KR890002660B1 - Plural gas-turbine engine system - Google Patents

Abstract

The system comprises a combustor (100) including fuel injection nozzle (101), an igniter (102), a combustion block (120), and a combustion cover block (121), a first helium gas expansion pipe (170) enclosing the combustor, a first helium gas expander (150) with the first hollow cylindrical helium gas expansion tank (160), a first helium gas expansion block (110) and an expansion cover block (111), a centrifugal compressor connected to a 2-step power turbine (240) driven by burned gas, a second helium gas expander (200), a first helium gas turbine (250) driven by the helium gas of the first helium gas expander, a first helium gas compressor (280), and a second helium gas turbine (251) connected to the second helium gas compressor.

Description

Combined gas turbine engine system

1 is a schematic diagram of a combined gas turbine engine system according to the present invention.

2 is a schematic diagram showing the connection and structure of the first and second helium gas expansion device, the gear box, the first and second helium gas compressor and the turbine of the present invention.

3 is a partially cut perspective view of the present invention showing the details of the combustion device and the first helium gas expansion device.

Figure 4 is a partially cut cross-sectional view showing the connection between the centrifugal compressor and the two-stage power turbine of the present invention.

5 is a cross-sectional view of the air heat exchanger along the line V-V in FIG.

* Explanation of symbols for main parts of the drawings

100: combustion device 101: fuel injection nozzle

102: ignition device 109: exhaust gas pipe

110: first helium gas expansion device 111: expansion cover block

120: combustion block 121: combustion cover block

130: air heat exchanger 150: first helium gas expansion device

155: helium gas heat exchanger 160: the first hollow park cylindrical helium gas expansion tank

161: heating fin 162: gas introduction pipe

163: gas discharge pipe 164: cooling pipe

165: cooling fin 170: first helium gas expansion pipe

200: second helium gas expansion device 205: second helium gas expansion block

210: second helium gas expansion tank 220: second hollow park cylindrical helium gas expansion tank

230: second helium gas expansion pipe 240: two-stage power turbine

242: power transmission shaft 245: centrifugal compressor

250 and 251: first and second helium gas turbines

256: power transmission shaft 260: gearbox

261: center gear 262, 263: torque transmission shaft

264, 265: Turbine power gear 266, 267: Transmission gear

280, 281: first and second helium gas compressors

300: output gear 301: starting motor

302: generator 303: compressed air generator

304: compressed air driven motor 305: output side

308: transmission gear 309: rotary gear

310: reduction gear box

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a new multi-gas turbine engine system that improves the thermal efficiency of a gas turbine engine. In particular, a high-temperature, high-pressure helium gas expanded by the heat of exhaust gas burned inside and outside a combustion block of a turbine engine, and a power turbine In the multi-gas turbine engine system, the output of a helium gas turbine driven by high-temperature, high-pressure helium gas expanded by the heat of exhaust gas that drives the blade at high speed is added to the output of the power turbine to increase thermal efficiency and produce high power. It is about.

Conventional gas turbine engines usually consist of one open cycle, compressing air in a compressor and injecting fuel into the compressed air to explode and expand the high-temperature and high-pressure exhaust gas in the combustion chamber, and the power turbine is discharged from the exhaust gas. It was to get power by rotating. However, the conventional gas turbine engine has a high fuel consumption, low thermal efficiency, extremely low partial load rate at low speed rotation, and uses a portion of the power turbine's output to compress air, thereby reducing the pay output.

In addition, in order to improve the thermal efficiency of the gas turbine engine, the pressure ratio and the inlet temperature of the power turbine must be increased. However, if the pressure ratio and the turbine inlet temperature are increased, the turbine is too heated, causing problems in cooling or metal materials of the turbine. Therefore, it is difficult to solve these problems comprehensively and fundamentally, and the output increase is very difficult. Particularly, in a turbine engine of a vehicle, a partial load operation time is longer than a total load operation time, and there is a big problem in reducing fuel consumption rate at a partial load.

