KR200459673Y1 - Parallel type horizontal super dynamics high effiency hybrid turbine engine - Google Patents

Abstract

In the parallel horizontal super power high efficiency hybrid turbine engine of the present invention, a first blade (impulse and recoil structure) and a second blade (impulse structure) are formed at the outer and outer sides of the rotating body coupled to the shaft, respectively. First, after the high pressure injection of the pressurized fluid to the second blade in the jet injection nozzle portion, the residual compressed fluid passing through the second blade is guided again to the first blade by the velocity curve diagram part and injected at high pressure, whereby the rotating body Impulse force is of course accelerated by the reaction force (加速) has the effect of reducing the energy loss. In addition, the present invention has the effect of increasing the output of the turbine can be further accelerated by selectively spraying the compressed fluid to the first blade of the rotating body in the thrust nozzle unit (booster). In addition, the present invention is designed so that the control unit is operated by computer programming, it detects the operating situation through various sensors such as speed sensor, capacity sensor, pressure sensor, temperature sensor, temperature sensor, and the like, By detecting and feeding back in real time, the operator automatically controls the jet nozzle section and compressed fluid injection of the thrust nozzle section, automatically controls the output of the turbine shaft, and displays this set of operating conditions with an indicator, allowing the operator to operate the turbine. Make sure to check.

Description

PARALLEL TYPE HORIZONTAL SUPER DYNAMICS HIGH EFFIENCY HYBRID TURBINE ENGINE}

The present invention relates to a parallel horizontal super-power high efficiency hybrid turbine engine, and more specifically, the first blade of the impulse and reaction structure is formed on the outer shell of the rotor coupled to the turbine shaft, The second blade (Second blade) of the impulse structure is formed on the outermost side, the turbine output is generated by the first blade and the second blade, and the turbine output can be selectively increased by the thrust nozzle part (booster). In addition, the present invention relates to a parallel horizontal super-power high efficiency hybrid turbine engine in which the turbine output can be automatically controlled by computer programming.

Common power generation methods include hydroelectric power generation using hydroelectric power, thermal power generation using fossil fuels, and nuclear power generation using nuclear power. However, these power generation methods generate enormous amounts of energy to operate large-scale power generation facilities and power generation facilities. in need. In particular, fossil fuels such as petroleum and coal as energy sources used in thermal power generation are highly dependent on other fuels, causing problems such as exhaustion of resources. Moreover, it is well known that fossil fuels such as oil and coal are the major causes of global warming by destroying the ozone layer. In addition, fossil fuels such as petroleum and coal are also the main causes of environmental pollution. Therefore, in order to prevent environmental pollution caused by depletion of resources caused by the use of petroleum or coal, and various disasters caused by global warming caused by burning oil or coal, and the generation of various pollutants, fossil fuels such as petroleum and coal are used. There is a need for breakthrough development methods that do not require

Patent publications 10-2004-7004016 (wind power generator), 10-2005-0021863 (wind generators for home use), 10-2005-7020515 (rotor blades for wind power generators) and the like are disclosed. Due to such demands, power generation methods that can utilize energy sources that are environmentally and permanently using natural energy such as solar, tidal, wave, and wind power have been developed and applied to reality. Among them, the solar and wind power generation method is a power generation method that can be applied not only to large-scale power generation but also to general households. In particular, the power generation method using wind power turns windmills (wind propellers) into natural winds and gears. It uses a mechanism to increase the speed and turn the generator to produce power. As a wind speed suitable for driving such a wind generator, it is known that 3m / s or more and 20m / s or less are suitable. In other words, in the breeze of less than 3m / s wind turbine generator is impossible to operate the power production itself, because the strong wind of more than 20m / s is the wind speed enough to burn the facilities. Therefore, it is usually designed to prevent the generator itself from operating in strong winds of 20m / s or more. This creates a problem that the wind generator is virtually impossible to operate if the wind speed is outside the range of 3 m / s to 20 m / s. As a result, in the case of the conventional wind generators, the wind turbine generator cannot be driven under climatic conditions unsuitable for driving the wind turbines. Thus, when the wind speed is blown, the device operates to generate electricity. The production efficiency is very low due to the extremely low utilization of the equipment compared to the cost of the facility.

The present invention is to solve the above problems, the first blade (impulse and recoil structure) is formed on the outer shell of the rotating body coupled to the turbine shaft and the second blade (impulsive structure) is formed on the outermost, First, after the high pressure injection of the pressurized fluid to the second blade in the jet injection nozzle portion, the residual compressed fluid passing through the second blade is guided again to the first blade by the velocity curve diagram part and injected at high pressure, whereby the rotating body It is an object of the present invention to provide a parallel horizontal super-powered high efficiency hybrid turbine engine capable of reducing energy loss by being accelerated by the impulse force as well as the reaction force.

In addition, the present invention is the first turbine engine unit and the second turbine engine unit is arranged in parallel, the first gear is installed on the turbine shaft of the first turbine engine unit, the second gear is installed on the turbine shaft of the second turbine engine unit. A connecting gear is installed between the first gear and the second gear, and a main turbine shaft is installed in the connecting gear, and the outputs of the first turbine engine unit and the two turbine engine unit are combined and output to the main turbine shaft, thereby doubling the turbine output. It is to provide a parallel horizontal super power high efficiency hybrid turbine engine that can be added.

In addition, the present invention is a parallel horizontal type ultra high pressure spraying the compressed fluid to the first blade of the rotating body in the thrust nozzle unit (booster) to selectively accelerate the rotating body to increase the output of the turbine Its purpose is to provide a power efficient high efficiency hybrid turbine engine.

