Gas turbine engine system fed by depleted fuel

FIELD: machine building.

SUBSTANCE: gas turbine system fed by depleted fuel comprises compressor, first catalytic chamber, turbine, recuperator, channel burner and extra device to feed auxiliary fuel arranged on compressor side to increase fuel concentration in the mix by adding extra auxiliary fuel in the mix. Compressor compresses aforesaid air-fuel mix with concentration equal to or lower than ultimate inflammability to obtain compressed gas. First catalytic combustion chamber allows combusting compressed gas by catalytic oxidation. Turbine may be driven by gas fed from first catalytic combustion chamber. Recuperator heats compressed gas by turbine exhaust gas while compressed gas is forced from compressor into said chamber. Channel burner is arranged between turbine and recuperator to combust exhaust gas with the help of auxiliary fuel in plasma burning.

EFFECT: higher efficiency, simplified design, ruled out fuel gas loss.

7 cl, 3 dwg

 

The technical field

The present invention relates to a gas turbine system with power depleted fuel intended for the use of the combustible component contained in such a mixture as the fuel for this system, by summing up the mixture in the engine system, in which receive the mixture, for example, by mixing air with a low-calorie gas, such as biogas from municipal solid waste (landfill gas)generated in landfills, or the like, and/or so-called CMM (coal mine methane), gas derived from coal mines or the like, controlling the concentration of this mixture to a level equal to or more than lower than the limit of Flammability to prevent unintended ignition of such a mixture when it is compressed by the compressor of this system.

The level of technology

In the traditional technology was known gas turbine designed for use methane component contained in a mixture, such as fuel for her, the introduction of gas in its engine when the methane concentration is adjusted to a level lower than the limit of Flammability. In a gas turbine of this type, the concentration of methane, if necessary, adjust within the range equal to or lower than the limit of Flammability, by mixing gas with high methane concentrations for receiving the Oia gas with low methane concentrations. Then this mixture is compressed by the compressor to receive compressed gas. After that, the compressed gas is burned by the catalytic oxidation in the catalytic combustion chamber for receiving a working gas formed by combustion products. This way the turbine system can be powered thus obtained a working gas. In accordance with this output from the turbine exhaust gases fed into the heat exchanger, which can be heated compressed gas introduced into the catalytic combustion chamber from the compressor (see, for example, the publication WO 2004/029433 A1 /next Document - 1/). In this gas turbine as fuel for it can be used in low-calorie gas, such as landfill gas and/or CMM-gas, in particular the so-called gas VAM (ventilation of coal mine methane), i.e. gaseous vent emissions from coal mines. Typically this gas VAM display or vented into the atmosphere as methane concentration in the gas is equal to or less than 1%, thus insufficient for combustion of such gas under normal combustion conditions. At the same time, now trying to restore order in respect of emissions of carbon dioxide (CO2by generating electricity using a gas turbine, in which you can dispose of such gas VAM as the e fuel for it.

However, in this gas turbine, the compressed gas supplied from the compressor, burned by the catalytic oxidation in the catalytic combustor. Therefore, the compressed gas supplied to the catalytic combustion chamber must be heated typically to a temperature of 300C. or higher and sometimes up to a temperature of approximately 500C, depending on the composition of the used catalyst. In particular, when starting the gas turbine or during low load, the heated compressed gas is produced only by using a recuperator, which tends to be insufficient. So in this case it is necessary to additionally heat the compressed gas, for example, with the use of an auxiliary heating system, for example the pre-chamber or the like. For example, according to the Document 1 between the compressor and the catalytic combustor place the prechamber, which serves gaseous propane or the like, and burn in the chamber with the higher pressure of this gas, thereby heating the compressed gas to flow into the catalytic combustion chamber. However, in the case of the use of such auxiliary heating systems have greatly increased the dimensions of the casing of the gas turbine. In particular, in the case of Document 1, it is necessary to additionally provide a device for injection of fuel, prednaznachen the e for injection of fuel, supplied to the settling chamber, under a certain pressure to be created at the output of the compressor, which leads to a significant reduction resulting power actually used for electricity generation, thus damage to the power output.

In addition, in the case in which a part of the mixture, derived from the compressor is used for cooling heated to a high temperature parts, such as turbine and the like, and/or used for the shaft seal, gaseous methane contained in such a mixture, stands out, remaining unreacted. Then there will be the so-called loss of fuel gas. In addition, this loss of fuel gas will also occur if a significant deterioration in the catalytic activity or performance in the catalytic combustor.

Brief description of the invention

Therefore, the present invention is the creation of a gas turbine system with power depleted fuel, which can work effectively with a substantial simplification of the design and at the same time also can successfully prevent the loss of fuel gas.