Due to the above problems, an object of the present invention is to recover the useless heat energy lost by expanding the helium gas with the heat energy of the combustion gas lost to the outside in the high temperature and high pressure combustion chamber to burn, and burned high temperature and high pressure After rotating the power turbine blades at high speed with exhaust gas, the helium gas is expanded again with high temperature and high pressure exhaust gas to recover the heat energy of exhaust gas before it is released into the atmosphere. It is to save fuel and improve thermal efficiency, and to preheat the intake air to high temperature by the heat of exhaust gas, and to make the high-temperature intake air to high pressure by centrifugal compressor connected coaxially with the power turbine and send it to the combustion chamber. And a combustion device composed of an ignition device, a combustion block and a combustion cover block. A first helium gas expansion device comprising a first helium gas expansion pipe, a first hollow cylindrical helium gas expansion tank, a first helium gas expansion block, and an expansion cover block that are enclosed as a wrap, and exhaust gas burned in a combustion chamber in a continuous block; A second stage turbine and a centrifugal compressor coaxially connected to the second stage turbine, a second helium gas expansion device for expanding the helium gas with the exhaust gas after driving the second stage power turbine, and the first helium gas. The first helium gas turbine, which is driven at a high speed by the helium gas expanded at a high temperature and high pressure in the expansion device, is coaxial with the first helium gas turbine and heat-exchanged and cooled to send the first helium gas expansion device to the first helium gas expansion device. Coaxial with a first helium gas compressor, a second helium gas turbine driven by helium gas expanded at high temperature and high pressure in a second helium gas expansion device, and a second helium gas turbine On and to provide a composite gas turbine engine system of the second helium gas compressor, such as sending to the second helium gas expansion device by compressing the cooled helium gas is a heat exchanger.

A feature of the present invention is to install the first helium gas expansion device on the inside and outside of the combustion block to recover the heat energy released into the atmosphere through the combustion block of the heat energy of the exhaust gas burned in the combustion chamber, at the same time two-stage power turbine wing After the rotation of the exhaust gas before the exhaust gas is discharged into the atmosphere, the second helium gas expansion device recovers the thermal energy of the exhaust gas to improve the output of the engine.

Another feature of the present invention is to drive the first and second helium gas turbines with the heat energy recovered through the helium gas in the first and second helium gas expansion device, and transmits the high-speed rotational power of the turbine to the power transmission shaft of the engine At the same time, the first and second helium gas compressors, which are coaxial with the first and second helium gas turbines, compress the helium gas rotated by the first and second helium gas turbines and then return to the first and second helium gas expansion devices. To send.

Another feature of the invention is that the invention consists of one open cycle and two closed cycles. In other words, the present invention makes a new intake air at a high temperature through an air heat exchanger and sends it to a centrifugal compressor, compresses it at a high pressure from a compressor and sends it to a combustion chamber of a combustion device, and rotates a two-stage power turbine with explosive expansion gas at high temperature and high pressure. One open cycle, which is discharged to the atmosphere through exhaust gas pape of air heat exchanger, is mixed with air and fuel in the combustion chamber of the combustion device and expanded at high temperature and high pressure to rotate the turbine blade of the first helium gas turbine at high speed. The first helium gas closed-circulation cycle, which is later cooled in a helium gas heat exchanger, and the cooled helium gas is compressed in the first helium gas compressor and sent back to the first helium gas expansion device: explodes at high temperature and high pressure in the combustion chamber of the combustion device. Exhaust before the expanded exhaust gas rotates the two-stage power turbine at high speed and is released into the atmosphere Due to the heat energy of the gas, the helium gas in the second helium gas expansion device expands at high temperature and high pressure, rotates the turbine blade of the second helium gas turbine at high speed, and then cools in the helium gas heat exchanger. The cooled helium gas is cooled in the second helium. Composed of a second helium gas closed circulation cycle is compressed in the gas compressor and sent back to the second helium gas expansion device.

An advantage of the present invention is to drive a vehicle or a small ship with the output of the power turbine and the output of helium gas turbine rotated with helium gas, the marginal output can be stored through the generator or compressed air generator to start and restart And it can be used when the need of high power, and in particular, in the turbine turbine prime mover for the vehicle has more partial load operation time than full load operation time to provide an engine with excellent partial load characteristics while improving the thermal efficiency to the maximum.

Other objects, features and advantages of the present invention will become apparent from the following description.

1 shows the overall system diagram of the combined gas turbine engine system according to the present invention. The composite gas turbine engine system of the present invention includes a combustion device 100, a first helium gas expansion device 150, a centrifugal compressor 245, a two-stage power turbine 240, a second helium gas expansion device 200, The first and second helium gas turbine 250, 251, the gear box 260, the first and second helium gas compressor 280, 281, the reduction gear box 310 and the like.