It is also an object of the present invention to provide a parallel horizontal super power high efficiency hybrid turbine engine capable of freely controlling the turbine output by computer programming of a control unit (control unit).

In order to achieve the above object, the parallel horizontal super power high efficiency hybrid turbine engine of the present invention is a new power engine technology that will lead the next generation green revolution, and the first turbine engine unit and the second turbine engine unit are disposed in parallel And a first gear is installed at the turbine shaft of the first turbine engine unit, a second gear is installed at the turbine shaft of the second turbine engine unit, and a connecting gear is installed between the first gear and the second gear. The main gear shaft is installed in the connecting gear, and the outputs of the first turbine engine unit and the second turbine engine unit are combined to be output to the main turbine shaft.

First, the first turbine engine unit includes a turbine shaft rotatably installed in the turbine casing; At least one rotor fixed to the turbine shaft, wherein a plurality of first blades (impact and recoil structures) are formed at the outer shell, and a plurality of second blades (impact structures) are formed at the outermost shell; A jet nozzle unit installed inside the turbine casing for high-pressure injection of compressed fluid (steam, gas, etc.) to the second blade; A velocity curve diagram portion formed at equal intervals in the turbine casing to guide and eject the residual compressed fluid passing through the second blade in the direction of the first blade; Fixed to both sides of the turbine casing rotatably supports the turbine shaft, the discharge curve is formed on the inside to discharge the compressed fluid passing through the first blade to the outside of the turbine casing by the velocity curve diagram portion Fixture; A plurality of thrust nozzle portions (Booster) installed in the turbine casing to accelerate the rotating body by spraying the compressed fluid to the first blade; A control unit which senses the rotational speed of the rotating body so as to control the output of the turbine shaft, and automatically controls the compressed fluid injection between the jet nozzle unit and the thrust nozzle unit; And a velocity guide plate installed adjacent to the velocity curve diagram portion to guide and eject residual compressed fluid in the direction of the first blade.

The second turbine engine unit may include a turbine shaft rotatably installed in the turbine casing; At least one rotor fixed to the turbine shaft, wherein a plurality of first blades (impact and recoil structures) are formed at the outer shell, and a plurality of second blades (impact structures) are formed at the outermost shell; A jet nozzle unit installed inside the turbine casing for high-pressure injection of compressed fluid (steam, gas, etc.) to the second blade; A velocity curve diagram portion formed at equal intervals in the turbine casing to guide and eject the residual compressed fluid passing through the second blade in the direction of the first blade; Fixed to both sides of the turbine casing rotatably supports the turbine shaft, the discharge curve is formed on the inside to discharge the compressed fluid passing through the first blade to the outside of the turbine casing by the velocity curve diagram portion Fixture; A plurality of thrust nozzle portions (Booster) installed in the turbine casing to accelerate the rotating body by spraying the compressed fluid to the first blade; A control unit which senses the rotational speed of the rotating body so as to control the output of the turbine shaft, and automatically controls the compressed fluid injection between the jet nozzle unit and the thrust nozzle unit; And a velocity guide plate installed adjacent to the velocity curve diagram portion to guide and eject residual compressed fluid in the direction of the first blade.

As described above, in the present invention, the first blade (impulse and recoil structure) is formed on the outer surface of the rotating body coupled to the turbine shaft, and the second blade (impulse structure) is formed on the outermost surface, thereby primarily jetting. After the high pressure injection of the pressurized fluid to the second blade at the injection nozzle part, the residual compressed fluid having passed through the second blade is guided to the first blade again by the velocity curve diagram part and injected at high pressure, whereby the rotating body Impulse force is of course accelerated by the reaction force (加速) has the effect of reducing the energy loss.

In addition, according to the present invention, a first turbine engine unit and a second turbine engine unit are arranged in parallel, a first gear is installed in a turbine shaft of the first turbine engine unit, and a second is installed in the turbine shaft of the second turbine engine unit. Gear is installed, connecting gear is installed between the first gear and the second gear, the main turbine shaft is installed in the connecting gear and the output of the first turbine engine unit and the two turbine engine unit is combined and output to the main turbine shaft. By configuring, the turbine output can be doubled.

In addition, the present invention has the effect of increasing the output of the turbine can be further accelerated by selectively spraying the compressed fluid to the first blade of the rotating body in the thrust nozzle unit (booster).

In addition, the present invention is designed so that the control unit is operated by computer programming, it detects the operation status through various sensors such as speed sensor, capacity sensor, pressure sensor, temperature sensor, and the rotational speed of the rotating body in real time And feedback, the automatic control of the injection of the jet nozzle and the thrust nozzle, the automatic control of the output of the turbine shaft, and the display of such a series of operating conditions, the operator can confirm the turbine operation Make sure

In addition, the present invention has the effect of increasing the fuel efficiency and reduce the air pollution by the exhaust gas by utilizing the exhaust gas by the turbocharger.

