TURBO-CLUSTER GAS TURBINE SYSTEM AND ACTIVATION METHOD THEREOF

Abstract

A turbo-cluster gas turbine system (2) comprising: at least one combustion chamber (4) configured to burn a fuel to produce a combustion gas; an output turbine (6) configured to be driven by the combustion gas from the at least one combustion chamber (4); and a plurality of charging systems (8) configured to supply compressed air to be delivered to the at least one combustion chamber (4), each of the charging systems (8) comprising: a first turbocharger (10) with a rotating shaft (20) configured separately from a rotating shaft (18) of the output turbine (6) and configured to be driven by the combustion gas from the combustion chamber (4); a first air duct (15) for delivering compressed air, compressed by a compressor (12) of the first turbocharger (10), to the combustion chamber (4);and a first combustion gas line (16) for supplying the combustion gas from the combustion chamber (4) to a turbine (14) of the first turbocharger (10), the turbo-cluster gas turbine system (2) further comprising: a piston engine (62) as a starter for igniting the combustion chamber (4); an activation line (64) connecting an outlet of the piston engine (62) to the first combustion gas line (16); a valve (66) provided in the first combustion gas line (16) upstream of a connection position between the first combustion gas line (16) and the activation line (64); and a valve (68) provided in the activation line (64).

Description

TECHNICAL FIELD

[0001] The present disclosure relates to a turbo-cluster gas turbine system and an activation method thereof. BACKGROUND

[0002] For example, as described in patent document 1, a conventional gas turbine is configured such that a compressor and an output turbine rotate integrally on the same axis. Citation list of patent literature

[0003] Patent Document 1: JP2000-73782A SUMMARY

[0004] However, if a gas turbine is configured such that a compressor and an output turbine rotate integrally on the same axis, the gas turbine will be large in the axial direction, which is likely to lead to limitations in the design of the gas turbine.

[0005] In view of the foregoing, an object of at least one embodiment of the present invention is to provide a turbo-cluster gas turbine system with a high degree of design freedom and an activation method thereof.

[0006] ( 1A turbo-cluster gas turbine system according to at least one embodiment of the present invention comprising: at least one combustion chamber configured for burning a fuel to produce a combustion gas; an output turbine configured to be driven by the combustion gas from the at least one combustion chamber; and a plurality of charging systems configured to supply compressed air to be supplied to the at least one combustion chamber, each of the charging systems comprising: a first turbocharger with a rotating shaft configured separately from a rotating shaft of the output turbine and configured to be driven by the combustion gas from the combustion chamber; a first air duct for supplying compressed air, which is compressed by a compressor of the first turbocharger, to the combustion chamber;and a first combustion gas line for supplying the combustion gas from the combustion chamber to a turbine of the first turbocharger.

[0007] According to the turbo-cluster gas turbine system according to ( 1Since the rotational shaft of the first turbocharger is separate from the rotational shaft of the output turbine, a multitude of first turbochargers can be arranged on an axis different from that of the output turbine, and a turbo-cluster gas turbine system with a high degree of design freedom can be realized. Furthermore, it is possible to obtain a desired output from an output turbine using a multitude of first turbochargers, while reducing the size of the devices configured integrally with an output turbine, including the output turbine in the axial direction of the output turbine, compared to a conventional gas turbine configured so that a compressor and output turbine rotate integrally on the same axis.Furthermore, by adjusting the number of driven first turbochargers from the multitude of first turbochargers, flexible part-load operation can be achieved. Moreover, even if one of the turbocharging systems cannot be used temporarily for specific reasons, high reliability in terms of operational stability can be maintained because the operation of the output turbine can be sustained by the other turbocharging systems. In addition, satisfactory maintenance characteristics can be achieved by using compact turbochargers as the first turbochargers.

[0008] ( 2 ) In some embodiments of the turbo-cluster gas turbine system according to ( 1), wherein each of the charging systems comprises: at least one second turbocharger with a rotational shaft that is separate from the rotational shaft of the output turbine and the rotational shaft of the first turbocharger; a second air line for supplying compressed air, which is compressed by a compressor of the second turbocharger, to the compressor of the first turbocharger; and a second combustion gas line for supplying the combustion gas discharged by a turbine of the first turbocharger to a turbine of the second turbocharger.

[0009] According to the turbo-cluster gas turbine system according to ( 2Since the rotational shaft of the first turbocharger is separate from the rotational shaft of the output turbine, multiple first turbochargers, multiple second turbochargers, and the output turbine can be arranged on separate axes, allowing for a turbo-cluster gas turbine system with a high degree of design flexibility. By supplying high-pressure air compressed by the first and second turbochargers to the combustion chamber, it is possible to obtain high combustion energy and achieve high output from the output turbine.