As shown in FIGS. 1 and 3, a combustion device 100 is formed in the first helium gas expansion device 150, and a combustion block 120 in which air and fuel are mixed and burned in the combustion device 100. ) And a combustion cover block 121 protruding from the support 103 having a fuel injection nozzle 101 for injecting fuel and covering the upper portion of the combustion block 120. Combustion block 120 has a plurality of air intake holes 104 for sucking the new compressed air into the combustion chamber 105 evenly from the top to the bottom of the combustion block 120 to allow complete combustion. do.

The first helium gas expansion device 150 seals the first helium gas expansion block 110 and the upper portion of the first helium gas expansion block, which are mounted to surround the combustion block at a predetermined interval. A first hollow cylinder-type helium gas expansion tank 160 for expanding helium gas in a space between the covering expansion cover block 111, the combustion block 120, and the first helium gas expansion block 110, and the combustion block 120. ) Through the space between the first hollow cylinder cylindrical helium gas expansion tank 160 and enters the combustion chamber 105 from the lower portion of the combustion block 120 and back up to the combustion cover block 121 and the expansion cover block 111. The first helium gas expansion pipe 170 for expanding the helium gas while passing through it is configured. The fuel injection nozzle 101 is inserted through the center hole of the expansion cover block 11 and the center hole of the support part 103 in the upper center of the combustion cover block 121 and injects fuel into the combustion chamber 105. It is supposed to be.

The support part 103 formed at the upper center of the combustion cover block 121 is inserted into the recess formed at the lower center of the expansion cover block 111 so as to withstand shaking and vibration during operation or operation of the engine. Securely support (101). The air suction hole 104 is drilled through the combustion block 120, but is also drilled around the support part 103 of the combustion cover block 121, so that the mixed gas of fuel and air is burned from the top to the bottom of the combustion chamber 105. Inflate. In addition, the ignition device 102 inserted through the combustion block 120 and the upper portion of the first helium gas expansion block 110 ignites the mixed gas in the combustion chamber 105 once, so that the mixed gas continues to expand and expand. As shown in FIG. 3, the helium gas passing through the first hollow cylindrical helium gas expansion tank is introduced into the lower portion of the first hollow park cylindrical helium gas expansion tank 160 through two gas introduction pipes 162, and the expansion tank ( Helium gas expanded to a high temperature in the 160 is to exit through the two gas discharge pipe 163 on the upper portion of the expansion tank at a right angle with the two gas introduction pipe 162. In addition, a plurality of heating fins 161 protruding in the axial direction are formed inside the first hollow park-type helium gas expansion tank 160, and are configured to absorb the heat energy emitted to the outside from the combustion chamber 105 to the maximum.

In this way, the explosion-expanded exhaust gas rotates the two-stage power turbine blades 241 of the two-stage power turbine 240 at high speed via the exhaust gas passage 107. The two-stage power turbine 240 is mounted on the power transmission shaft 242, so the centrifugal compressor 245, which supplies new hip air into the combustion chamber 105, is also mounted on the power transmission shaft 242. The power turbine 240 and the centrifugal compressor 245 rotate at the same speed.

A second helium gas expansion device 200 is installed downstream of the two-stage power turbine 240. The second helium gas expansion device 200 includes a second helium gas expansion block 205, a second helium gas expansion tank 210 positioned in the center of the second helium gas expansion block 205, and a second helium gas expansion. The space between the second hollow cylinder cylindrical helium gas expansion tank 200, the second helium gas expansion block 205 and the second hollow cylinder cylindrical helium gas expansion tank 220, which is located at a slight distance from the block 205, is formed. The second helium gas expansion tank 220 is composed of a second helium gas expansion pipe 230 that passes through the heating fins 223 protruding in the axial direction from the inside.

As shown in FIGS. 1 and 3, helium gas expanded in the second helium gas expansion tank 210 located in the center of the first helium gas expansion block 205 is gas at the downstream end of the expansion tank 210. It is expanded to some extent while approaching the expansion tank 210 through the introduction pipe 211, and enters the expansion tank 210 at an upstream end of the expansion tank 210. The expansion tank 210 is provided with a plurality of heating fins 213 radially on the outer circumferential surface to maximize the heat energy of the exhaust gas, expands by transferring heat to helium gas and is discharged through the gas discharge pipe 212. .

