. Then, as the sun gear 1340 accelerates and rotates at a transmission ratio in the direction opposite to the rotation direction of the main rotor 120, the main rotor 120 of the positive displacement compressor 1100 is transferred to the main rotor of the positive displacement turbine 1200. 120) and rotate in the opposite direction.

In this way, since the main rotor 120 of the positive displacement compressor 1100 is accelerated and rotates at a speed ratio than the main rotor 120 of the positive displacement turbine 1200, the positive displacement turbine 1200 At each rotation, compressed air is continuously supplied by the positive displacement compressor 1100 at a ratio corresponding to the transmission ratio of the transmission 1300 to be compressed.

For example, when the transmission ratio is 3:1, the air compressed in the three

closed sections

111a, 111b, and 111c of the positive displacement compressor 1100 is the three

closed sections

111a and 111b of the positive displacement turbine 1200. , 111c) and can be compressed by the positive displacement turbine 1200, it is possible to increase the compression ratio compared to the case where there is no transmission.

Meanwhile, the transmission 1300 may be accommodated in the transmission housing 1350. As another example, the transmission 1300 may be accommodated in the casing 110 of the positive displacement compressor 1100 or the casing 110 of the positive displacement turbine 1200.

The positive displacement turbine engine 1000 may include a connection passage 1351 and a check valve 1352. The connection passage 1351 delivers air discharged from the positive displacement compressor 1100 to the positive displacement turbine 1200. The connection passages 1351 may have the same number as the discharge ports 160 of the positive displacement compressor 1100. The connection passages 1351 may connect the discharge ports 160 of the positive displacement compressor 1100 and the suction ports 150 of the positive displacement turbine 1200 on a one-to-one basis.

The connection passages 1351 may be formed in the transmission housing 1350. As another example, the discharge port 160 of the positive displacement compressor 1100 and the suction port 150 of the positive displacement turbine 1200 may be connected to a separate pipe body, and a connection passage 1351 may be formed in the pipe body. The connection passage 1351 may have a certain cross-sectional area. Although not shown, the connection passage 1351 is formed in a form extending from the discharge port 160 of the positive displacement compressor 1100 to the suction port 150 of the positive displacement turbine 1200 to diffuse air, thereby reducing the pressure of the air. You can increase it.

The check valve 1352 controls air to flow only from the positive displacement compressor 1100 to the positive displacement turbine 1200 through the connection passage 1351. The check valve 1352 allows air to flow only from the discharge port 160 of the positive displacement compressor 1100 to the suction port 150 of the positive displacement turbine 1200 and prevents backflow of air. Accordingly, the positive displacement turbine 1200 may receive compressed air from the positive displacement compressor 1100 without loss. The check valve 1352 may be installed for each connection passage 1351. As another example, the check valve 1352 may be mounted for each discharge port 160 of the positive displacement compressor 1100 or may be installed for each suction port 150 of the positive displacement turbine 1200.

The positive displacement turbine engine 1000 may include a diffuser 1353. The diffuser 1352 diffuses air discharged from the positive displacement compressor 1100 and transfers it to the positive displacement turbine 1200. The diffuser 1352 converts velocity energy of air into pressure energy of air. Air discharged from the discharge ports 160 of the positive displacement compressor 1100 may be supplied to the combustion chamber 1210 of the positive displacement turbine 1200 by increasing the pressure as the speed decreases through the diffuser 1353. Accordingly, the efficiency of the positive displacement turbine 1200 may be further increased.

The diffuser 1352 may be configured to diffuse air discharged from the discharge port 160 of the positive displacement compressor 1100 in the internal space of the transmission housing 1350. Meanwhile, the internal space of the transmission housing 1350 may be used as a compressed air storage tank. The transmission housing 1350 may be omitted.

An example of the operation of the positive displacement turbine engine 1000 according to the first embodiment will be described below.