1 is a perspective view showing the appearance of a parallel horizontal super power high efficiency hybrid turbine engine according to a preferred embodiment of the present invention
FIG. 2 is a perspective view of the gearbox of the parallel horizontal super power high efficiency hybrid turbine engine of FIG. 1; FIG.
3 is a front view of the parallel horizontal super power high efficiency hybrid turbine engine of FIG.
4 is a plan view showing a parallel horizontal super power high efficiency hybrid turbine engine according to a preferred embodiment of the present invention
5 is a sectional view of the inside of the first turbine engine unit;
6 is a perspective view showing a turbine casing of a first turbine engine unit and a rotating body installed in the turbine casing;
7 is a front view of the turbine casing of the first turbine engine unit;
8 is a front view showing the inside of the turbine casing of the first turbine engine unit;
9 is a perspective view of a rotating body of the first turbine engine unit;
10 is a front view showing a rotor of the first turbine engine unit and a diagram for explaining the first and second blades of the rotor;
FIG. 11 is a perspective view showing a first blade of the first turbine engine unit and a diagram illustrating the twist angles of the top and bottom of the first blade; FIG.
12 is a view for explaining the principle of rotation of the rotating body of the first turbine engine unit.
13 is a front view showing the fixtures located on both sides of the turbine casing of the first turbine engine unit;
14 is a cross-sectional view of FIG.
15 is a front view showing a fixture located in the middle of the turbine casing of the first turbine engine unit;
16 is a cross-sectional view of FIG. 15
17 is a cross-sectional view of the inside of the second turbine engine unit.
18 is a perspective view showing a turbine casing of a second turbine engine unit and a rotating body installed in the turbine casing;
19 is a front view of the turbine casing of the second turbine engine unit;
20 is a front view of the inside of the turbine casing of the second turbine engine unit;
21 is a perspective view of a rotor of the second turbine engine unit;
22 is a front view showing a rotating body of the second turbine engine unit and a view for explaining the first blade and the second blade of the rotating body.
FIG. 23 is a perspective view showing a first blade of the second turbine engine unit and a diagram illustrating the twist angles of the top and bottom of the first blade; FIG.
24 is a view for explaining the rotational principle of the rotor of the second turbine engine unit.
25 is a front view showing the fixture located on both sides of the turbine casing of the second turbine engine unit;
FIG. 26 is a cross-sectional view of FIG. 25
27 is a front view showing a fixture positioned in the middle of the turbine casing of the second turbine engine unit;
FIG. 28 is a cross-sectional view of FIG. 27

Hereinafter, with reference to the accompanying drawings will be described in detail a horizontal type super-power high efficiency hybrid turbine engine and its super-power high efficiency hybrid turbine engine automatic control method according to a preferred embodiment of the present invention in detail.

1 is a perspective view showing the parallel horizontal super power high efficiency hybrid turbine engine appearance according to a preferred embodiment of the present invention, Figure 2 is a perspective view of the gearbox removed from the parallel horizontal super power high efficiency hybrid turbine engine of Figure 1, 3 is a front view showing a parallel horizontal super power highly efficient hybrid turbine engine of FIG. 1, and FIG. 4 is a plan view showing a parallel horizontal super power highly efficient hybrid turbine engine according to a preferred embodiment of the present invention.

Referring to the drawings, in the horizontal horizontal super power high efficiency hybrid turbine engine 1 according to a preferred embodiment of the present invention, the first turbine engine unit 10 and the second turbine engine unit 20 are arranged in parallel The first gear 121 is installed in the turbine shaft 120 of the first turbine engine unit 10, and the second gear 221 is installed in the turbine shaft 220 of the second turbine engine unit 20. The connecting gear 30 is installed between the first gear 121 and the second gear 221, and the main turbine shaft 31 is installed at the connecting gear 30 to provide the first turbine engine unit ( 10) and the output of the two turbine engine unit 20 is combined to be output to the main turbine shaft 31.

The gearbox 40 is covered with the first gear 121, the second gear 221, and the connecting gear 30, and a bearing cap 50 is installed. Lubricating oil is present in the gearbox 40 to prevent wear between the gears. An oil sealer S is installed in the turbine shafts 120 and 220 (see FIG. 4).

First, referring to FIGS. 5 to 16, the first turbine engine unit 10 includes a turbine casing 110; A turbine shaft 120 rotatably installed in the turbine casing 110; At least one rotating body (130) fixed to the turbine shaft (120), wherein a plurality of first blades (131) are formed at an outer shell, and a plurality of second blades (133) are formed at the outermost shell; A jet nozzle unit (140) installed inside the turbine casing (110) to inject high pressure to the second blade (133); Velocity curve diagram part formed at equal intervals in the turbine casing 110 to guide and inject the residual compressed fluid passing through the second blade 133 toward the first blade 131 ( 150); The turbine fluid is fixed to the turbine casing 110 to rotatably support the turbine shaft 120, and the compressed fluid passing through the first blade 131 by the velocity curve diagram part 150 is transferred to the turbine casing ( 110, the fixing body 160, 160 'is formed in the discharge portion (161, 161') to discharge to the outside; A plurality of thrust nozzle parts 170 installed on the turbine casing 110 to accelerate the rotating body 130 by spraying a compressed fluid on the first blade 131; And in real time to detect the rotational speed of the rotor 130 so as to control the output of the turbine shaft 120, and automatically injects the compressed fluid of the jet nozzle unit 140 and the thrust nozzle unit 170. A control unit (control unit) C for controlling is provided.

Hereinafter, in the parallel horizontal super power high efficiency hybrid turbine engine 1 according to a preferred embodiment of the present invention, the configuration of the first turbine engine unit 10 will be described in more detail.

First, the plurality of turbine casings 110 are formed in a cylindrical shape, horizontally positioned, supported by the base support bracket BS, and fixed to the base plate BP (see FIGS. 1 and 2). The plurality of turbine casings 110 are fastened by conventional fastening means, for example, through bolts B, and the like, and bolt holes H to which the through bolts B are coupled to the outside of the turbine casing 110. 6 are formed at regular intervals.

The jet nozzle part 140 is formed in the turbine casing 110 in place. The jet nozzle unit 140 plays a role of high pressure spraying the compressed fluid (steam, gas, etc.) to the second blade 133 (see FIGS. 1 and 5).