In addition, the second helium gas expansion tank 220 inside the second helium gas expansion block 205 has a plurality of heating fins 223 protruding in the axial direction to absorb the heat energy of the exhaust gas. Therefore, the helium gas in the second hollow cylindrical helium gas expansion tank 220 is introduced through the two gas introduction pipe 221, and after expanding in the expansion tank 220, the two gas introduction pipe 221 and the perpendicular direction It is discharged through the two gas discharge pipe 222 mounted as.

The second helium gas expansion pipe 230 introduced from the downstream side to the upstream side between the second helium gas expansion block 205 and the second hollow park cylindrical helium gas expansion tank 220 is disposed inside the expansion tank 220. The helium gas in the expansion pipe 230 is expanded while passing downstream between the heating fins 223.

As described above, the exhaust gas that delivers thermal energy to the second helium gas expansion device 200 still has a certain pressure and temperature, and is discharged into the atmosphere after heat exchange in the air heat exchanger 130 through the exhaust gas passage 108. As shown in FIGS. 1 and 5, the air heat exchanger 130 includes an air heat exchanger block 133, a plurality of exhaust gas pipes 109 installed in the block in the longitudinal direction (axial direction), and To the exhaust gas inlet 112 and the exhaust gas outlet 113 for introducing and discharging the exhaust gas, and the air inlet 131 and the air outlet 132 for introducing and discharging new intake air to be sent to the centrifugal compressor 245. Consists of. The cross-sectional area of the exhaust gas pipe 109 is large enough to exhaust the exhaust gas flowing through the exhaust gas passage 108 without great resistance.

As shown in FIG. 1 and FIG. 4, the centrifugal compressor 245, which heat-exchanges in the air heat exchanger 130 and compresses the new suction air, which has become a high temperature, has a compressor wing 246, a compressor inlet 247, and compressed air. 106 and the like. Furthermore, the power transmission shaft 242 is equipped with a centrifugal compressor 245 and a two-stage power turbine 240 so as to rotate at the same rotational speed, so the centrifugal compressor has sufficient suction air to the combustion chamber 105 in the combustion device 100. Will be supplied.

As shown in FIG. 1 and FIG. 2, the power transmission shaft 256 integrally coupled with the power transmission shaft 242 is connected to the first and second helium gas turbines 250 through the gearbox 260, ( 251 and first and second helium gas compressors 280 and 281 are mounted. A center gear 261 is mounted on the circumference of the power transmission shaft 256 in the gearbox 260 and is connected to the turbine power gears 264 and 265 via the transmission gears 266 and 267. . The first helium gas turbine 250, the compressor 280, the second helium gas turbine 251, and both ends of the rotational force transmission shafts 262 and 263 equipped with the turbine power gears 264 and 265, respectively. Since the compressor 281 and are provided, it is made to rotate at the same rotation speed. On the other hand, the rotating shaft of the starting motor 301 can be connected to the shaft on which the transmission gear 266 is mounted, so that the rotary shaft of the starting motor and the central shaft of the transmission gear 266 are connected at the start, and then started after starting. The rotating shaft of the motor 301 and the central shaft of the transmission gear 266 are separated from each other.

One end of the power transmission shaft 256 is connected to the power transmission shaft 242, and the other end of the power transmission shaft 256 is equipped with a compressed air drive motor 304 and the reduction gear box 310 and the reduction gear box. The output shaft 305, the compressed air generator 303, the generator 302, and the like are mounted therethrough. The rotational force of the helium gas turbine and the two-stage power turbine acting on the power transmission shaft 256 are decelerated by the reduction gear box 310 to be output to the output shaft 305. The output gear 300 of the output shaft 305 is connected to the rotary gear 309 through the transmission gear 308, the rotary gear 309 is mounted, the compressed air generator 303 and the generator 302 on both ends of the rotary shaft ) Is installed. Therefore, as the output gear 300 rotates, the rotary gear 309 rotates, so that the generator 302 at one end of the rotary gear 309 generates and stores power, and the compressed air generator at the other shaft end. 303 is for making compressed air. The compressed air produced by the compressed air generator 303 is continuously stored in the compressed air tank 306 and the compressed air auxiliary tank 307, and one end of the power transmission shaft 256 with the compressed air stored at the same time or when high power is required. It is configured to drive the compressed air driven motor 304 installed in the.