The positive displacement turbine 1200 combusts the fuel mixed with air in each combustion chamber 1210 by a corresponding combustor 1220 at startup. Then, the combustion gas is expanded and is sucked and discharged in each of the

closed sections

111a, 111b, and 111c of the positive displacement turbine 1200. In this process, the main rotor 120 of the positive displacement turbine 1200 is rotated by the expansion energy of the combustion gas. Then, the main rotor 120 of the positive displacement compressor 1100 receives rotational power from the main rotor 120 of the positive displacement turbine 1200 through the transmission 1300, and the corresponding

closed sections

111a, 111b, 111c Compressed air in

Compressed air is supplied to the combustion chambers 1210 of the positive displacement turbine 1200 through the check valve 1352 in each

closed section

111a, 111b, and 111c of the positive displacement compressor 1100. At this time, since the main rotor 120 of the positive displacement compressor 1100 is accelerated and rotates at a speed ratio than the main rotor 120 of the positive displacement turbine 1200, the positive displacement turbine 1200 is operated every time of the corresponding main rotor 120. Compressed air is continuously supplied by the exhibition displacement compressor 1100 at a rate corresponding to the transmission ratio of the transmission 1300 to be burned. As a result, the efficiency of the positive displacement turbine engine 1000 may be increased.

Meanwhile, since the main rotor 120 of the positive displacement compressor 1100 outputs relatively high rotational power, it can be used in a device that requires a high-speed rotational power. Since the main rotor 120 of the positive displacement turbine 1200 outputs a relatively low rotational power, it may be used in a device requiring a low rotational power.

On the other hand, if the number of

closed sections

111a, 111b, 111c of the positive displacement turbine 1200, which functions as a turbine, is reduced, the compression ratio can be further increased. For example, if it is configured to perform the turbine function only in two closed sections among the three

closed sections

111a, 111b, and 111c of the positive displacement turbine 1200 and perform the compression function in the remaining one closed section, Air compressed at a ratio of 5:1 at every rotation of the turbine 1200 may be used for a turbine function.

As another example, if one of the three

closed sections

111a, 111b, and 111c of the positive displacement turbine 1200 is configured to perform a turbine function only in one closed section and perform a compression function in the remaining two closed sections, 11: Air compressed at a ratio of 1 is available for turbine function.

6 is a perspective view of a positive displacement turbine engine according to a second embodiment of the present invention. 7 is a side cross-sectional view of FIG. 6. 8 is an exploded perspective view of FIG. 6. 9 is a front cross-sectional view of the positive displacement compressor in FIG. 6. 10 is a front cross-sectional view for explaining the operation of the positive displacement compressor shown in FIG.

6 to 10, a positive displacement turbine engine 2000 according to a second embodiment of the present invention includes a rotary positive displacement compressor 2100, a rotary positive displacement turbine 2200, and a transmission. 2300).

The rotary type positive displacement compressor 2100 includes the casing 210, the main rotor 220, the blades 230, the satellite rotors 240, the suction ports 250, and the discharge ports 260. Include.

The casing 210 has a cylindrical inner space. The main rotor 220 is disposed in the center of the casing 210 and rotates by rotational power. The main rotor 220 is disposed coaxially with the casing 210. The main rotor 220 may rotate by receiving the rotational power of an external driving source, that is, the positive displacement turbine 2200 through a rotation shaft 220a coaxially coupled to the center.

The main rotor 220 forms an inner flow path 211 between the outer diameter portion and the inner diameter portion of the casing 210. The axial length of the main rotor 220 may be set such that the front and rear surfaces of the main rotor 220 maintain airtightness with the front and rear inner walls of the casing 210. The main rotor 220 is formed to have a cylindrical shape except for the blades 230 of the outer diameter. Accordingly, the inner flow path 211 may be formed in the shape of a donut having a uniform width in the radial direction except for the blades 230 and the satellite rotor 240.

The blades 230 are arranged at equal intervals along the outer diameter of the main rotor 220. The blades 230 revolve according to the rotation of the main rotor 220 while maintaining airtightness with the inner diameter portion of the casing 210 while protruding from the outer diameter portion of the main rotor 220, respectively.

The blades 230 are formed so that each protruding end maintains airtightness with the inner diameter portion of the casing 210. In addition, the blades 230 have the same length as the axial length of the main rotor 220 and are formed to maintain airtightness with the front and rear inner walls of the casing 210. All of the blades 230 have the same shape. The blades 230 may be manufactured integrally with the main rotor 220.