The jet nozzle unit 140 is provided with a compressed fluid control valve 117 for adjusting the flow rate of the compressed fluid, and each of the compressed fluid control valve 117 is provided with a pressure gauge P (see FIGS. 1 and 5). ).

A plurality of toggle brackets 115 are installed in the turbine casing 110 at regular intervals to prevent backflow of the compressed fluid injected from the jet nozzle unit 140 (see FIG. 7).

A velocity curve diagram portion 150 is formed at equal intervals within the turbine casing 110, that is, along the inner circumferential surface thereof (see FIGS. 5 and 12).

The velocity curve diagram unit 150 serves to guide and spray the residual compressed fluid that has passed through the second blade 133 toward the first blade 131, and does not impede the flow of the compressed fluid. It has a smooth curve shape.

At a position adjacent to the velocity curve diagram unit 150, a velocity guide plate 190 is fixedly installed inside the turbine casing 110 to guide and eject the residual compressed fluid in the direction of the first blade 131. (See Figure 5).

A guide hole 192 is formed between the guide blades 191 of the velocity guide plate 190 (see FIG. 12).

The velocity guide plate 190 may not only generate a reaction force by the residual compressed fluid guided by the velocity curve diagram unit 150 but also generate an impulse force by the compressed fluid injected from the thrust nozzle unit 170. The guide blades 191 have a thicker inlet portion and become thinner toward the outlet portion, and the guide hole 192 has a narrower outlet portion than the inlet portion (see FIG. 12).

The turbine shaft 120 is horizontally positioned at the center of the turbine casing 110 and rotatably installed. Four rotors 130 are fixedly installed on the turbine shaft 120 at regular intervals from each other (see FIG. 5). The number of the rotor 130 may be changed according to the design conditions.

The rotating body 130 has a plurality of first blades (internal blade) 131 is formed at the outer shell, a plurality of external blades (133) are formed at the outermost (see Fig. 9).

The first blade 131 has an impulsive and semi-reactive blade structure, and the second blade 133 is formed with an impulsive blade structure.

As shown in FIG. 5, the rotor 130 includes a left blade type and a light blade type, and the first blade 131 is disposed in the same manner as the left blade type and the light blade type. In the case of the second blade 133, the left blade type and the light blade type are positioned to face each other.

As such, the left blade type and the light blade type are opposite to each other and have the same shape. Therefore, only the left blade type is shown and described in the drawings in order to avoid duplication of description.

First, the second blade 133 has a symmetrical shape and is formed such that the incident angle and the projection angle of the compressed fluid are maintained at the same angle at 30 °, respectively (see FIGS. 5 and 10).

In the second blade 133, the compressed fluid injected from the jet nozzle unit 140 is incident at 30 ° and is output at 20 ° to the second blade 133, and a rotating body is generated by the impulse force generated at this time. Generate a rotational force of 130.

In addition, the first blade 131 has a left-right asymmetric shape, twisted downward from the upper end 131a to the lower end 131b, and gradually thickened, and the upper end 131a is twisted at 50 °. The lower end 131b is formed in a structure in which the angle is twisted at 20 ° (see FIG. 11).

In the first blade 131, the compressed fluid guided to the velocity curve diagram unit 150 is incident at 30 ° and output at 20 ° through the guide hole 192 of the velocity guide plate 190. At this time, the rotational force of the rotating body 130 is generated by the reaction force generated.

In addition, the compressed fluid of the thrust nozzle unit (booster) 170 is incident at 30 ° and output at 20 ° through the guide hole 192 of the velocity guide plate 190, and is rotated by the impulse force generated at this time. The rotational force of the whole 130 is generated (see FIG. 10).

The second blade 133 has a symmetrical shape and is formed such that the incident angle and the projection angle of the compressed fluid are maintained at the same angle at 30 °, respectively (see FIGS. 2 and 7).

In other words, in the impulsive structure, the relative speed of the compressed fluid at the inlet and the outlet of the second blade 133 is constant, so that the rotational force of the rotor 130 is generated only by the injection pressure of the compressed fluid. However, in the reactionary structure, the relative velocity of the compressed fluid at the inlet and the outlet of the first blade 131 increases, so that the injection pressure of the compressed fluid and the expansion pressure of the compressed fluid are added to generate the rotational force of the rotating body 130. Here, the first blade 131 generates an impulse rotational force by the compression fluid injection of the thrust nozzle unit (booster) 170 as well as the reaction force of the reaction type.

The fixed body 160 is fixed to both sides of the turbine casing 110 by a conventional fastening means, for example, a bolt (B), the center of the fixed body 160 can rotate the turbine shaft 120 The bearing portion 164 to be supported is installed. The bearing cover 165 is fixed to the bearing portion 164 by a bolt B '.

The fixed body 160 has a discharge part 161 therein for discharging the compressed fluid passing through the first blades 131 by the velocity curve diagram part 150 to the outside of the turbine casing 110. It is provided.

The discharge part 161 of the fixing body 160 is formed with a discharge hole 162 for discharging the compressed fluid passing between the second blade 133 to the outside of the turbine casing 110, the discharge An inclined fixed blade 163 is formed at the inlet of the hole 162 (see FIGS. 13 and 14).

The fixed body 160 'is fixed in the middle of the turbine casing 110, and a bearing portion 164' for rotatably supporting the turbine shaft 120 is installed at the center of the fixed body 160 '. do. The stationary body 160 ′ has an exhaust portion 161 ′ therein for discharging the compressed fluid passing through the first blade 131 to the outside of the turbine casing 110 by the velocity curve diagram portion 150. ).