[0010] ( 3 ) In some embodiments of the turbo-cluster gas turbine system according to ( 2 ), wherein the turbo cluster gas turbine system includes a plurality of combustion chambers, and the plurality of charging systems is configured to each supply compressed air to the plurality of combustion chambers.

[0011] According to the turbo-cluster gas turbine system according to (3 The compressed air from the compressor of a first turbocharger is fed to a combustion chamber (a heat chamber) via the first air line. Therefore, the first air line of each turbocharging system can be connected to the corresponding combustion chamber without connecting it to the first air line of another turbocharging system. This allows for a reduction in pressure loss through gentle turbocharging, resulting in highly efficient combustion. By adjusting the number of first turbochargers driven by the multiple first turbochargers, flexible part-load operation can be achieved.

[0012] ( 4 ) In some embodiments of the turbo-cluster gas turbine system according to ( 2 ) or ( 3 ), the output turbine is provided in the first combustion gas line.

[0013] According to the turbo-cluster gas turbine system according to ( 4The combustion gas, having passed through the output turbine and whose temperature has dropped, can be fed to the first turbocharger. Therefore, even if the combustion gas temperature at the combustion chamber outlet is set to approximately 1300°C, which corresponds to the combustion gas temperature at the combustion chamber outlet of a conventional marine gas turbine, the combustion gas temperature at the first turbocharger's turbine inlet will drop to approximately 960°C. Therefore, from a heat resistance perspective, a turbocharger (one that can be mass-produced at low cost) designed for gasoline engines in automobiles, where nickel-based alloys or similar materials are used in the components, can be used as the first turbocharger, thus achieving cost reduction for the turbo-cluster gas turbine system.

[0014] ( 5) In some embodiments of the turbo-cluster gas turbine system according to ( 2 ) or ( 3 ), each of the charging systems contains a third combustion gas line to supply the combustion gas that has passed through the turbine of the second turbocharger to the output turbine.

[0015] According to the turbo-cluster gas turbine system according to ( 5 ) by appropriately adjusting the temperature of the combustion gas at the outlet of the combustion chamber, a turbocharger (a turbocharger that can be mass-produced cost-effectively) designed for gasoline engines for automobiles where nickel-based alloys or similar materials are used in the components can be used as the first turbocharger, and the cost reduction of the turbo-cluster gas turbine system can be achieved.

[0016] ( 6 ) In some embodiments of the turbo-cluster gas turbine system according to one of ( 2 ) until ( 5), each of the charging systems contains an intercooler provided in the second air duct.

[0017] According to the turbo-cluster gas turbine system according to ( 6 It is possible to increase the density of the compressed air supplied to the combustion chamber in order to improve the combustion efficiency of the combustion chamber.

[0018] ( 7 ) In some embodiments of the turbo-cluster gas turbine system according to one of ( 2 ) until ( 6 ), is the sum of the number of first turbochargers and the number of second turbochargers 10 or more.

[0019] According to the turbo-cluster gas turbine system according to ( 7It is possible to obtain a desired output turbine power using ten or more first turbochargers. Furthermore, by adjusting the number of driven first turbochargers from among the ten or more, it is possible to achieve flexible part-load operation.

[0020] (8) In some embodiments, the turbo cluster gas turbine system according to one of ( 2 ) until ( 7 ) furthermore: a heat exchanger for carrying out a heat exchange between the compressed air flowing through the first air line and the combustion gas emitted from the turbine of the second turbocharger.

[0021] According to the turbo cluster gas turbine system according to (8) it is possible to collect the exhaust heat of the second turbocharger using the heat exchanger and to improve the overall efficiency of the system.

[0022] (9) In some embodiments, the turbo-cluster gas turbine system according to one of ( 2 ) until ( 7 ) furthermore: a heat exchanger for carrying out a heat exchange between a heating medium and the combustion gas discharged by the turbine of the second turbocharger; and a turbine configured to be driven by the heating medium discharged from the heat exchanger.

[0023] According to the turbo cluster gas turbine system according to (9) it is possible to collect the exhaust heat of the second turbocharger using the heat exchanger and the turbine and to improve the efficiency of the overall system.

[0024] (10) In some embodiments, the turbo-cluster gas turbine system according to one of ( 1) to (9) further: a piston engine; an activation line connecting an outlet of the piston engine to the first combustion gas line; a first valve provided in the first combustion gas line upstream of a connection position between the first combustion gas line and the activation line; and a second valve provided in the activation line.

[0025] According to the turbo-cluster gas turbine system of (10), when the system is activated, the compressed air supplied from the piston engine is directed through the activation line and the first combustion gas line to the turbine of the first turbocharger to initiate the rotation of the first turbocharger in a state where the first valve is closed and the second valve is open. The compressed air that has passed through the turbine of the first turbocharger is directed to the turbine of the second turbocharger, and the second turbocharger begins to rotate. In this way, the air compressed by the compressor of the second turbocharger is further compressed by the compressor of the first turbocharger, the compressed air discharged from the compressor is directed to the combustion chamber via the first air line, and the combustion chamber ignites the fuel using the supplied compressed air.