As an example, the blades 230 may be provided in three and may be arranged at 120 degree intervals on the outer diameter portion of the main rotor 220. As another example, two or four or more blades 230 may be arranged at equal intervals on the outer diameter portion of the main rotor 220.

The satellite rotors 240 are equally spaced in the inner flow path 211 of the casing 210 in the same number of

closed sections

211a, 211b, 211c as the number of blades 230 along the rotation direction of the main rotor 220 It is divided into. The satellite rotors 240 are supported so that they can rotate while being partially accommodated in the inner diameter of the casing 210.

All of the satellite rotors 240 may have the same shape. The satellite rotor 240 may be formed in a cylindrical shape except for the passage groove 241. The satellite rotor 240 may be set to rotate in the inner space of the casing 210 while maintaining airtightness between the front and rear inner walls of the casing 210 based on the axial length. The satellite rotor 240 may be rotatably supported on the casing 210 by a central shaft.

The casing 210 may include satellite rotor chambers 212 in an inner diameter portion. The satellite rotor chambers 212 are arranged at equal intervals along the inner diameter of the casing 210 in the same number as the number of the satellite rotors 240. All of the satellite rotor chambers 212 have the same shape. The satellite rotor chambers 212 are formed on the inner diameter of the casing 210, respectively.

The satellite rotor chambers 212 support each rotational motion of the satellite rotors 240 in a state in which the satellite rotors 240 are partially accommodated. The satellite rotor chamber 212 may be formed in the inner diameter of the casing 210 as a semi-pillar groove. The casing 210 may have a uniform thickness by protruding the outer diameter portion as much as a groove so that the inner diameter portion forms the satellite rotor chambers 212.

The satellite rotors 240 are rotated by the linkage mechanism 270 during the orbital movement of the blades 230 and pass the blades 230 through each of the passage grooves 241. Each of the passage grooves 241 may be formed on the outer diameter of the satellite rotor 240. The passage groove 241 is made of a size that can completely accommodate the blade 230 and allow it to pass through.

The linkage mechanism 270 may include satellite rotor gears 271 and a main rotor gear 272. The satellite rotor gears 271 are formed on the outer diameter portions of the satellite rotors 240, respectively. The main rotor gear 272 is formed on the outer diameter of the main rotor 220 with the same number of teeth as the total number of teeth of the satellite rotor gears 271, and is engaged with the satellite rotor gears 271 to rotate the blades 230. Accordingly, the satellite rotors 240 are rotated. Accordingly, the blades 230 may orbit without colliding with the satellite rotors 240 according to the rotation of the main rotor 220 and compress the air in the

closed sections

211a, 211b, 211c.

The main rotor gear 272 is formed on the outer diameter of the main rotor 220 in the form of an external gear. If the number of satellite rotors 240 is N, the main rotor gear 272 and the satellite rotor gear 271 have a gear ratio of N:1 to each other. For example, when the number of satellite rotors 240 is three, the main rotor gear 272 and the satellite rotor gear 271 have a gear ratio of 3:1 to each other.

As another example, the satellite rotor gear 271 may be formed in a portion other than the outer diameter portion of the satellite rotor 240, and the main rotor gear 272 is also formed in a portion other than the outer diameter portion of the main rotor 220, It can also perform a function.

The suction ports 250 are formed in the casing 210 to correspond to the starting points of the

closed sections

211a, 211b, 211c, and communicate with the

closed sections

211a, 211b, 211c. The intake ports 250 allow air to be sucked into the

closed sections

211a, 211b, 211c, respectively.

The discharge ports 260 correspond to respective end points of the

closed sections

211a, 211b, 211c, and are formed in the casing 210 to communicate with the

closed sections

211a, 211b, 211c. The discharge ports 260 allow air to be discharged from the

closed sections

211a, 211b, 211c, respectively. The discharge port 260 may form a pair with the suction port 250 to pass through the casing 210 on both sides of the satellite rotor 240.

In this way, the blades 230 of the second embodiment are replaced with the satellite rotors 140 of the first embodiment, and the satellite rotors 240 of the second embodiment are configured to be replaced with the blades 130 of the first embodiment. I can.