To solve this problem the gas turbine system with power depleted fuel according to the invention includes: a compressor configured to, with the Atiyah mixture, obtained by mixing fuel (i.e. fuel component) with air and having a concentration equal to or less than the threshold of Flammability, to receive compressed gas; the first catalytic combustion chamber, made with the possibility of combustion of the compressed gas by catalytic oxidation; a turbine configured to actuate the working gas supplied from the first catalytic combustion chamber; a heat exchanger configured to heat the compressed gas of the exhaust gases output from the turbine, while the compressed gas is introduced from the compressor in the first catalytic combustion chamber; and a duct burner, placed between the turbine and the recuperator and made with the possibility of combustion of the first auxiliary fuel by flaming combustion in the exhaust gases.

According to this gas turbine system mixture with a concentration equal to or less than the threshold of the fire, squeeze the compressor and then thus obtained compressed gas is burned by the catalytic oxidation in the first catalytic combustion chamber, in result of which the turbine can be brought into rotation with a high pressure working gas obtained by catalytic oxidation, thereby setting in motion the consumer power, such as a compressor, an electric generator, etc. In the case, to the m, the inlet temperature of the first catalytic combustion chamber does not reach a certain or predetermined temperature to initiate catalytic oxidation (for example, when starting the turbine system or its operation with partial load), channel the burner is placed on the outlet side of exhaust gases from the turbine, serves the first auxiliary fuel from the feeder of the first auxiliary fuel so that the temperature of the exhaust gases leaving the turbine, could be improved by flaming combustion of the first auxiliary fuel. In this case, since the pressure of the exhaust gases is approximately equal to atmospheric pressure, the power required to increase the pressure of the first auxiliary fuel, is rather small. Then the exhaust gases are subjected to to raise the temperature in the flaming combustion of the first auxiliary fuel is directed into the heat exchanger, where the exhaust gases, in turn, is subjected to heat exchange with the compressed gas supplied from the compressor in the first catalytic combustion chamber. The result is that the inlet temperature of the first catalytic combustion chamber can be increased by the compressed gas, is subjected to higher temperature due to such heat exchange, thereby ensuring proper catalytic combustion in the first catalytic combustion chamber. This way the gas turbine can be brought into rotation, even when using a mixture with such a low concentration of fuel (the Li concentration of gaseous methane), which is landfill gas, gases CMM or VAM. In addition, the use of catalytic oxidation can certainly prevent the formation of oxides of nitrogen (NOx). Further, unlike the prototype gas turbine system according to the present invention does not use any auxiliary heating system, such as a chamber or the like, So this gas turbine system can operate with high efficiency, in which all its design is greatly simplified. In addition, the use of methane gaseous fuel gases such as CMM or VAM or the like, can certainly reduce the amount of gaseous methane emitted into the atmosphere, thereby preventing the warming of the earth.

Preferably the gas turbine system with power depleted fuel according to the present invention additionally includes a second catalytic combustion chamber, provided between the duct burner and recuperator. With this arrangement, the exhaust gas temperature must be increased by the combustion duct burner only to such temperature, which may provide an opportunity for catalytic combustion in the second catalytic combustion chamber. Thus, the number of the first auxiliary fuel with a relatively high concentration (or high quality), under the line duct burner, can be significantly reduced. In addition, in the case in which the output gas or air supplied from the compressor is used for cooling heated to a high temperature parts, such as turbine and the like, and/or used for shaft sealing, the mixture, that is, the gas output after use for such cooling and/or shaft seal, will be mixed with the exhaust gases flowing on the side downstream relative to the turbine. In addition, even when the catalytic activity or the performance of catalytic combustion chamber is greatly reduced, the mixture containing some amount of unreacted fuel, will also be mixed with the exhaust gases. Then such reared and unreacted mixture, respectively mixed in the exhaust gas can be further burned in the second catalytic combustion chamber. Therefore, can be reliably prevented loss of the fuel gas, that is, when the mixture is brought out, as unreacted or unused.

Preferably the gas turbine system with power depleted fuel according to the present invention further includes a device for the introduction of the second auxiliary fuel placed between the duct burner and the second catalytic combustion chamber and made the second with the possibility of introducing a second auxiliary fuel in the exhaust gases. This introduction of a second auxiliary fuel in the exhaust gases emerging from the duct burners in the side of the second catalytic combustion chamber, can be significantly reduced number of the first auxiliary fuel with a high concentration (or high quality), submitted for flaming combustion in the duct burner. In this case, since the second auxiliary fuel burn by catalytic oxidation in the second catalytic combustion chamber, as this second auxiliary fuel may be used fuel with a relative low concentration and low value.

Preferably, the gas turbine system with power depleted fuel according to the present invention further comprises a temperature sensor configured to determine the temperature at the inlet of the first catalytic combustion chamber, and a device for controlling the supply of fuel is arranged to control at least the input number of the first auxiliary fuel to control the inlet temperature within the specified range. With this arrangement, at least, the applied amount of the first auxiliary fuel can be adjusted for reliable temperature setting input within a given range, thus with C is uchitelnoj savings first auxiliary fuel.