[0026] In this way, it is possible to activate the turbo-cluster gas turbine system quickly, as rapid ignition in the combustion chamber is achieved with a simple configuration and the output turbine is driven by the combustion gas generated by the combustion chamber.

[0027] ( 11 ) In some embodiments of the turbo-cluster gas turbine system according to one of ( 1 ) to (10), the first turbocharger is configured to meet heat resistance requirements against the combustion gas.

[0028] According to the turbo-cluster gas turbine system according to ( 11 ) it is possible to suppress damage to the first turbocharger caused by the heat of the combustion gas, even if no cooling mechanism is provided in the first turbocharger.

[0029] (12) In some embodiments of the turbo-cluster gas turbine system according to a design by ( 1 ) until ( 11), is the first turbocharger designed for gasoline engines in automobiles.

[0030] According to the turbo cluster gas turbine system according to (12) it is possible to achieve a cost reduction of the turbo cluster gas turbine system.

[0031] ( 13 A turbo-cluster gas turbine system activation method according to at least one embodiment of the present invention comprising: supplying compressed air, delivered by a piston engine, to a turbine of a first turbocharger to allow the first turbocharger to be set into rotation; supplying compressed air, delivered by a compressor of the first turbocharger, which has started to rotate, to a combustion chamber; igniting a fuel using the compressed air supplied to the combustion chamber; and supplying a combustion gas delivered from the combustion chamber to an output turbine to allow the output turbine to be set into rotation.

[0032] According to the turbo cluster gas turbine system activation method according to (13), it is possible to achieve rapid ignition in the combustion chamber with a simple configuration using a piston engine and to quickly activate the output turbine with the combustion gas generated by the combustion chamber.

[0033] ( 14 ) In some embodiments, the turbo-cluster gas turbine system activation method according to (13) further includes: supplying compressed air that has passed through the turbine of the first turbocharger to a turbine of a second turbocharger to allow the second turbocharger to be set into rotation; and supplying compressed air that is discharged from a compressor of the second turbocharger, which is starting to rotate, to the compressor of the first turbocharger.

[0034] According to the turbo cluster gas turbine system activation method according to (13), it is possible to achieve rapid ignition in the combustion chamber with a simple configuration using a piston engine and to quickly activate the output turbine with the combustion gas generated by the combustion chamber.

[0035] According to at least one embodiment of the present invention, a turbo cluster gas turbine system with a high degree of design freedom and an activation method thereof are provided. List of characters Fig. Figure 1 is a schematic diagram showing the entire configuration of a turbo-cluster gas turbine system. 2 according to one embodiment. Fig. 2 is a diagram showing the overall configuration of each charging system. 8 represents. Fig. 3 is a diagram that shows a cycle assessment of the in Fig. 1 and Fig. 2 depicted turbo cluster gas turbine systems 2 represents when the temperature of a combustion gas at the inlet of an output turbine 6 was set to 1300°C. Fig. Figure 4 is a diagram showing a relationship between the temperature (turbine inlet temperature) of a combustion gas at the inlet of the output turbine. 6 and the output of a generator connected to the output turbine 9 in the Fig. The 3 shown configuration represents cases where the turbine inlet temperature was set to 1050°C, 1300°C and 1450°C. Fig. 5 is a schematic diagram that shows an example of a match between a combustion chamber 4 of the turbo cluster gas turbine system 2 and a first turbocharger 10 a charging system 8 represents. Fig. Figure 6 is a schematic diagram showing the arrangement of the combustion chamber 4 and the first turbocharger 10 of the charging system 8 in an axial view of the output turbine 6 in the Fig. The configuration shown in section 5 is represented. Fig. 7 is a schematic diagram that shows a modification of the one in Fig. The configuration shown in section 3 represents the configuration shown. Fig. 8 is a schematic diagram that shows a modification of the one in Fig. The configuration shown in the 3 images is illustrated. Fig. 9 is a diagram describing an activation procedure of the output turbine. 6 . Fig. 10 is a schematic diagram that shows a modification of the one in Fig. The configuration shown in section 3 represents the configuration shown. DETAILED DESCRIPTION

[0036] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. However, it is intended that the dimensions, materials, shapes, relative positions, and the like of the components described in the embodiments, unless specifically stated otherwise, are intended only for illustration and not to limit the scope of application of the present invention.