A discharge hole 162 'is formed in the discharge part 161' of the fixing body 160 'to discharge the compressed fluid passing between the second blades 133 to the outside of the turbine casing 110. At the inlet of the discharge hole 162 ′, an inclined fixed blade 163 ′ is formed (see FIGS. 15 and 16).

An exhaust pipe 119 may be connected to the discharge parts 161 and 161 ′, and a turbocharger (T) (see FIG. 1) may be installed in the exhaust pipe 119. The turbocharger T serves to increase the output of the turbine engine using exhaust gas.

The thrust nozzle unit 170 is installed in a position inside the turbine casing 110 to further inject a compressed fluid to the first blade 131 to further accelerate the rotating body 130. In this case, the first blade 131 is preferably installed to inject the compressed fluid inclined at a predetermined angle (see FIGS. 1 and 2).

The control unit (C) is designed to operate by computer programming, and is operated through various sensors (not shown) such as a speed sensor, a capacity sensor, a pressure sensor, a temperature sensor, and a temperature sensor installed in the turbine casing 110. Detects a situation, detects the rotational speed of the rotor 130 in real time, automatically controls the injection of the compressed fluid of the jet nozzle unit 140 and the thrust nozzle unit 170, and the turbine shaft 120 In addition to the automatic control of the output, the series of operating conditions are displayed by an indicator (not shown), allowing the operator to confirm the turbine operation (see FIG. 5).

On the other hand, in the parallel horizontal super power high efficiency hybrid turbine engine 100 according to a preferred embodiment of the present invention, looks at the configuration of the second turbine engine unit 20 in more detail.

First, the plurality of turbine casings 210 are formed in a cylindrical shape, horizontally positioned, supported by the base support bracket BS, and fixed to the base plate BP (see FIGS. 1 and 2). The plurality of turbine casings 210 are fastened by conventional fastening means, for example, through bolts B, and the like, and bolt holes H to which the through bolts B are coupled to the outer surface of the turbine casing 210. 12 are formed in a plurality at regular intervals.

The jet nozzle part 240 is formed in the turbine casing 210 in place. The jet nozzle unit 240 serves to high-pressure spray the compressed fluid (steam, gas, etc.) to the second blade 233 (see FIGS. 1 and 17).

The jet nozzle unit 240 is provided with a compressed fluid control valve 217 for adjusting the flow rate of the compressed fluid, and each of the compressed fluid control valve 217 is provided with a pressure gauge P (see FIGS. 1 and 17). ).

A plurality of toggle brackets 215 are installed in the turbine casing 210 at regular intervals to prevent backflow of the compressed fluid injected from the jet nozzle unit 240 (see FIG. 19).

A velocity curve diagram portion 250 is formed at equal intervals inside the turbine casing 210, that is, along the inner circumferential surface (see FIGS. 17 and 24).

The velocity curve diagram part 2150 guides and sprays the residual compressed fluid that has passed through the second blade 233 toward the first blade 231, and does not hinder the flow of the compressed fluid. It has a smooth curve shape.

In a position adjacent to the velocity curve diagram part 250, a velocity guide plate 290 is fixedly installed inside the turbine casing 210 to guide and eject the residual compressed fluid in the direction of the first blade 231. (See Figure 17).

Guide holes 292 are formed between the guide blades 291 of the velocity guide plate 290 (see FIG. 24).

The velocity guide plate 290 may not only generate a reaction force by the residual compressed fluid guided by the velocity curve diagram part 250 but may also generate an impulse force by the compressed fluid injected from the thrust nozzle part 270. In the structure, the guide blades 291 have a thick inlet portion and become thinner toward the outlet portion, and the guide hole 292 has a narrower outlet portion than the inlet portion (see FIG. 24).

The turbine shaft 220 is horizontally positioned at the center of the turbine casing 210 and rotatably installed. Four rotors 230 are fixedly installed on the turbine shaft 220 at regular intervals from each other (see FIG. 17). The number of the rotor 230 may be changed according to the design conditions.

The rotor 230 has a plurality of first blades (internal blades) 231 is formed at the outer shell, a plurality of external blades (233) are formed at the outermost shell (see Fig. 21).

The first blade 231 has an impulsive and semi-reactive blade structure, and the second blade 233 is formed with an impulsive blade structure.

As shown in FIG. 17, the rotor 230 includes a left blade type and a light blade type, and the first blade 231 is disposed in the same manner as the left blade type and the light blade type. In the case of the second blade 233, the left blade type and the light blade type are positioned to face each other.

As such, the left blade type and the light blade type are opposite to each other and have the same shape. Therefore, only the left blade type is shown and described in the drawings in order to avoid duplication of description.

First, the second blade 233 has a symmetrical shape and is formed such that the incident angle and the projection angle of the compressed fluid are maintained at the same angle at 30 °, respectively (see FIGS. 17 and 22).

In the second blade 233, the compressed fluid injected from the jet nozzle unit 240 is incident on the second blade 233 at 30 ° and output at 20 °, and the rotating body is generated by an impulse force generated at this time. Generate a rotational force of (230).

In addition, the first blade 231 has a left and right asymmetrical shape, twisted downward from the upper end 231a to the lower end 231b, and gradually thickened, and the upper end 231a is twisted at 50 °. The lower end 231b is formed in a structure in which the angle is twisted at 20 ° (see FIG. 23).

In the first blade 231, the compressed fluid guided to the velocity curve diagram unit 250 is incident at 30 ° and output at 20 ° through the guide hole 292 of the velocity guide plate 290. The rotational force of the rotating body 230 is generated by the reaction force generated at this time.