Preferably the gas turbine system with power depleted fuel according to the present invention further comprises a device for the introduction of the third auxiliary fuel placed on the suction side of the compressor and configured to increase the concentration of the fuel mixture by adding a third auxiliary fuel in the mixture. With this arrangement, as soon as the inlet temperature of the first catalytic combustion chamber reaches a predetermined temperature during the start mode, the third auxiliary fuel will enter from the device for the introduction of the third auxiliary fuel to increase the temperature of the working gas supplied to the turbine from the first catalytic combustion chamber, thereby increasing the number of revolutions of the engine.

Preferably the gas turbine system with power depleted fuel according to the present invention further comprises a device for injection of air, is placed on the suction side of the compressor and configured to reduce the concentration of fuel in the mixture by adding air to the mixture. With this arrangement, in the case of an emergency stop of the engine, the air can be fed into the compressor from the device for injection of air, located on the suction side of the compressor, resulting in reducing the end is the acidity of the fuel mixture and thereby appropriately suppressing excessive temperature rise in the catalytic combustion chamber, which leads to a significant reduction in the time required to stop the engine.

Preferably in a gas turbine system with power depleted fuel according to the present invention along the wall surface in each passage for exhaust gases in the heat exchanger is placed catalyst for oxidation of exhaust gases. Because with this build you can eliminate the need for the second catalytic combustion chamber, the entire system can be more simplified.

Preferably the gas turbine system with power depleted fuel according to the present invention further comprises a gas mixing channel made with the possibility of mixing of the fuel mixture and air in the exhaust gases leaving the heat exchanger; a catalytic reactor made with the possibility of oxidation of the fuel component contained in the exhaust gases, mixed with the mixture, using catalytic oxidation; and a heat exchanger configured to heat the mixture flowing through the gas mixing channel subjected to the oxidation of exhaust gases withdrawn from the catalytic reactor. This arrangement can successfully prevent the formation of NOx, and can handle quite a large number of mixtures, with a significant reduction in the number of gaseous ETANA, we throw out, even in the case of use as a gas mixture with a low concentration of methane, such as CMM, VAM or similar

The effects of the invention

Thus, according to the invention a gas turbine system with power depleted fuel can work effectively, and the whole construction is greatly simplified without the need for additional heating system such as a chamber or the like, as shown in the prototype.

Brief description of drawings

Fig. 1 is a schematic diagram that illustrates a gas turbine system with power depleted fuel according to the first variant implementation of the present invention;

Fig. 2 is a perspective view of a heat exchanger for use in the second embodiment of the present invention; and

Fig. 3 is a schematic diagram that illustrates a gas turbine system with power depleted fuel according to the third variant of implementation of the present invention.

The best way of carrying out the invention

Hereinafter will be described some preferred embodiments of the invention with reference to the drawings.

First, as shown in Fig. 1, the gas turbine system GT with the power of depleted fuel according to the first variant implementation of the present invention includes a compressor 1, the first is analiticheskoy the combustion chamber 2 using a catalyst, such as platinum, palladium and/or the like, and the turbine 3. In this system, the mixture G1 of air and fuel (i.e. fuel component), such as low-calorie gas, such as landfill gas generated at the landfill, or the like, the gas CMM and/or VAM produced in a coal mine, or the like, is compressed in the compressor 1. Then the compressed gas G2 is fed to the first catalytic combustion chamber 2 and burn it in the presence of a catalyst, such as platinum, palladium and/or etc. then working gas G3 under high pressure, obtained by such combustion is fed to the turbine 3. Thus the turbine 3 can be set in motion. In this case, since the concentration (i.e. the concentration of the combustible component) fuel contained in the mixture G1 is less than the Flammability limit of this gas G1 to ignite even being compressed in the compressor 1. The turbine 3 is connected to the compressor 1 of the rotating shaft 5 so that the compressor 1, in turn, can be brought in by the turbine 3. In addition, the output of the gas turbine system GT is driven electric generator 4, i.e. the kind of consumer power in this system. This way link system 50 for electricity generation, including gas turbine system GT. If necessary, the fuel concentration in the mixture G1 may be enhanced by the proper add what begins to gas G1 fuel component with a high concentration.

Further, the gas turbine system GT contains the heat exchanger 6, is arranged to heat the compressed gas G2 is introduced from the compressor 1 in the first catalytic combustion chamber 2, and channel the burner 7, placed between the turbine 3 and the heat exchanger 6 and is made with combustion exhaust gas G4. More specifically, the heat exchanger 6 can be used to heat the compressed gas G2 exhaust gases G4, leaving the turbine 3, while the duct burner 7 may be used for combustion exhaust gas G4 by flaming combustion of the first auxiliary fuel F1. In this case, the first auxiliary fuel F1, such as natural gas or the like, which may be subjected to flaming combustion (or can be burned in a flame), can be made to channel the burner 7 from source 11 filing of the first auxiliary fuel through the device 8 for supplying the first auxiliary fuel, composed, for example, a valve to regulate the flow rate. In accordance with this exhaust gases G4 withdrawn from the heat exchanger 6 will be released into the atmosphere after plugging the exhaust to the muffler (not shown).