[0037] For example, an expression of a relative or absolute arrangement such as "in a direction", "along a direction", "parallel", "orthogonal", "centered", "concentric" and "coaxial" is not to be interpreted as only indicating the arrangement in the narrow sense of the word, but also includes a state in which the arrangement is shifted relatively by a tolerance or by an angle or a distance, by which the same function can be achieved.

[0038] For example, an expression of an equal state such as "identical", "equal" and "uniform" is not to be interpreted as indicating only the state in which the feature is strictly equal, but also includes a state in which there is a tolerance or a difference that can still fulfill the same function.

[0039] Furthermore, in the present specification, an expression of a shape, such as a rectangular shape or a cylindrical shape, is not to be interpreted only as the geometrically strict shape, but also includes a shape with irregularities or chamfered corners within the area in which the same effect can be achieved.

[0040] Furthermore, in this specification, expressions such as "comprise", "include", "have", "contain" and "consist" should not exclude other components.

[0041] Furthermore, in some embodiments described later, the same reference numbers indicate components that have similar configurations, unless specifically indicated and a redundant description is omitted.

[0042] Fig. Figure 1 is a schematic diagram showing an entire configuration of a turbo-cluster gas turbine system. 2 according to one embodiment.

[0043] As in Fig. Figure 1 shows the turbo cluster gas turbine system. 2 a large number of combustion chambers 4 , which are configured to burn a fuel to produce a combustion gas, an output turbine 6 , which is configured to be powered by a combustion gas supplied by the multitude of combustion chambers 4 is delivered, and a variety of charging systems 8, which are configured to accommodate the multitude of combustion chambers 4 Supply compressed air. A generator. 9 is connected to the output turbine 6 connected, and the generator 9 generates electrical energy when the output turbine 6 rotates. Although the output turbine's power 6 Since the power output is not particularly limited, it can be, for example, 10 MW or more. It is noted that in an exemplary embodiment described in Fig. Figure 1 shows the turbo cluster gas turbine system. 2 sixteen charging systems 8 contains.

[0044] Fig. Figure 2 is a diagram showing a schematic configuration of each of the charging systems. 8 represents.

[0045] As in Fig. As shown in section 2, each of the charging systems includes 8 a first turbocharger 10 , a first air line 15, a first combustion gas line 16 , a large number of second turbochargers 24 , a second air duct 30 , a second combustion gas line 32 , a first distributor 34 and a second distributor 36 . In this context, “air line” means an air pipeline and “gas line” means a gas pipeline.

[0046] The first turbocharger 10 includes a compressor 12 and a turbine 14 , which form a rotational wave 20 share and are configured to work with the combustion gas from the combustion chamber 4 are powered (see Fig. 1) The rotational wave 20 of the first turbocharger 10 is separated from a rotating wave 18 (see Fig. 1) the output turbine 6 (see Fig. 1) formed and is on a different axial line than that of the rotational wave 18arranged. If a compact turbocharger, mass-produced and designed, for example, for gasoline engines in automobiles, is the first turbocharger 10 When used, it is possible to use the turbo cluster gas turbine system. 2 to achieve this at extremely low costs compared to a conventional gas turbine.

[0047] The first air line 15 is configured so that the compressor 12 of the first turbocharger 10 compressed air of the combustion chamber 4 is supplied.

[0048] The first combustion gas line 16 is configured so that the combustion chamber 4 exhaust gas escaping from the turbine 14 of the first turbocharger 10 is supplied.

[0049] Each of the second turbochargers 24 includes a compressor 26 and a turbine 28, which form a rotational wave 22 share and are configured to be powered by the combustion gas that comes from the combustion chamber 4 is emitted. Furthermore, the rotational wave 22 of the second turbocharger 24 separated from the rotating wave 18 the output turbine 6 and the rotational wave 20 of the first turbocharger 10 formed and on a different axial line than that of the rotational waves 18 and 20 arranged. If a compact turbocharger, which is mass-produced and designed, for example, for gasoline engines in automobiles, is used as a second turbocharger 24 When used, it is possible to use the turbo cluster gas turbine system. 2 to achieve this, which is very cost-effective compared to a conventional gas turbine.

[0050] It should be noted that in the illustrated exemplary embodiment, there are four second turbochargers. 24 are arranged parallel to the flow direction of the combustion gas. In the exemplary illustration in Fig. 1 and Fig. 2 includes the turbo cluster gas turbine system 2 therefore sixteen first turbochargers 10 and sixty-four second turbochargers 24 for an output turbine 6 and includes a cluster 25 (a turbo cluster) consisting of a total of eighty turbochargers.

[0051] The second air duct 30 is configured so that the compressor 26 every second turbocharger 24 compressed air to the compressor 12 of the first turbocharger 10 is supplied. A downstream end of the second air duct 30 is equipped with an inlet of the compressor 12 of the first turbocharger 10connected, an upstream end of the second air line 30 branches out via the first distributor 34 into a multitude of points and is connected to the compressor outlet. 26 each of the second turbochargers 24 tied together.