An example of the operation of the positive displacement compressor 2100 will be described below.

First, when the main rotor 220 rotates in a direction for air compression by rotational power in the inner space of the casing 210, the blades 230 orbitally move according to the rotation of the main rotor 220. At the same time, the satellite rotors 240 rotate in a direction opposite to the rotational direction of the main rotor 220 by an action between the satellite rotor gears 271 and the casing gear 272. At this time, the blades 230 sequentially pass through the satellite rotors 240 through the respective passage grooves 241 of the satellite rotors 240 according to their own orbital motion and the rotational motions of the satellite rotors 240, while three closed sections. The

fields

211a, 211b, 211c are continuously moved.

In this process, the volume on the front end side of the blade 230 is narrowed in each closed section (211a, 211b, 211c), and the volume on the rear end side of the blade 230 is widened, so that the intake and discharge of air are independently performed. Air can be compressed. As a result, since the main rotor 220 rotates with inertia and achieves a volume change corresponding to three times the internal volume per rotation, a considerable amount of compressed air can be transferred even with a relatively small standard.

Meanwhile, the above-described positive displacement compressor 2100 may also be applied in a manner of compressing air while rotating the casing 210 while the main rotor 220 is not rotated.

The rotary type positive displacement turbine 2200 may also be configured similarly to the rotary type positive displacement compressor 2100. Accordingly, the positive displacement turbine 2200 includes the casing 210 constituting the positive displacement compressor 2100, the main rotor 220, the blades 230, the satellite rotors 240, and the suction port 250. Fields, and discharge ports 260 may be included. Here, the suction port 250 and the discharge port 260 of the positive displacement turbine 2200 may be located opposite to each other from the suction port 250 and the discharge port 260 of the positive displacement compressor 2100.

On the other hand, the positive displacement compressor 2100 is composed of the positive displacement compressor 1100 of the first embodiment and is combined with the positive displacement turbine 2200, or the positive displacement turbine 2200 is used as the positive displacement turbine 1200 of the first embodiment. It may be configured and combined with the positive displacement compressor 2100. In addition, the positive displacement compressor 2100 may be configured as a general rotary type positive displacement compressor, and the positive displacement turbine 2200 may also be configured as a general rotary positive displacement type turbine.

The positive displacement turbine 2200 may be provided with combustion chambers 2210 in the

closed sections

111a, 111b, and 111c, respectively. The combustion chamber 2210 may be formed in the casing 110 to communicate with the suction port 150. The combustion chamber 2210 may have a combustor 2220 such as a burner or an ignition plug therein. The combustor 2220 combusts fuel mixed with compressed air.

The transmission 2300 may include an internal gear 1310, planetary gears 1320, a carrier 1330, and a sun gear 1340, similar to the transmission 1300 of the first embodiment. The transmission 2300 may be accommodated in the transmission housing 2350. As another example, the transmission 2300 may be accommodated in the casing 210 of the positive displacement compressor 2100 or the casing 210 of the positive displacement turbine 2200.

The positive displacement turbine engine 2000 may include a connection passage 2351 and a check valve 2352. The connection passage 2351 may function in the same manner as the connection passage 1351 of the first embodiment. That is, the connection passage 2351 delivers the air discharged from the discharge port 260 of the positive displacement compressor 2100 to the suction port 250 of the positive displacement turbine 2200. The connection passages 2351 may be formed in the transmission housing 2350. As another example, the discharge port 260 of the positive displacement compressor 2100 and the suction port 250 of the positive displacement turbine 2200 may be connected by a separate pipe body, and a connection passage 2351 may be formed in the pipe body.

The check valve 2352 may act in the same way as the check valve 1352 of the first embodiment. That is, the check valve 2352 allows air to flow only from the positive displacement compressor 2100 to the positive displacement turbine 2200 through the connection passage 2351 and prevents air from flowing backward. The check valve 2352 may be installed for each connection passage 2351. The check valve 2352 may be mounted for each discharge port 260 of the positive displacement compressor 2100 or may be installed for each suction port 250 of the positive displacement turbine 2200.