Additionally, in the embodiment shown in Fig. 1, the second catalytic chamber 9 combustion using a catalyst, such as platinum, palladium and/or the like, is placed between the channel is the burner 7 and the heat exchanger 6, and a device 13 for the introduction of the second auxiliary fuel, such as fuel injection nozzle or the like, made with the possibility of introduction of the second auxiliary fuel F2 in the exhaust gases G4, placed in the channel for the exhaust gases passing between the second catalytic chamber 9 of the combustion channel and the burner 7. In this case, the second auxiliary fuel F2, which is like a mixture of G1 may be connected to the device 13 for the introduction of the second auxiliary fuel from a source 15 of the filing of the second auxiliary fuel through the device 14 for supplying a second auxiliary fuel, such as a valve to regulate the flow rate. In addition, on the suction side of the first catalytic chamber 2 combustion placed first temperature sensor 71, configured to determine the temperature at the input (i.e. the input temperature of the first catalytic chamber 2 chamber.

In addition, the control block 21, is arranged to control the entire system, provided by the device 22 for controlling the supply of fuel. The device 22 for controlling the supply of fuel can be used to receive the signal of the designated temperature, sent him the first temperature sensor 71, and then issuing control signals to the devices 8, 14 for supplying the first and second auxiliary Topley is and. More specifically, the device 22 for controlling the supply of fuel generates control signals for the respective control devices 8, 14 for supplying the first and second auxiliary fuel based on the temperature value, the first temperature sensor 71, thereby adjusting the feed rate of each of the first and second auxiliary fuel F1, F2. This way the inlet temperature of the first catalytic chamber 2 combustion can be maintained constant (or within a predefined range) according to the increase in the number of revolutions of the gas turbine system GT. However, in this case the inlet temperature of the first catalytic chamber 2 combustion can be adjusted within a specified range only by adjusting the amount of fuel supplied from the device 8 for supplying the first auxiliary fuel.

Further, in the supply channel located on the side upstream relative to the compressor 1, place the device 17 for the introduction of the third auxiliary fuel, such as fuel injection nozzle or the like, the device 17 for the introduction of the third auxiliary fuel is provided to increase the concentration of the mixture G1 by adding a third auxiliary fuel F3 to the mixture G1. Namely, in this case, the third auxiliary fuel F3, such natural is the gas having a fuel concentration (i.e. the concentration of methane) is higher than that in the mixture G1 may be connected to the device 17 for the introduction of the third auxiliary fuel from a source 19 for supplying the third auxiliary fuel through the device 18 for supplying the third auxiliary fuel, such as a valve to regulate the flow rate. Again, the device 18 for supplying the third auxiliary fuel is controlled by a device 22 for controlling the fuel supply to the control block 21. With this arrangement, as soon as the inlet temperature of the first catalytic chamber 2 of the combustion chamber reaches a predetermined temperature, the third auxiliary fuel F3 may be filed for mixing with a mixture of G1 from the device 18 for supplying the third auxiliary fuel based on the output signal from the device 22 for controlling the supply of fuel, thereby increasing the number of revolutions of the gas turbine system GT.

Since each of the first and second auxiliary fuel F1, F2 injected into the channel for the exhaust gases flowing from the turbine 3 and maintained at approximately atmospheric pressure, the power required for compression of each of these fuels with any suitable fuel pump is relatively low. In addition, since the third auxiliary fuel F3 is compressed by the compressor 1, the gas is urbinas system GT, there is no need for any additional fuel pump for additional compression of the fuel F3.

In addition, in the supply-side channel upstream relative to the compressor 1 place the device 23 for the introduction of air, such as a control valve or the like, is made with the possibility of adding air to the mixture And G1.

Namely, in the gas turbine system GT with the above-described construction, the mixture G1 of air and fuel containing low-calorie gas, such as landfill gas, gas CMM and/or the like, is first compressed in the compressor 1 and then the compressed gas G2 is burned by the catalytic oxidation in the first catalytic combustion chamber 2. Thus, the turbine 3 can be brought into rotation working gas G3 from the high pressure resulting from such combustion, thereby setting in motion the consumer power, such as the compressor 1, the electric generator 4 and the like In this case, when starting the gas turbine system GT electric generator 4 is used as a starter and serves to maintain the number of revolutions of the gas turbine system GT at a low level.