[0052] The second combustion gas line 32 is configured so that the turbine 14 of the first turbocharger 10 exhaust gas from the turbine 28 each of the second turbochargers 24 is supplied. An upstream end of the second combustion gas line 32 is with the turbine outlet 14 of the first turbocharger 10 connected, and a downstream end of the second combustion gas line 32 branches off via the second distributor 36 into a multitude of points and is connected to the turbine inlet 28 each of the second turbochargers 24 tied together.

[0053] According to this configuration, since the rotating shaft 20 of the first turbocharger 10 separated from the rotating wave 18 the output turbine 6 is formed, the multitude from first turbochargers 10 on a different axis than that of the output turbine 6 be arranged, and the turbo cluster gas turbine system 2 can be achieved with a high degree of design freedom.

[0054] Furthermore, it is possible to set a desired output power of the output turbine. 6 to be obtained using the multitude of first turbochargers 10 during a reduction in the size of the devices (in the in Fig. 1 configuration shown, a device in which the combustion chamber 4 , the output turbine 6 and the generator 9 are integrated), which are integral with the output turbine 6 including the output turbine6 in the axial direction of the output turbine 6 are configured, in contrast to a conventional gas turbine, which is configured so that a compressor and an output turbine rotate integrally on one axis.

[0055] Furthermore, it is possible to adjust the number of first turbochargers. 10 , which are among the many early turbochargers 10 To be powered, it is possible to implement flexible partial load operation. Furthermore, even if a charging system is used, it is possible to achieve this. 8 from the multitude of charging systems 8 could not be used temporarily for certain reasons, as the operation of the output turbine was not possible. 6 through the other charging systems 8High reliability in terms of operational stability can be achieved, which can be maintained. Furthermore, the use of compact turbochargers, such as the numerous first and second turbochargers, allows for... 10 and 24 to achieve satisfactory maintenance characteristics.

[0056] Fig. 3 is a diagram that provides a cycle assessment for the in Fig. 1 and Fig. 2 depicted turbo cluster gas turbine systems 2 represents when the temperature of the combustion gas at the inlet of the output turbine 6 was set to 1300°C.

[0057] In the Fig. The example shown in point 3 is in the second air duct. 30 an intercooler 38 provided, and those through the second air line 30 Flowing compressed air is heated by heat exchange between the charge air cooler and the intercooler. 38 and cooled by a cooling medium. In which in Fig. In the example shown, the temperature and pressure of the air at the compressor inlet are... 26 20°C and 0.1 MPa, the temperature of the compressed air at the inlet of the charge air cooler. 38 The temperature of the compressed air at the compressor inlet is 222°C. 12 is 59°C and the temperature of the compressed air at the inlet of the combustion chamber 4 The temperature is 271°C. Furthermore, the temperature and pressure of the combustion gas at the combustion chamber outlet are... 4 (the temperature and pressure of the combustion gas at the inlet of the output turbine) 6 ) 1300°C and 1.79 MPa, the temperature of the combustion gas at the turbine inlet 14 The temperature of the combustion gas at the turbine inlet is 968°C. 28 is 802°C, and the temperature and pressure of the combustion gas at the turbine outlet 28 The temperatures are 644°C and 0.1 MPa.

[0058] In the Fig. The configuration shown in section 3 can be used, since the output turbine 6 in the first combustion gas line 16 The combustion gas supplied to the output turbine is provided. 6 has passed through and its temperature has dropped, the first turbocharger 10 supplied. Even if the temperature of the combustion gas at the combustion chamber outlet 4 When the temperature is set to approximately 1300°C, which corresponds to the temperature of the combustion gas at the outlet of the combustion chamber of a conventional ship gas turbine, the temperature of the combustion gas at the inlet of the turbine decreases. 14 of the first turbocharger 10to approximately 960°. Therefore, from the point of view of heat resistance, a turbocharger (a turbocharger that can be mass-produced cost-effectively) designed for gasoline engines for automobiles, where nickel-based alloys or similar materials are used in the components, can be considered the first turbocharger. 10 to be used, and the cost reduction of the turbo cluster gas turbine system 2 to be realized.

[0059] Fig. Figure 4 is a diagram showing a relationship between the temperature (turbine inlet temperature) of a combustion gas at the inlet of the output turbine. 6 and the output of the generator connected to the output turbine 9 in the Fig. Figure 3 represents the configuration shown and depicts cases in which the turbine inlet temperature was set to 1050°C, 1300°C, and 1450°C. In the diagram shown Fig. 3 and Fig. The example shown in section 4 is in the first and second turbochargers. 10 and 24 No cooling mechanism is provided.