In addition, the pressurized fluid of the thrust nozzle unit (booster) 270 is incident at 30 ° and output at 20 ° through the guide hole 292 of the velocity guide plate 290, and is rotated by the driving force generated at this time. The rotational force of the whole 230 is generated (see FIG. 10).

The second blade 233 has a symmetrical shape and is formed such that the incident angle and the projection angle of the compressed fluid are maintained at the same angle at 30 °, respectively (see FIGS. 14 and 19).

In other words, in the impulse type structure, the relative speed of the compressed fluid at the inlet and the outlet of the second blade 233 is constant, so that the rotational force of the rotor 230 is generated only by the injection pressure of the compressed fluid. However, in the reactionary structure, the relative velocity of the compressed fluid at the inlet and the outlet of the first blade 231 increases, so that the injection pressure of the compressed fluid and the expansion pressure of the compressed fluid are added to generate the rotational force of the rotor 230. In this case, the first blade 231 generates a pulsating force of the impulse type by the compression fluid injection of the thrust nozzle part (booster) 270 as well as the reaction force of the reaction type.

The fixing body 260 is fixed to the both sides of the turbine casing 210 by the usual fastening means, for example, bolt (B), the center of the fixing body 260 can rotate the turbine shaft 220 The bearing portion 264 is installed to support it. The bearing cover 265 is fixed to the bearing portion 264 by a bolt B '.

The fixing body 260 has a discharge part 261 disposed therein for discharging the compressed fluid passing through the first blade 231 by the velocity curve diagram part 250 to the outside of the turbine casing 210. Equipped.

The discharge part 261 of the fixing body 260 is provided with a discharge hole 262 for discharging the compressed fluid passing between the second blade 233 to the outside of the turbine casing 210, the discharge An inclined fixed blade 263 is formed at the inlet of the hole 262 (see FIGS. 25 and 26).

The fixing body 260 'is fixed in the middle of the turbine casing 210, and a bearing portion 264' for rotatably supporting the turbine shaft 220 is installed at the center of the fixing body 260 '. do. The fixture 260 ′ has an outlet portion 261 ′ therein for discharging the compressed fluid passing through the first blade 231 by the velocity curve diagram portion 250 to the outside of the turbine casing 210. ).

The discharge portion 261 ′ of the fixing body 260 ′ is provided with a discharge hole 262 ′ for discharging the compressed fluid passing between the second blades 233 to the outside of the turbine casing 210. At the inlet of the discharge hole 262 ′, an inclined fixed blade 263 ′ is formed (see FIGS. 27 and 28).

An exhaust pipe 219 is connected to the discharge parts 261 and 261 ′, and a turbocharger (T) (see FIG. 1) may be installed in the exhaust pipe 219. The turbocharger T serves to increase the output of the turbine engine using exhaust gas.

The thrust nozzle unit 270 is installed in the turbine casing 210 in a suitable location to further inject a compressed fluid to the first blade 231 to further accelerate the rotating body 230. In this case, the first blade 231 is preferably installed to inject the compressed fluid inclined at a predetermined angle (see FIGS. 1 and 2).

The control unit (C ') is designed to operate by computer programming, through a variety of sensors (not shown), such as a speed sensor, a capacity sensor, a pressure sensor, a temperature sensor, a temperature sensor installed in the turbine casing 210 Detects an operating situation, detects the rotational speed of the rotor 230 in real time, automatically controls the injection of compressed fluid between the jet nozzle unit 240 and the thrust nozzle unit 270, and the turbine shaft 220 In addition to the automatic control of the output, the series of operating conditions are displayed by an indicator (not shown), allowing the operator to confirm turbine operation (see FIG. 17).

It will be described in more detail with respect to the parallel horizontal super power high efficiency hybrid turbine engine automatic control method according to a preferred embodiment of the present invention configured as described above.

In the control unit (C) (C '), the jet nozzle unit 140, 240 allows the high pressure injection of the compressed fluid toward the second blades (133, 233) of the rotating body (130, 230). An impulse force is generated by the high pressure injection of the jet nozzles 140 and 240 to receive the rotation force of the rotors 130 and 230 primarily.

At this time, the incidence angle and the projection angle of the compressed fluid are maintained at the same angle at 30 degrees, respectively, so that the residual compressed fluid passing through the second blades 133 and 233 is not included in the velocity curve diagram portion of the turbine casing 110 and 210 ( 150 to 250 and guide blades 191 and 291 of the velocity guide plates 190 and 290 to the first blades 131 and 231 of the rotors 130 and 230. The reaction force is injected to accelerate the rotors 130 and 230 again.

The relative speed of the compressed fluid increases at the inlet and the outlet of the first blades 131 and 231, so that the injection pressure of the compressed fluid and the expansion pressure of the compressed fluid are added to generate the rotational force of the rotors 130 and 230.

In the control unit (C) (C '), the compressed fluid control valves 117 and 217 adjust the amount of fluid to adjust the compressed fluid flow rate of the jet nozzles 140 and 240, so that the rotating body 130 The rotation of the 230 may be controlled.

If the turbine output is to be increased further (if the thrust is desired), the control unit (C) (C ') is the thrust nozzle section 170, 270 is the pressure of the velocity guide plate 190, 290 High pressure injection into the guide holes (192, 292), and compressed fluid injected into the guide holes (192, 292) to the first blade (131, 231) of the rotating body (130) (230) The impulse force is generated by being injected toward the high pressure, thereby further accelerating the rotors 130 and 230.