When the number of revolutions of the gas turbine system GT is relatively small (for example, when starting the system, GT and/or during operation with partial load) and if the temperature determined by the first temperatureinduced 71, placed on the suction side of the first catalytic chamber 2 combustion, does not reach a predetermined temperature (for example, a temperature equal to or higher than 300C), which may be initiated by the catalytic oxidation in the first catalytic combustion chamber 2, the first auxiliary fuel F1 serves to channel the burner 7, placed on the outlet side of exhaust gases from the turbine 3, device 8 for supplying the first auxiliary fuel on the basis of the signal or command issued by the device 22 to the fuel control unit 21 controls. Then, when the supply of the first auxiliary fuel F1 exhaust gases G4, leaving the turbine 3 will not burn in the catalytic combustion or combustion in the presence of a catalyst), and by flaming combustion. After that, the exhaust gases G4, processed flaming combustion, served in the heat exchanger 6 and is subjected therein to heat exchange with the compressed gas G2 supplied from the compressor 1 to the first catalytic combustion chamber 2. Thus, the temperature of the compressed gas G2 can be increased, thereby increasing the inlet temperature of the first catalytic chamber 2 of the combustion, so that it can be initiated by catalytic combustion.

In the channel the burner 7, the temperature of the exhaust gas G4 should be raised only to such of those is the temperature, which may provide an opportunity for catalytic combustion in the second catalytic chamber 9 combustion. Therefore, the number of the first auxiliary fuel F1 is supplied to the duct burner 7 can be greatly reduced. If necessary, low-calorie second auxiliary fuel F2, which is like a mixture of G1 can be summed up in the channel for the exhaust gases from the device 14 for supplying a second auxiliary fuel. Thus, it can be additionally saved the first auxiliary fuel F1 with relatively high concentrations of fuel.

As soon as the inlet temperature of the first catalytic chamber 2 of the combustion chamber defined by the first temperature sensor 71 reaches a predetermined temperature and exceed it during the start mode of the gas turbine system GT, the third auxiliary fuel F having a fuel concentration higher than the concentration in the mixture G1, will be submitted and added to a mixture of G1 from the device 13 for supplying the third auxiliary fuel based on the output signal sent from the device 22 for controlling the supply of fuel. As a result, the temperature of the working gas G3 is supplied from the first catalytic chamber 2 combustion may be increased, thereby increasing the speed of a gas-turbine system GT.

In accordance with this during normal slave whom you gas turbine system GT inlet temperature of the first catalytic chamber 2 of the combustion is determined by the first temperature sensor 71, and then number each of the first to third auxiliary fuel F1-F3, respectively, of the input device 8, 14, 18 to flow from the first to the third auxiliary fuel, controlled by the unit 22 for controlling the supply of fuel based on the result of determination. Further, in response to the conditions of the exhaust gas turbine system GT inlet temperature of the first catalytic chamber 2 combustion is regulated within a specified range (for example, 300C or higher). This way catalytic combustion in the first catalytic combustion chamber 2 can be performed with high efficiency. In addition, for additional temperature control at the inlet of the first catalytic chamber 2 of the first or second combustion auxiliary fuel F1 or F2 can be summed up in the channel for the exhaust gases, as required, from the device 8 for supplying the first auxiliary fuel or device 14 for supplying a second auxiliary fuel.

Further, when an emergency stop of the gas turbine system GT will open the channel 23 for the introduction of air, is placed on the suction side of the compressor 1, thereby the temperature of the mixture G1 can be reduced by the introduction of air into the mixture G1 of the channel 23 for the introduction of air. As a result the temperature, for this moment is increased due to the combustion reaction in the PE the howl of the catalytic combustion chamber 2, can be quickly reduced, thereby significantly reducing the time required to completely stop the operation of the gas turbine system GT.

Typically, in a gas turbine air extracted from the compressor is used to cool the components heated to high temperatures, such as turbine and the like, and/or used for the shaft seal, and then such the inferred air after use for cooling and/or shaft seal will be mixed with the exhaust gases flowing on the side downstream relative to the turbine. Accordingly, in this embodiment, the mixture G1 after use for cooling and/or shaft seal is mixed with the exhaust gas G4. Next, after mixing with the exhaust gases G4 mixture G1 is burnt in the second catalytic chamber 9 combustion. Therefore, the so-called loss of fuel gas or gaseous methane (that is, when gaseous methane contained in the mixture G1, comes out, as unreacted or unused) can be successfully prevented. In addition, even when the catalytic activity or performance in the first catalytic combustion chamber 2 is significantly reduced, the fuel, which can be released as unreacted, from a first catalytic chamber 2 combustion can be further soji is but the second catalytic chamber 9 combustion, thereby further preventing the loss of fuel gas.

As described above, since this embodiment does not use any heating system, such as a chamber or the like, the gas turbine system GT can work with high efficiency, and the overall construction is greatly simplified, while the loss of the mixture can be successfully prevented.