The combustion device 100, the first helium gas expansion device 150, the centrifugal compressor 245 and the two-stage power turbine 240, the second helium gas expansion device 200, the air heat exchanger 130, and the like are formed. The structure, construction, and operation of the open cycle are described.

Hereinafter, the first helium gas expansion device 150, the second helium gas expansion device 200, the first and second helium gas turbines 250, 251, the first and second helium gas compressors 280, (281), the structure, construction, and operation of two closed circulation cycles formed by the helium gas heat exchanger 155 and the like will be described.

One hermetic circulation cycle, that is, the first helium gas hermetic circulation cycle, includes the first helium gas expansion device 150, the first helium gas turbine 250, the first and second helium gas compressors 280, and the classifier 251. , The combiner 152, the helium gas tank 153, the helium gas auxiliary tank 154, and the second helium gas sealed circulation cycle includes the second helium gas expansion device 200 and the second helium gas turbine ( 251, the second helium gas 281, the classifier 201, the combiner 202, the helium gas tank 203, the helium gas auxiliary tank 204, and the like. In addition, the helium gas heat exchanger 155 cools the helium gas passing through the first and second helium gas closed circulation cycles, and the coolant in the helium gas heat exchanger 155 cooling the helium gas is radiated from the radiator 315. 316 and the cooling fan 317 are forcibly supplied to the water pump 318.

As shown in FIG. 1 and FIG. 2, first, in the first helium gas closed-circulation cycle, when the mixed gas of air and bridge is exploded and expanded in the combustion chamber 105 of the combustion apparatus 100, Thermal energy of the exhaust gas discharged to the surroundings through the combustion block 120 is helium in the first helium gas expansion tank 160 and the first helium gas expansion pipe 170 of the first helium gas expansion device 150. Inflate the gas to high pressure. The helium gas expanded at such a high pressure is collected in the combiner 152 and sent to the helium gas inlet 252 of the first helium gas turbine 250. The helium gas introduced through the helium gas inlet 252 is rotated at two speeds of the turbine blades at high speed, and then is sent to the gas inlet 158 of the helium gas heat exchanger 155 through the helium gas outlet 254. The helium gas cooled by the cooling fins 165 of the helium gas heat exchanger 155 and exited through the gas outlet 159 is formed of the first helium gas compressor 280 coaxially with the first helium gas turbine 250. It is sent to helium gas inlet (282). The helium gas compressed at low temperature and high pressure in the first helium gas compressor 280 and exited through the helium gas outlet 284 is separated by the classifier 151 in the first helium gas expansion tank of the first helium gas expansion device 150. 160 and the first helium gas expansion pipe (170). The helium gas that is naturally lost while circulating in this way is supplemented in the helium gas tank 153 and the helium gas auxiliary tank 154 so that the helium gas in the first helium gas closed circulation cycle is always maintained at a certain pressure.

In the second helium gas closed circulation cycle, the mixed gas of air and fuel is exploded and expanded into a high temperature and high pressure exhaust gas in the combustion chamber 105 of the combustion apparatus 100, and the exhaust gas is a two-stage power turbine 240. After driving at a high speed is sent to the second helium gas expansion device (200). The helium gas in the second helium gas expansion tank 210, the second hollow cylinder cylindrical helium gas expansion tank 220, and the second helium gas expansion pipe 230 of the second helium gas expansion device 200 is applied to the heat of the exhaust gas. By high pressure. The helium gas expanded at high pressure in the second helium gas expansion device 200 is collected at the combiner 202 and sent to the helium gas inlet 253 of the second helium gas turbine 251. The helium gas introduced through the helium gas inlet 253 is driven at a high speed by a two-stage turbine blade and is sent to the gas inlet 158 of the helium gas heat exchanger 155 through the helium gas outlet 255. The helium gas introduced through the gas outlet 158 of the helium gas heat exchanger 155 is cooled by the plurality of cooling fins 165 and then discharged through the gas outlet 159 to be discharged through the second helium gas turbine 251. It is sent to the helium gas inlet 283 of the second helium gas compressor 281 provided coaxially. The helium gas, which is compressed at a low temperature and high pressure in the second helium gas compressor 281 and exits through the helium gas outlet 285, is separated by the classifier 201 from the second helium gas expansion tank 210 of the second helium gas expansion device 200. ) And the second hollow cylinder cylindrical helium gas expansion tank 220 and the second helium gas expansion pipe (230). The helium gas which is naturally lost while circulating in this way is supplemented in the helium gas tank 203 and the helium gas auxiliary tank 204 so that the helium gas in the second helium gas closed circulation cycle is always maintained at a certain pressure.