The positive displacement turbine engine 2000 may include a diffuser 2353. The diffuser 2353 may function in the same way as the diffuser 1352 of the first embodiment. That is, the diffuser 2353 diffuses the air discharged from the positive displacement compressor 2100 and transfers it to the positive displacement turbine 2200.

The diffuser 2353 may be configured to diffuse air discharged from the discharge port 260 of the positive displacement compressor 2100 in the internal space of the transmission housing 2350. Meanwhile, the internal space of the transmission housing 2350 may be used as a compressed air storage tank. The transmission housing 2350 may be omitted. The positive displacement turbine engine 2000 according to the second exemplary embodiment operates in the same manner as the positive displacement turbine engine 1000 according to the first exemplary embodiment, thereby increasing efficiency.

The present invention has been described with reference to one embodiment shown in the accompanying drawings, but this is only illustrative, and those of ordinary skill in the art will understand that various modifications and other equivalent embodiments are possible therefrom. I will be able to. Accordingly, the true scope of protection of the present invention should be determined only by the appended claims.

Claims

A rotary type positive displacement compressor that increases pressure through volume reduction by inhaling air by rotational power;

A rotary type positive displacement turbine for obtaining rotational power by burning fuel mixed with air; And

A transmission for accelerating rotational power input from the output shaft of the positive displacement turbine and outputting it to the input shaft of the positive displacement compressor;

Positive displacement turbine engine comprising a.
The method of claim 1,

At least one of the positive displacement compressor and positive displacement turbine,

A casing having a cylindrical inner space;

A main rotor disposed in the center of the casing, rotating by rotational power, and forming an inner flow path between an outer diameter portion and an inner diameter portion of the casing;

Blades each protruding from the inner diameter portion of the casing so as to divide the inner flow path of the casing into a plurality of closed sections at equal intervals along the rotation direction of the main rotor;

Arranged at equal intervals with the number of closed sections along the outer diameter of the main rotor and partially accommodated in the outer diameter of the main rotor, while maintaining airtightness with the inner diameter of the casing, it is supported to enable rotational motion. Satellite rotors that orbit according to the rotation of the main rotor and pass through the blades through respective passage grooves while rotating by a linkage mechanism during the orbital motion;

Suction ports formed in the casing to correspond to the starting points of the closed sections and communicated with the closed sections; And

Discharge ports formed in the casing to correspond to respective end points of the closed sections to communicate with the closed sections;

Displacement type turbine engine comprising a.
The method of claim 1,

At least one of the positive displacement compressor and positive displacement turbine,

A casing having a cylindrical inner space;

A main rotor disposed in the center of the casing, rotating by rotational power, and forming an inner flow path between an outer diameter portion and an inner diameter portion of the casing;

Blades arranged at equal intervals along the outer diameter portion of the main rotor, each protruding from the outer diameter portion of the main rotor, maintaining airtightness with the inner diameter portion of the casing, and revolving according to the rotation of the main rotor;

It is supported so that the inner flow path of the casing is divided into closed sections equal to the number of blades along the rotation direction of the main rotor at equal intervals while being partially accommodated in the inner diameter of the casing to enable rotational motion, the Satellite rotors passing through the blades through respective passage grooves while rotating by the linkage mechanism during the revolution movement of the blades;

Suction ports formed in the casing to correspond to the starting points of the closed sections and communicated with the closed sections; And

Discharge ports formed in the casing to correspond to respective end points of the closed sections to communicate with the closed sections;

Displacement type turbine engine comprising a.
The method of claim 1,

The transmission,

An internal gear connected to the output shaft of the positive displacement turbine,

Planetary gears arranged around the internal gear while being engaged with the internal gear, respectively,

A carrier supporting each of the planetary gears to enable rotation, and

A positive displacement turbine engine comprising a sun gear connected to an input shaft of the positive displacement compressor in a state engaged with the planetary gears at the center of the internal gear.
The method of claim 1,

A connection passage for delivering air discharged from the positive displacement compressor to the positive displacement turbine, and

And a check valve for controlling air to flow only from the positive displacement compressor to the positive displacement turbine through the connection passage.
The method of claim 1,

And a diffuser for diffusing the air discharged from the positive displacement compressor and transferring it to the positive displacement turbine.