The control unit (C) (C ') of course detects the rotational speed of the rotor 130, 230 in real time through a conventional speedometer (not shown) installed inside the turbine casing 110, 210 It detects and feeds back an operating situation through various sensors (not shown), such as a capacity sensor, a pressure sensor, a temperature sensor, and a temperature sensor, and adjusts the compressed fluid control valves 117 and 217 to control the jet nozzle 140. By controlling the 240, the turbine output can be automatically controlled by controlling the speeds of the rotors 130 and 230 and controlling the injection of the compressed fluid of the thrust nozzle units 170 and 270. .

In the present invention, the first turbine engine unit 10 and the second turbine engine unit 20 are described as an example of being arranged in parallel, but the third and fourth engine units (not shown) may be additionally arranged. Of course.

As described above, in the present invention, the first blade (impulse and recoil structure) is formed on the outer surface of the rotating body coupled to the turbine shaft, and the second blade (impulse structure) is formed on the outermost surface, thereby primarily jetting. After the high pressure injection of the pressurized fluid to the second blade at the injection nozzle part, the residual compressed fluid having passed through the second blade is guided to the first blade again by the velocity curve diagram part and injected at high pressure, whereby the rotating body Impulse force is of course accelerated by the reaction force (加速) has the effect of reducing the energy loss.

In addition, the present invention is the first turbine engine unit and the second turbine engine unit is arranged in parallel, the first gear is installed on the turbine shaft of the first turbine engine unit, the second gear is installed on the turbine shaft of the second turbine engine unit And a connecting gear is installed between the first gear and the second gear, and a main turbine shaft is installed in the connecting gear, and the output of the first turbine engine unit and the two turbine engine unit are combined to be output to the main turbine shaft. The turbine output can be doubled.

In addition, the present invention has the effect of increasing the output of the turbine can be further accelerated by selectively spraying the compressed fluid to the first blade of the rotating body in the thrust nozzle unit (booster).

In addition, the present invention is designed so that the control unit is operated by computer programming, it detects the operating situation through various sensors such as speed sensor, capacity sensor, pressure sensor, temperature sensor, temperature sensor, and the like, By detecting and feeding back in real time, the operator automatically controls the jet nozzle section and compressed fluid injection of the thrust nozzle section, automatically controls the output of the turbine shaft, and displays this set of operating conditions with an indicator, allowing the operator to operate the turbine. Make sure to check.

In addition, the present invention has the effect of increasing the fuel efficiency and reduce the air pollution by the exhaust gas by utilizing the exhaust gas by the turbocharger.

As described above, the right of the present invention is not limited to the above-described embodiment, and is defined by the claims, and various modifications can be made within the scope of the claims by those skilled in the art. It is self evident.

10: first turbine engine unit
20: second turbine engine unit
30: connecting gear
31: main turbine shaft
100,200: ultra-power high efficiency composite turbine engine
110,210: turbine casing
115,215: toggle bracket
117,217: compressed fluid supply control valve
119,219: exhaust pipe
120,220: turbine shaft
130,230: rotating body
131,231: first blade
133,233: second blade
140,240: jet nozzle
150,250: Velocity curve diagram part
160,260: stationary
161,161 ', 261,261': outlet
162,162 ', 262,262': discharge hole
163,163 ', 263,263': Fixed blade in bevel
164,164 ', 264,264': Bearing part
170,270: thrust nozzle
C, C ': control unit
190,290: Velocity guide plate
191,291: guide blade
192,292: guide hole

Claims (18)