[0060] As in Fig. As shown in Figure 4, the generator's power output increases with increasing turbine inlet temperature. Furthermore, even if the turbine inlet temperature is any one of 1050°C, 1300°C, and 1450°C, a turbocharger designed for gasoline engines in automobiles can be used as a first and second turbocharger. 10 and 24 can be used without a cooling mechanism in each of the first and second turbochargers 10 and 24 is provided, and it can be an extremely cost-effective turbo-cluster gas turbine system. 2 This can be achieved. Furthermore, at a turbine inlet temperature of 1050°C, it is not necessary to have a [missing information] in each blade of the output turbine. 6 to provide a cooling mechanism, and it is possible to use a turbo-cluster gas turbine system.2 to achieve this at lower costs.

[0061] Fig. Figure 5 is a schematic diagram that shows an example of a match between the combustion chamber 4 of the turbo cluster gas turbine system 2 and the first turbocharger 10 of the charging system 8 represents.

[0062] Fig. Figure 6 is a schematic diagram showing the arrangement of the combustion chamber 4 and the first turbocharger 10 of the charging system 8 in an axial view of the output turbine 6 in the Fig. The configuration shown in section 5 is represented.

[0063] In some embodiments, such as in Fig. 5 and Fig. Figure 6 shows the variety of charging systems. 8 configured so that each supplies compressed air to the multitude of combustion chambers 4 supply. In an exemplary embodiment, which is described in Fig. 5 and Fig. As shown in section 6, the number of combustion chambers is... 4 (the number of heating chambers) 16 and the number of charging systems 8 (the number of first turbochargers 10 ) 16, and the number of combustion chambers 4 corresponds to the number of charging systems 8 Therefore, compressed air is supplied by the compressor. 12 of a first turbocharger 10 via the first air duct 15 to a combustion chamber 4 (a heat chamber) was guided.

[0064] In the Fig. 5 and Fig. In the embodiment shown in section 6, it is possible because the first air duct 15 each charging system 8 with the corresponding combustion chamber 4 is connected without being connected to the first air line 15 of another charging system 8 to be connected, to reduce the pressure loss with the help of gentle charging in order to achieve highly efficient combustion.

[0065] By adjusting the number of first turbochargers to be driven 10 from the multitude of early turbochargers 10 Is it possible to implement flexible partial load operation? In the Fig. 5 and Fig. In the example shown in section 6, it is possible to obtain a power output of 1 / 16 of the maximum load.

[0066] In some versions, such as in Fig. 5 and Fig. As shown in section 6, the output turbine 6 a large number of division sections 46 on, which extend in a radial direction, so that a housing 40 the output turbine 6 in a circumferential direction between the combustion chamber 4 and a single-stage stationary bucket 42 the output turbine 6 into a multitude of housing sections 44 is subdivided. This is due to the multitude of combustion chambers. 4 The emitted combustion gas is directed to the housing parts 44fed into. In the illustrated exemplary embodiment, the output turbine has 6 four division sections 46 , which the case 40 the output turbine 6 into four housing sections 44 in the circumferential direction between the combustion chamber 4 and the single-stage stationary bucket 42 the output turbine 6 split, and combustion gas is drawn from the four combustion chambers 4 the housing sections 44 forwarded.

[0067] According to this configuration, it is possible to control the activation and deactivation of the multitude of first turbochargers. 10 , which are the housing parts 44 corresponding, possible, the percentage (a partial insertion ratio) of the housing parts 44 , to which the combustion gas from the multitude of housing parts 44The flow rate is easy to adjust. In the illustrated exemplary embodiment, it is possible to easily change the partial insertion ratio to 25%, 50%, 75%, and 100% and obtain robust characteristics that provide high performance in all load ranges.

[0068] In some embodiments, such as in the one described above, Fig. The configuration shown in section 5 includes the output turbine. 6 a Rateau level 48 with a single-stage stationary bucket 42 and a single-stage rotor blade 43 Since a compressor does not rotate on the shaft 18 the output turbine 6 of the turbo cluster gas turbine system 2 When connected, it is possible through the use of the powerful Rateau stage. 48as a partially inserted turbine to achieve two goals simultaneously (i.e., it is possible to achieve high power output while simultaneously reducing thrust load).

[0069] In some versions, such as in Fig. The heat exchanger is shown in figure 7. 50 in the first air duct 15 provided. In the Fig. In the configuration shown in section 7, the air duct is replaced by the first air duct. 15 Compressed air flowing in the heat exchanger 50 Heat is released with the combustion gas that comes out of the turbine. 28 of the second turbocharger 24 is released, and is then heated with increased temperature of the combustion chamber 4 forwarded.

[0070] In this way it is possible to extract the heat energy from the combustion chamber 4 to collect the emitted combustion gas and to ensure high efficiency of the turbo-cluster gas turbine system 2 to realize.