Fig. 2 illustrates the heat exchanger 6 for use in the second embodiment of the present invention, in which the heat exchanger 6 can be also used as the second catalytic combustion chamber 9. As shown in the drawing, the heat exchanger 6 is a heat exchanger plate-fin type, composed of numerous plates 31 and ribs 32, respectively, arranged in the foot alternately on each other. The front surface of the heat exchanger 6 can serve as the inlet port 34 to the exhaust gas G4, while the rear surface may serve as the outlet for exhaust gas G4. In this case, many passages 36 for exhaust gas G4 placed respectively extended through the heat exchanger 6 from its front surface to its rear surface. In addition, the right lateral side of the heat exchanger 6 can serve as the inlet port 38 for compressed gas G2, then the AK the left lateral side may serve as the outlet port 39 for compressed gas G2. Namely, numerous passages 40 for compressed gas G2 are placed respectively extended through the heat exchanger 6 from its right side to the left side. Each rib 32 is formed of a corrugated plate so that can be formed passages 36 and 40, respectively, each rib 32 is placed between two adjacent flat plates 31. More specifically, the passages 36 for exhaust gas G4 and passages 40 for compressed gas G2, respectively, are placed alternately in the vertical direction, at the same time respectively located perpendicularly relative to each other.

Next, the surface of the wall of each passage 36 for exhaust gas G4 bears or contains a catalyst, such as platinum, palladium and/or the like, used for catalytic oxidation during combustion or the combustion exhaust gas G4. This arrangement can eliminate the need for placement of the second catalytic combustion chamber 9 shown in Fig. 1, and you can simplify the entire structure of the gas turbine system GT.

Fig. 3 illustrates a third alternative implementation of the present invention, in which the oxidizing unit 60, made with the possibility of oxidation of the mixture G1 with heat recovery exhaust gas G4 withdrawn from the heat exchanger 6, is added to the system 50 to generate electric energy is Gia from the above-described first variant, it is shown in Fig. 1. This version is designed to reduce emissions of gaseous methane contained in the gas CMM or VAM. Oxidative unit 60 includes a gas mixing channel 61 that is designed to add a mixture of G1 containing gaseous methane, such as gas CMM or VAM, to the exhaust gas G4 emerging from the heat exchanger 6, the catalytic reactor 62, made with the possibility of oxidation by catalytic oxidation of the fuel component contained in the mixed exhaust gas G5 formed by adding a mixture of G1 to the exhaust gas G4, that is, the fuel contained in the mixture G1, and the heat exchanger 63, made with the possibility of heating the mixture G1 flowing through the gas mixing channel 61, using the oxidized exhaust gas G6 withdrawn from catalytic reactor 62. On the side of the intake channel of a catalytic reactor 62 is placed second temperature sensor 72, configured to determine the temperature at the inlet of the catalytic reactor 62, that is, the temperature of the mixed exhaust gas G5 formed by adding a mixture of G1 to the exhaust gas G4. In this case, the signal on the designated temperature from the second temperature sensor 72 is supplied in unit 21 of the management system 50 to generate electric energy, and then the block 21 the Board regulates the amount of air directed blower unit 64, based on the temperature of the mixed exhaust gas G4 determined by the sensor 72. This way you can adjust the amount of the mixture G1, primitively to the exhaust gas G4, thereby adjusting the temperature at the inlet of the catalytic reactor 62, within an appropriate range (for example, from 250 to 300C) for catalytic oxidation. While oxidative unit 60 according to this embodiment is controlled by a block 21 of the control system 50 to generate electric energy, this oxidation unit 60 can be controlled by another special controller that are separate from the unit 21 of the control.

Instead of applying gas CMM or VAM in the present invention can be used with any other suitable gas, under the condition that the gas is flammable or contains the proper amount of fuel component.

As indicated above, while the preferred options have been shown and described as examples, they should be interpreted in such a way that the scope of the present invention can be made a variety of modifications and/or changes.

1. Gas turbine system with power depleted fuel, comprising: a compressor configured to compress a mixture obtained by mixing the fuel with air and having a concentration equal to or less than p is published by third parties of Flammability, for receiving compressed gas; the first catalytic combustion chamber, made with the possibility of burning of the compressed gas by catalytic oxidation; a turbine configured to actuate the working gas supplied from the first catalytic combustion chamber; a heat exchanger configured to heat the compressed gas of the exhaust gas leaving the turbine, while the compressed gas is introduced from the compressor in the first catalytic combustion chamber; duct burner located between the turbine and the recuperator and is made with combustion exhaust gas by using the first auxiliary fuel conditions flaming combustion; and an additional device for the introduction of auxiliary fuel located on the suction side of the compressor and configured to increase the concentration of the fuel mixture by adding additional auxiliary fuel to the mixture.

2. The system according to claim 1, additionally containing a second catalytic combustion chamber, located between the duct burner and recuperator.

3. The system according to claim 2, optionally containing one additional device for injecting auxiliary fuel channel located between the burner and the second catalytic combustion chamber and configured to introduce the who of an additional auxiliary fuel in the exhaust gas.