Meanwhile, the helium gas heat exchanger 155 for cooling the helium gas in the first and second helium gas closed circulation cycles discharges the two helium gas inlets 158 for introducing helium gas and the cooled helium gas for cooling. Two helium gas outlets 1759, a cooling pipe 164 for cooling the helium gas introduced through the helium gas inlet 158, and a plurality of mounted at right angles to the longitudinal direction of the cooling pipe in the circumference of the cooling pipe It is formed of a cooling fin 165, a water inlet 156 and a water outlet 157 for introducing and discharging cooling water. The devices for supplying the cooled coolant to the helium gas heat exchanger 155 are the radiator 315, the electric motor 316, the cooling fan 317 and the water pump 318, and the coolant cooled by the devices is water It is introduced into the helium gas heat exchanger 155 through the inlet 156 to cool the cooling fin 165 and return to the radiator 315 through the water outlet 157.

The operation of the combined gas turbine engine system having the structure, construction, and operation of the present invention as described above will be described below.

First, at start-up, power is supplied to the starter motor 301 to drive the starter motor 301. The rotational force of the starting motor 301 is transmitted to the power transmission shaft 256 of the center gear 261 via the transmission gear 266 of the gearbox 260 connected to the starting motor. The power transmission shaft 242 integrally coupled to this shaft rotates together. Therefore, the two-stage power turbine 240 mounted on the power transmission shaft 242 and the centrifugal compressor 245 rotate to supply compressed air into the combustion chamber 105 of the combustion apparatus 100, and at the same time the fuel injection nozzle 101 It starts to inject fuel. At this time, the ignition device 102 ignites the mixed gas of fuel and air, and by this ignition, the high-temperature, high-pressure exhaust gas rotates the second-stage power turbine blade 241 of the two-stage power turbine 240, and then the second helium Pass the gas expansion device (200).

In this initial starting state, the first and second helium gas turbines 250 and 251 and the first and second helium gas compressors 280 and 281 are continuously rotated by the starting motor 301. Within 10 to 15 seconds after the engine is started, the first helium gas expansion device 150 inside and outside the combustion block 120 of the combustion device 100 normally expands the helium gas.

In this manner, the helium gas expands and circulates normally, and the first helium gas turbine 250 and the compressor 280 continue to rotate to rotate the power transmission shafts 242 and 256 at high speed. In addition, the high-temperature, high-pressure exhaust gas generated in the combustion chamber rotates the two-stage power turbine blade 241 at high speed, and sufficiently transfers the heat energy of the exhaust gas to the second helium gas expansion device 200 and passes the air heat exchanger 130. Emissions to the atmosphere. Accordingly, the helium gas in the second helium gas expansion device 200 expands and circulates, and the second helium gas turbine 251 and the compressor 281 also continue to rotate, so that the power transmission shafts 242 and 256 at higher speeds. Will rotate.

As described above, when the multi-gas turbine engine system of the present invention operates normally, the connection between the starting motor 301 and the transmission gear 266 is separated and cuts off the power supply to the starting motor. Exhaust gas exploded and expanded at high temperature and high pressure by igniting a mixture of air and fuel rotates the blades of a two-stage power turbine, and simultaneously transfers heat energy of the exhaust gas to the first and second helium gas expansion devices, and then passes through the air heat exchanger to the atmosphere. One open cycle and two helium gas closed circulation cycles through which the helium gas expanded in the first and second helium gas expanders pass through the first and second helium gas compressors and the turbine are operated normally. Output through 256 and the reduction gear box 310 is output to the output shaft (305). In addition, the compressed air generator 303 and the generator 302 at both ends of the rotary gear 309 connected to the output gear 300 through the transmission gear 308 to generate and store the compressed air and the compressed air generator is compressed The air driving motor is driven to add rotational force to the power transmission shaft 256 and the generator supplies power to the starting motor at startup.

As described above, the composite gas turbine engine system of the present invention installs a closed circulation cycle helium gas expansion device, a turbine, and a compressor in an open cycle gas turbine engine to increase the rotational force of the power turbine, maximize thermal efficiency, and partially load This has the effect of preventing the engine from falling.