[0071] In some embodiments, for example, as in Fig. As shown in Figure 8, the energy of the combustion gas exiting the turbine can be... 28 of the second turbocharger 24 is given away, collected through a combination with the Rankine cycle. In the Fig. The configuration shown in diagram 8 includes the turbo cluster gas turbine system. 2 a turbine 54 , a capacitor 56 , a pump 58 and a heat exchanger 60 , which is equipped with a generator 52 is connected. A heating medium that supplies the heat exchanger. 60 from the pump 58 The incoming fluid evaporates with a temperature increase through heat exchange with the fluid from the turbine. 28 of the second turbocharger 24 emitted combustion gas and drives the turbine 54 to.

[0072] In this way, the energy of the combustion gas coming from the turbine can be used. 28is delivered by the electrical power of the generator. 52 can be collected. A steam turbine, for example, can be used as a turbine. 54 in auxiliary systems of passenger ships, merchant ships or barges, and a supercritical CO2 turbine in which a heat exchanger can be manufactured in a compact size can be used as a turbine 54 They are used in warships where a compact size is important.

[0073] In the turbo-cluster gas turbine system 2 are the turbocharger pipes 10 and 24 divided, a heating medium can enter from several directions in Fig. 7 or Fig. 8 heat exchangers shown for example 38 , 50 and 60 The degree of design freedom around the heat exchangers will be introduced. 38 , 50 and 60It can be improved, and the heat exchangers can be manufactured in a compact design. Furthermore, if, for example, a mist separator, a heat exchanger, an exhaust system, and the like are combined to a certain extent and provided for use in each turbocharger, it will be possible to achieve greater efficiency. 10 or 24 Similar to automobiles, the degree of design freedom is improved.

[0074] In some embodiments, such as in Fig. Figure 9 shows the turbo cluster gas turbine system. 2 a piston engine 62 as a starter for igniting the combustion chamber 4 The piston engine 62 is, for example, only in one or two of the many charging systems 8 provided. The piston engine 62 is via the activation line 64 with the first combustion gas line 16 connected, and a valve 66is in the first combustion gas line 16 upstream of the junction between the first combustion gas line 16 and the activation line 64 provided, and a valve 68 is in the activation line 64 provided.

[0075] If the system 2 When activated, the piston engine 62 Compressed air delivered via the activation line 64 and the first combustion gas line 16 the turbine 14 of the first turbocharger 10 directed to initiate the rotation of the first turbocharger 10 to start in a state where the valve 66 closed and the valve 68 is open. The one powered by the turbine 14 of the first turbocharger 10 Guided compressed air is fed to the turbine 28 of the second turbocharger 24 supplied, and the second turbocharger 24begins to rotate. The one from the compressor 26 of the second turbocharger 24 , which begins to rotate, compressed air is drawn from the compressor 26 delivered and to the compressor 12 of the first turbocharger 10 fed and from the compressor 12 further compressed. The air from the compressor 12 The compressed air supplied is routed via the first air line. 15 the combustion chamber 4 (see Fig. 1) supplied, and the combustion chamber 4 It ignites the fuel using the supplied compressed air. In addition, the combustion gas from the combustion chamber is... 4 was delivered, the output turbine 6 directed (see Fig. 1) and the output turbine 6 begins to spin.

[0076] This makes it possible because of the rapid ignition in the combustion chamber. 4through a simple configuration using the piston engine 62 is realized and the output turbine 6 with the combustion chamber 4 The turbo-cluster gas turbine system is driven by the generated combustion gas. 2 to activate quickly.

[0077] While the embodiment of the present invention has been described, the present invention is not limited to the embodiments described above, but includes modifications of the embodiments described above and suitable combinations of these modifications.

[0078] For example, some of the embodiments described above depict a configuration in which the output turbine 6 in the first combustion gas line 16 is provided. In another embodiment, the output turbine can 6 however, on the downstream side of the turbine 28of the second turbocharger 24 will be provided. In the Fig. Each of the 10 depicted configurations includes one of the charging systems. 8 a third combustion gas line 70 to supply the combustion gas that passes through the turbine 28 of the second turbocharger 24 to the output turbine 6 has arrived.

[0079] In this configuration, the temperature of the combustion gas at the combustion chamber outlet can be adjusted. 4 a turbocharger designed for gasoline engines for automobiles, where nickel-based alloys or similar materials are used in the component materials, as a first and second turbocharger, with a heat resistance of approximately 1050°C. 10 and 24 to be used and the cost reduction of the turbo cluster gas turbine system 2 to be realized.