4. System according to any one of claims 1 to 3, further containing a temperature sensor configured to determine the temperature at the inlet of the first catalytic combustion chamber, and a device for controlling the supply of fuel is arranged to control at least the input number of the first auxiliary fuel to regulate the inlet temperature within the specified range.

5. System according to any one of claims 1 to 3, further containing a device for injection of air, which is located on the suction side of the compressor and configured to reduce the concentration of fuel in the mixture by adding air to the mixture.

6. System according to any one of claims 1 to 3, in which the catalyst for the oxidation exhaust gas is located along the surface of the walls of the passage for exhaust gas in the recuperator.

7. System according to any one of claims 1 to 3, additionally containing gas mixing channel, made with the possibility of adding a mixture of fuel and air to the exhaust gas emerging from the heat exchanger; a catalytic reactor made with the possibility of oxidation of the fuel component contained in the exhaust gas mixed with the mixture by catalytic oxidation; and a heat exchanger configured to heat the mixture flowing through the gas mixing channel, okislennaya gas, coming out of the catalytic reactor.



 

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1 dwg

FIELD: power industry.

SUBSTANCE: burner (4) for gas burner includes: swirler (21), plate (58), the first channel (18) via which fuel gas with low calorific value is supplied, and second channel (17) via which combustion air is supplied. The first and the second channels (17, 18) are located concentrically relative to longitudinal axis (2). Output of the first channel (18) is formed with convergent nozzle (50). Swirler (21) is installed at the outlet of the second channel (17). Plate (58) is tightly installed in the first channel (18) upstream nozzle (50) and has many holes (56) with calibrated section of the passage. Holes (56) are inclined in tangential direction relative to longitudinal axis (2) at the specified angle. For fuel gases having flame propagation speed of less than 300 mm/s, plate (58) has 36 to 38 holes (56) the diameter of which is 11.5 to 12.0 mm, and inclination angle of holes (56) is approximately 22. For fuel gases having flame propagation speed of 300 mm/s to 400 mm/s, plate (58) has 80 holes (56) the diameter of which is 8.5 mm to 9.0 mm, and inclination angle of holes (56) is 17 to 22. If calorific value of gas with low calorific value from the first channel (18) is less than 4.0 MJ/kg, then natural gas consumption is assumed from pilot line (46). Burner (5) is used only when gases with low calorific value are not available.

EFFECT: high burner flexibility; operation is possible at the gas used with low calorific value and of any type within the whole working range of gas turbine.

12 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed gas turbine comprises compressor linked up with the drive. In its turn, compressor drive comprises 1st and 2nd stages, inner and outer shafts with blower fitted on inner shaft and compressor fitted on outer shaft. It includes also HP and LP turbines with cooling system, primary combustion chamber arranged between compressor and HP turbine. Gas turbine comprises also outer combustion chamber and heat exchanger-heater arranged behind HP turbine and communicated, via heat carrier circulation lines, with heat exchanger arranged behind outer combustion chamber.

EFFECT: higher efficiency and reliability.

3 cl, 4 dwg

Power supply system // 2307946

FIELD: power engineering.

SUBSTANCE: proposed power supply system generating electric power using self-forming gas contains gas motor, gas turbine, gas collector for self-forming gas, device to separate gas and device to control calorific value for selective mixing of gases differing in content of fuel component. Gas separating device continuously separates gas delivering from gas collector whose fuel component content changes in time according to content of fuel component of gas. Calorific value control device for selective mixing of gases differing in content of fuel component which are separated by gas separating device, controls content of fuel component of gas which is to be supplied to gas motor and gas turbine. System control device is provided to control operation of gas motor, gas turbine and calorific value control device.

EFFECT: provision of power supply system maintaining stable generation of power, irrespective of changes of amount of self-forming gas and its calorific value.

13 cl, 8 dwg

The invention relates to a method and evaporator deeply refrigerated liquid working medium

Power supply system // 2307946

FIELD: power engineering.

SUBSTANCE: proposed power supply system generating electric power using self-forming gas contains gas motor, gas turbine, gas collector for self-forming gas, device to separate gas and device to control calorific value for selective mixing of gases differing in content of fuel component. Gas separating device continuously separates gas delivering from gas collector whose fuel component content changes in time according to content of fuel component of gas. Calorific value control device for selective mixing of gases differing in content of fuel component which are separated by gas separating device, controls content of fuel component of gas which is to be supplied to gas motor and gas turbine. System control device is provided to control operation of gas motor, gas turbine and calorific value control device.

EFFECT: provision of power supply system maintaining stable generation of power, irrespective of changes of amount of self-forming gas and its calorific value.

13 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed gas turbine comprises compressor linked up with the drive. In its turn, compressor drive comprises 1st and 2nd stages, inner and outer shafts with blower fitted on inner shaft and compressor fitted on outer shaft. It includes also HP and LP turbines with cooling system, primary combustion chamber arranged between compressor and HP turbine. Gas turbine comprises also outer combustion chamber and heat exchanger-heater arranged behind HP turbine and communicated, via heat carrier circulation lines, with heat exchanger arranged behind outer combustion chamber.