In addition, under partial load, the compressed air made by the compressed air generator is used to drive the compressed air drive motor to add rotational force to the power transmission shaft, thereby reducing the maximum power reduction and maintaining the rotational force of the power turbine.

This engine system maintains a large rotational force by a helium gas sealed cycle of helium gas with a pressure of 180 to 200㎏ / ㎠ during no load operation or low speed operation. It can be used when needed or when restarting. In addition, helium gas has a low friction loss, a high operating pressure, and a high density, so that a large output can be produced even if the engine size of the closed cycle is small.

The engine of the present invention-combined gas turbine engine system has a small torque variation, low vibration, high speed operation, and large torque.

As described above, it will be apparent that the present invention can be variously modified and changed without departing from the spirit of the present invention with reference to the detailed description and the accompanying drawings.

Claims (3)

A combined gas turbine engine system comprising: a combustion device, first and second helium gas expansion devices, a centrifugal compressor, a two-stage power turbine, first and second helium gas compressors, first and second helium gas; It consists of auxiliary devices such as turbines and other helium gas heat exchangers, air heat exchangers, compressed air generators, generators, compressed air driven motors, starting motors, and the combustion device has a plurality of air suction holes in the main wall and a combustion chamber inside. A combustion block forming a combustion block, a combustion cover block covering the upper portion of the continuous block, the combustion cover block having a plurality of air suction holes around the support portion of the upper center portion, a fuel injection nozzle inserted through the center hole in the support portion of the combustion cover block; The first helium gas expansion device comprises a first helium gas expansion block and a first helium gas expansion block which are positioned at a distance to the outside of the combustion block. An expansion cover block that seals and covers the upper portion of the first cylinder, a first hollow cylinder type helium gas expansion tank installed in a space between the combustion block and the first helium gas expansion block, and expands the helium gas; and a combustion block and the first hollow cylinder type helium gas. Between the expansion tank is introduced between the plurality of heating fins installed on the inner wall of the first hollow-cylinder type helium gas expansion tank, and enters the combustion block from the bottom of the combustion block and expands the helium gas as it rises up along the inner wall of the combustion block. The second helium gas expansion device comprises a first helium gas expansion pipe, a second helium gas expansion block, a second helium gas expansion tank at the center of the second helium gas expansion block, and a second helium gas expansion block. It is introduced between the second helium gas expansion tank near the inner wall, the second helium gas expansion block and the second helium gas expansion tank, and the second helium gas cylinder type. Consists of the second helium gas expansion pipe from the upper side of the helium gas expansion tank into the inside of the second helium gas expansion tank and through a plurality of heating fins mounted on the inner wall of the helium gas expansion tank. And a centrifugal compressor and a two-stage power turbine are mounted together on the power transmission shaft and rotated at the same rotational speed, and the first helium gas compressor and the turbine, the second helium gas compressor, and the turbine are mounted on the same shaft and have the same rotational speed. The helium gas is compressed and sent to each helium gas expander in the compressor, and each helium gas is driven by the expanded helium gas in the expander, and is supplied from the auxiliary device to the helium gas heat exchanger. Cooling the helium gas, an air heat exchanger is mounted on the outlet side of the second helium gas expansion device and It exchanges heat with heat energy of exhaust gas emitted into the atmosphere and supplies it to the centrifugal compressor, and the compressed air generator is driven by the output shaft marginal output to make a large amount of compressed air, and the generator generates electricity with the marginal output of the output side and can be used at start-up. The compressed air drive motor is driven by the compressed air produced by the compressed air generator to supply additional rotational force to the power transmission shaft, and the starting motor is driven by electricity such as a generator to rotate the power transmission shaft and the rotational force transmission shaft at startup. Combined gas turbine engine system, characterized in that configured According to claim 1, wherein the centrifugal compressor and the two-stage power turbine is mounted on the same axis so that the air compressed in the centrifugal compressor is widely distributed from the top to the bottom of the combustion block and the air in the combustion cover block support And a mixed gas of fuel injected into the combustion chamber through the suction hole and into the combustion chamber through the fuel injection nozzle to be first ignited by the ignition apparatus and continue to explode. The engine of claim 1, wherein the starting motor rotates the power transmission shaft and the rotational force transmission shaft through the gearbox until the engine is normally operated, and the starting motor disconnects the connection from the gearbox after the engine is started. Composite gas turbine engine system.

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