[0080] In some of the embodiments described above, a configuration was shown in which the output turbine is connected to the generator. However, the output turbine can also be connected to a propeller, for example, to provide propulsion for ships. If a turbocharger designed for gasoline engines in automobiles is used as the first and second turbocharger, the output turbine, given the high responsiveness of the turbocharger designed for gasoline engines in automobiles, can be appropriately used to drive the propeller.

[0081] In some of the embodiments described above, a turbo-cluster gas turbine system with a plurality of combustion chambers was depicted. However, the number of combustion chambers contained in a turbo-cluster gas turbine system can be as small as one. In this case, the compressed air generated by a plurality of turbocharging systems is fed into a single combustion chamber.

[0082] In some of the embodiments described above, a charging system with a plurality of secondary turbochargers was depicted. However, the number of secondary turbochargers included in the charging system can be as small as one.

[0083] Furthermore, in another embodiment, a variety of turbo-cluster gas turbine systems can be provided. QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] JP 2000073782 A

[0003]

Claims

[1] A turbo cluster gas turbine system comprising: at least one combustion chamber configured to burn a fuel to produce a combustion gas; an output turbine configured to be driven by the combustion gas from the at least one combustion chamber; and a variety of charging systems configured to supply compressed air to be delivered to at least one combustion chamber, wherein Each of the charging systems includes: a first turbocharger with a rotary shaft that is designed and configured separately from a rotary shaft of the output turbine to be driven by the combustion gas from the combustion chamber; a first air line for supplying compressed air, which is compressed by a compressor of the first turbocharger, to the combustion chamber; and a first combustion gas line to supply the combustion gas from the combustion chamber to a turbine of the first turbocharger. [2] Turbo cluster gas turbine system according to claim 1, wherein each of the charging systems comprises: at least one second turbocharger with a rotational shaft that is separate from the rotational shaft of the output turbine and the rotational shaft of the first turbocharger; a second air line for supplying compressed air, which is compressed by a compressor of the second turbocharger, to the compressor of the first turbocharger; and a second combustion gas line for supplying the combustion gas delivered by a turbine of the first turbocharger to a turbine of the second turbocharger. [3] Turbo cluster gas turbine system according to claim 2, wherein The turbo cluster gas turbine system includes a large number of combustion chambers, and The multitude of charging systems is configured to each supply compressed air to the multitude of combustion chambers. [4] Turbo cluster gas turbine system according to claim 2 or 3, wherein the output turbine is provided in the first combustion gas line. [5] Turbo cluster gas turbine system according to claim 2 or 3, wherein each of the charging systems includes a third combustion gas line for supplying the combustion gas that has passed through the turbine of the second turbocharger to the output turbine. [6] Turbo cluster gas turbine system according to any one of claims 2 to 5, wherein each of the charging systems includes an intercooler provided in the second air duct. [7] Turbo cluster gas turbine system according to any one of claims 2 to 6, wherein the sum of the number of first turbochargers and the number of second turbochargers is 10 or more. [8] Turbo cluster gas turbine system according to any one of claims 2 to 7, further comprising: a heat exchanger for carrying out a heat exchange between the compressed air flowing through the first air line and the combustion gas emitted from the turbine of the second turbocharger. [9] Turbo cluster gas turbine system according to any one of claims 2 to 7, further comprising: a heat exchanger for carrying out heat exchange between a heating medium and the combustion gas emitted by the turbine of the second turbocharger; and a turbine configured to be driven by the heating medium discharged from the heat exchanger. [10] Turbo cluster gas turbine system according to any one of claims 1 to 9, further comprising: a piston engine; an activation line that connects an outlet of the piston engine to the first combustion gas line; a valve provided in the first combustion gas line upstream of a connection point between the first combustion gas line and the activation line; and a valve provided in the activation line. [11] Turbo cluster gas turbine system according to any one of claims 1 to 10, wherein the first turbocharger is configured to meet heat resistance requirements against the combustion gas. [12] Turbo cluster gas turbine system according to any one of claims 1 to 11, wherein the first turbocharger is a turbocharger designed for an automotive gasoline engine. [13] A turbo cluster gas turbine system activation method comprising: Supplying compressed air, emitted by a piston engine, to a turbine of a first turbocharger to set the first turbocharger in rotation; Supplying compressed air, delivered by a compressor of the first turbocharger that has started to rotate, to a combustion chamber; Igniting a fuel using the compressed air supplied to the combustion chamber; and delivering a combustion gas discharged from the combustion chamber to an output turbine to allow the output turbine to rotate. [14] Turbo cluster gas turbine system activation method according to claim 13, further comprising: Supplying compressed air that has passed through the turbine of the first turbocharger to a turbine of a second turbocharger, in order to allow the second turbocharger to rotate; and Supplying compressed air, which is delivered from a compressor of the second turbocharger, which begins to rotate, to the compressor of the first turbocharger.

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