The first turbine engine unit 10 and the second turbine engine unit 20 are disposed in parallel, and a first gear 121 is installed in the turbine shaft 120 of the first turbine engine unit 10. A second gear 221 is installed on the turbine shaft 220 of the two turbine engine unit 20, and a connecting gear 30 is installed between the first gear 121 and the second gear 221. The main gear shaft 31 is installed in the connecting gear 30 so that the outputs of the first turbine engine unit 10 and the second turbine engine unit 20 are combined and output to the main turbine shaft 31. The first gear 121, the second gear 221, the connecting gear 30 is covered with a gear box 40, a bearing cap 50 is installed,
The first turbine engine unit 10 includes a plurality of turbine casings 110 formed in a cylindrical shape and horizontally positioned; A turbine shaft 120 horizontally positioned inside the turbine casing 110 and rotatably installed; At least one rotating body (130) fixed to the turbine shaft (120), wherein a plurality of first blades (131) are formed at an outer shell, and a plurality of second blades (133) are formed at the outermost shell; A jet nozzle unit (140) installed inside the turbine casing (110) to inject high pressure to the second blade (133); A velocity curve diagram unit 150 formed at equal intervals in the turbine casing 110 to guide and spray the residual compressed fluid passing through the second blade 133 in the direction of the first blade 131; The turbine fluid is fixed to the turbine casing 110 to rotatably support the turbine shaft 120, and the compressed fluid passing through the first blade 131 by the velocity curve diagram part 150 is transferred to the turbine casing ( 110, the fixing body 160, 160 'is formed in the discharge portion (161, 161') to discharge to the outside; And a plurality of thrust nozzle units 170 installed in the turbine casing 110 to accelerate the rotating body 130 by spraying compressed fluid onto the first blade 131.
The second turbine engine unit 20 includes a plurality of turbine casings 210 formed in a cylindrical shape and horizontally positioned; A turbine shaft 220 horizontally positioned inside the turbine casing 210 and rotatably installed; At least one rotor 230 fixed to the turbine shaft 220 and having a plurality of first blades 231 formed at an outer side thereof and having a plurality of second blades 233 formed at the outermost side thereof; A jet nozzle unit (240) installed inside the turbine casing (210) for high-pressure injection of compressed fluid into the second blade (233); A velocity curve diagram unit 250 formed at equal intervals in the turbine casing 210 to guide and spray the residual compressed fluid passing through the second blade 233 toward the first blade 231; The turbine fluid is fixed to the turbine casing 210 to rotatably support the turbine shaft 220, and the compressed fluid passing through the first blade 231 by the velocity curve diagram part 250 is the turbine casing ( 210 is a fixed body 260 (260 ') having a discharge portion (261, 261') is formed inside to discharge to the outside; And a plurality of thrust nozzle parts 270 installed on the turbine casing 210 to accelerate the rotating body 230 by spraying a compression fluid on the first blade 231.
Velocity guide plate 190 is fixedly installed in a position adjacent to the velocity curve diagram portion 150 to guide and eject the residual compressed fluid in the direction of the first blade 131, and the turbine shaft 120 A control unit (C) for sensing the rotational speed of the rotating body 130 so as to control the output and for automatically controlling the injection of compressed fluid of the jet nozzle unit 140 and the thrust nozzle unit 170, and the turbine Control unit (C) for detecting the rotational speed of the rotating body 230 to control the output of the shaft 220 and automatically controls the injection of compressed fluid of the jet nozzle unit 240 and the thrust nozzle unit 270 Parallel horizontal super-powered high efficiency composite turbine engine including '). The method of claim 1,
The horizontal horizontal super-power high efficiency hybrid turbine engine, characterized in that the first blade (131) has a left and right asymmetrical shape, the second blade (133) has a left and right symmetrical shape. The method of claim 2,
The first blade 131 has an impulse and rebound blade structure, the second blade 133 is a parallel horizontal super-power high efficiency hybrid turbine engine, characterized in that formed in the impulse blade structure. The method of claim 1,
Discharge holes 161 and 161 ′ of the fixing bodies 160 and 160 ′ may include discharge holes for discharging the compressed fluid passing between the second blades 133 to the outside of the turbine casing 110. 162 and 162 ', and parallel horizontal super-powered high efficiency hybrid turbine engines are characterized by inclined fixed blades 163 and 163' formed at the inlet of the discharge holes 162 and 162 '. . The method of claim 1,
The horizontal horizontal super-power high efficiency hybrid turbine engine, characterized in that the toggle bracket 115 is installed inside the turbine casing 110 to prevent the back flow of the compressed fluid injected from the jet nozzle unit 140. The method of claim 1,
The thrust nozzle unit 170 is a horizontal horizontal super-power high efficiency hybrid turbine engine, characterized in that installed in the turbine casing (110) to inject the inclined fluid at a predetermined angle to the first blade (131). The method of claim 1,
Parallel horizontal super-power high efficiency composite turbine engine, characterized in that the bearing portion (164) (164 ') for supporting the turbine shaft 120 is installed at the center of the stationary body (160, 160'). The method of claim 1,
Parallel jet type super-powered high efficiency hybrid turbine engine, characterized in that the jet nozzle unit 170 is provided with a compressed fluid control valve 117 for controlling the supply amount of the compressed fluid. The method of claim 1,
The horizontal horizontal super power high efficiency hybrid turbine engine, characterized in that the first blade (131) and the second blade (133) are formed on the rotating body at a predetermined interval from each other. The method of claim 1,
The velocity guide plate 190 may not only generate a reaction force by the residual compressed fluid guided by the velocity curve diagram unit 150 but also generate an impulse force by the compressed fluid injected from the thrust nozzle unit 170. Parallel horizontal super-power high efficiency hybrid turbine engine characterized in that the structure. The method of claim 10,
The guide blades 191 of the velocity guide plate 190 have a thicker inlet portion and become thinner toward the outlet portion, and the guide hole 192 has a narrower outlet portion than the inlet portion. Equilibrium super power high efficiency composite turbine engine. The method of claim 1,
The first blade 131 has a right and left asymmetrical shape, twisted downward from the upper end 131a to the lower end 131b and gradually thickened, and the upper end 131a is twisted at 50 ° and lower end ( 131b) A horizontal horizontal super-powered high efficiency hybrid turbine engine, characterized in that it is formed in a structure twisted at an angle of 20 °. The method of claim 12,
In the case of the first blade 131, the compressed fluid guided to the velocity curve diagram unit 150 is incident at 30 ° and output at 20 ° through the guide hole 192 of the velocity guide plate 190. Parallel horizontal, ultra-powered, highly efficient hybrid turbine engine. The method of claim 1,
The compressed fluid injected from the thrust nozzle part (booster) 170 is incident to 30 ° through the guide hole 192 of the velocity guide plate 190 and is outputted at 20 ° horizontal super power high efficiency Composite turbine engine. The method of claim 1,
The second blade (133) has a horizontally symmetrical shape, parallel horizontal super-power high efficiency hybrid turbine engine, characterized in that the incidence angle and the projection angle of the compressed fluid is formed to maintain the same angle at 30 degrees, respectively. The method of claim 1,
An exhaust pipe 119 is connected to the discharge parts 161 and 161 ′, and a horizontal horizontal super power is installed in the exhaust pipe 119 by a turbocharger (turbocharger, turbo-supercharger) T. High efficiency composite turbine engine. The method of claim 1,
Parallel horizontal candle further comprises a velocity guide plate 290 fixedly installed at a position adjacent to the velocity curve diagram portion 250 to guide and eject residual compressed fluid in the direction of the first blade 231. Power efficient high efficiency turbine turbine engine. The method of claim 1,
The first blade 231 has a right and left asymmetrical shape, the second blade 233 has a horizontal horizontal super power high efficiency hybrid turbine engine, characterized in that the.

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