EFFECT: higher efficiency and reliability.

3 cl, 4 dwg

FIELD: power industry.

SUBSTANCE: burner (4) for gas burner includes: swirler (21), plate (58), the first channel (18) via which fuel gas with low calorific value is supplied, and second channel (17) via which combustion air is supplied. The first and the second channels (17, 18) are located concentrically relative to longitudinal axis (2). Output of the first channel (18) is formed with convergent nozzle (50). Swirler (21) is installed at the outlet of the second channel (17). Plate (58) is tightly installed in the first channel (18) upstream nozzle (50) and has many holes (56) with calibrated section of the passage. Holes (56) are inclined in tangential direction relative to longitudinal axis (2) at the specified angle. For fuel gases having flame propagation speed of less than 300 mm/s, plate (58) has 36 to 38 holes (56) the diameter of which is 11.5 to 12.0 mm, and inclination angle of holes (56) is approximately 22. For fuel gases having flame propagation speed of 300 mm/s to 400 mm/s, plate (58) has 80 holes (56) the diameter of which is 8.5 mm to 9.0 mm, and inclination angle of holes (56) is 17 to 22. If calorific value of gas with low calorific value from the first channel (18) is less than 4.0 MJ/kg, then natural gas consumption is assumed from pilot line (46). Burner (5) is used only when gases with low calorific value are not available.

EFFECT: high burner flexibility; operation is possible at the gas used with low calorific value and of any type within the whole working range of gas turbine.

12 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: peak hydrogen steam turbine plant includes steam turbine and compressor, hydrogen and oxygen storage tanks and combustion chamber, which are installed on one shaft. Steam turbine and compressor are connected by means of system of steam pipelines so that closed steam circuit is formed. Combustion chamber is located before steam turbine and connected by means of pipelines to receivers. Regenerative heat exchanger and cooler are included in closed steam circuit. Condensing turbine with condenser is connected to steam pipeline connecting the steam turbine to compressor. Electrolysis unit is connected to condenser via pipeline on which there mounted is water pump, and interconnected with hydrogen and oxygen storage tanks via pipelines on which gas compressors are installed. Plant capacity is controlled by changing the hydrogen and oxygen supply to combustion chamber and steam discharge from closed circuit to condensing turbine.

EFFECT: increasing the plant efficiency and decreasing thermal stresses in turbomachines at variable loads due to almost unchangeable temperature in closed steam circuit.

1 dwg

FIELD: machine building.

SUBSTANCE: proposed system comprises air compressor, steel work gas compressor, combustion chamber, turbine, transmission for coupling drive shaft with steel work gas compressor. Turbine is driven by combustion chamber waste gas to transmit mechanical power to air compressor and using equipment, in particular, to AC generator and drive shaft. Compressed air and steel work compressed gas and/or natural gas are fed into combustion chamber. Transmission comprises means of coupling/uncoupling steel work gas compressor with/from drive shaft during rotation of the latter.

EFFECT: increased electric power output, decreased idle time, higher efficiency at restart of turbine and AC generator.

9 cl, 2 dwg

FIELD: machine building.

SUBSTANCE: gas turbine system fed by depleted fuel comprises compressor, first catalytic chamber, turbine, recuperator, channel burner and extra device to feed auxiliary fuel arranged on compressor side to increase fuel concentration in the mix by adding extra auxiliary fuel in the mix. Compressor compresses aforesaid air-fuel mix with concentration equal to or lower than ultimate inflammability to obtain compressed gas. First catalytic combustion chamber allows combusting compressed gas by catalytic oxidation. Turbine may be driven by gas fed from first catalytic combustion chamber. Recuperator heats compressed gas by turbine exhaust gas while compressed gas is forced from compressor into said chamber. Channel burner is arranged between turbine and recuperator to combust exhaust gas with the help of auxiliary fuel in plasma burning.

EFFECT: higher efficiency, simplified design, ruled out fuel gas loss.

7 cl, 3 dwg

FIELD: power engineering.

SUBSTANCE: gas turbine plant for conversion of associated petroleum gas into power comprises an air compressor, a turbine, a combustion chamber, a power generator and a device o air heating downstream the compressor, comprising a heat exchange regenerator device arranged in an exhaust pipe. The combustion chamber with the exhaust pipe are arranged in the form of a surface flare for burning of associated petroleum gas. The compressor is equipped with an electric drive. The turbine at the outlet side is communicated with environment with the help of an autonomous pipe. The surface flare at the side of associated petroleum gas supply is made with a device of atmospheric air intake.

EFFECT: expanded area of gas turbine plant application, increased efficiency of carbon fuel usage and improved environmental capability of environment.

2 cl, 2 dwg

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