JP3900026B2 - Manufacturing method of gas turbine equipment - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a method for manufacturing a gas turbine used in various gas turbine systems.
[0002]
[Prior art]
Since the exhaust temperature of the gas turbine is as high as about 500 ° C., for example, as described in the Journal of the Gas Turbine Society of Japan Vol.25, No.97 (1997), combined cycle, combined heat and power cycle, regeneration cycle, high humidity For example, a minute use cycle is used, and higher efficiency than a simple cycle is achieved. In these cycles, lowering the pressure ratio and raising the exhaust temperature, or raising the turbine inlet temperature and raising the exhaust temperature, may improve the overall system efficiency, rather than the maximum efficiency point of the simple cycle. is there.
[0003]
Further, for example, in a high humidity utilization cycle as disclosed in International Publication No. WO 98/48159, moisture is mixed into the compressor discharge air to drive the turbine, so that the capacity of the turbine relative to the capacity of the compressor is reduced. , Larger than other cycles. Therefore, it is necessary to develop a gas turbine for a high-humidity utilization cycle separately from the simple cycle. Or used in relatively small gas turbines as shown in the literature (Upgrading of a Small Size Gas Turbine to HATCycle Operation: Thermodynamic and Economic Analysis, Umberto Desideri and Francesco di Maria, ASME Paper 99-GT-372, 1999) It is necessary to configure a high-humidity utilization cycle by combining a compressor used with a turbine used in a relatively large gas turbine. Alternatively, as disclosed in JP-A-11-229894, movable blades are provided in a part of the compressor or turbine so that the compressor and the turbine can be used in a simple cycle and a high-humidity utilization cycle. It is necessary to take matching.
[0004]
[Problems to be solved by the invention]
As described above, even in a gas turbine used under the same flow rate, temperature, and pressure conditions, the optimum compression ratio for each cycle and the flow rates of the compressor and the turbine change. Turbine needs to be designed. However, designing and producing a compressor and turbine for each cycle is costly and increases the number of parts to be managed.
[0005]
The objective of this invention is providing the manufacturing method of the gas turbine equipment which can be applied to various cycles.
[0006]
[Means for Solving the Problems]
In order to achieve the above object, according to the present invention, a main part of the gas turbine equipment is set in advance based on roughly set conditions (for example, turbine inlet temperature and flow rate), and a desired part is set based on the main part. The number of stages of the compressor and the turbine for obtaining conditions suitable for the cycle (for example, turbine outlet temperature) is set, and the compressor and turbine of the set number of stages among the main parts are combined to be configured.
[0007]
DETAILED DESCRIPTION OF THE INVENTION
FIG. 2 is a schematic diagram of a simple gas turbine cycle having a main part of a preset gas turbine facility according to an embodiment of the present invention. The air 101 is sucked from the louver 2 at the inlet of the intake chamber 1, cleaned by the filter 3, passes through the intake guide vanes 5 provided in the intake outer cylinder 4, and is compressed by the compressor 6. For example, the compressor shown in FIG. 2 is a 16-stage compressor having 16 compressor blades 8 and 16 compressor vanes 9 in a compressor outer cylinder 7, and has an optimum pressure ratio for a simple gas turbine cycle. Designed to be Of the 16 stages, the 14 stages on the downstream side are designed to have an optimum flow rate and pressure ratio when used in a high-humidity utilization cycle described later. Of the 16 stages, the 14 stages on the upstream side are designed to have an optimum pressure ratio when used in a combined cycle and a combined heat and power cycle described later.
[0008]
The high-pressure air 102 compressed by the compressor flows into the combustor 11 through the main body outer cylinder 10. The combustor 11 includes a combustor outer cylinder 12, a combustor cover 13, a fuel nozzle 14, a combustor liner 15, a combustor tail cylinder 16, and the like. The high-pressure air 102 flowing into the combustor 11 flows toward the combustor head while cooling the combustor tail cylinder 16 and the combustor liner 15, and passes through an opening provided in the combustor liner 15. It flows into the liner 15. Then, it is mixed with the fuel 201 ejected from the fuel nozzle 14 and combusted to become a high-temperature combustion gas 106, which is guided to the turbine 17 through the combustor liner 15 and the combustor tail cylinder 16.
[0009]
For example, the turbine in FIG. 2 is a four-stage turbine having four turbine stationary blades 19 and four turbine rotor blades 20 in a turbine outer cylinder 18 and designed to have an optimum expansion ratio for a simple gas turbine cycle. Has been. Of these four stages, the upstream two stages are designed to have an optimum load and expansion ratio when used in a two-shaft gas turbine described later. The upstream three stages are designed to have an optimum expansion ratio when used in a combined cycle, a combined heat and power cycle, and a regeneration cycle, which will be described later. The combustion gas 106 expands when passing through the stationary and moving blades of the turbine 17, and the pressure and temperature decrease, and is discharged as turbine exhaust gas 107.
[0010]
FIG. 6 is a flow diagram of a method of manufacturing a gas turbine used in various cycles, mainly including the above-described simple cycle gas turbine, in particular, each stage of the compressor, a combustor liner, a combustor tail, a turbine moving blade and the like. . Here, a case will be described in which the temperature and flow rate at the turbine inlet are set conditions (step 101), and the compressor and turbine stage numbers are designed so that the turbine outlet temperature conditions of various cycles are appropriate.
[0011]
For example, consider the high-humidity utilization cycle gas turbine described below. First, the main part of the gas turbine having a plurality of stages of compressors and turbines is designed (step 102), and then the turbine outlet temperature at which optimum efficiency is obtained from the cycle calculation (step 103). The high-humidity utilization cycle is a cycle that is used for combustion after humidifying the compressor discharge air and regenerating the exhaust gas from the turbine outlet. Therefore, the higher the turbine outlet temperature, the higher the temperature of the combustion air. Therefore, if the turbine inlet temperature is the same, the amount of fuel can be reduced, and the gas turbine efficiency is improved. The upper limit of the turbine outlet temperature is limited by the heat resistance conditions of the regenerator, but the optimum turbine outlet temperature is higher than that in the simple cycle.
[0012]
Next, a pressure ratio for obtaining the turbine outlet temperature is obtained (step 104). When the turbine inlet temperature is substantially the same, the lower the pressure ratio, the higher the turbine outlet temperature. Therefore, the high humidity utilization cycle has a smaller pressure ratio than the simple cycle. Then, the number of stages of the compressor and turbine that are the pressure ratio is set (steps 105 and 106).
[0013]
In parallel with the setting of the number of stages, a compressor flow rate for obtaining the set turbine inlet flow rate is set (step 107). In the high-humidity utilization cycle, moisture is added to the compressor discharge air, so the turbine flow rate is higher than the compressor flow rate, and in some cases is about 1.2 times. Therefore, the required compressor flow rate is obtained from the set humidification amount, and the inlet area of the compressor first stage moving blade portion that can obtain the flow rate is calculated using the corrected flow rate (step 108). As described above, when the turbine inlet flow rate is substantially the same, the high humidity utilization cycle has a smaller compressor flow rate than the simple cycle, so the inlet area of the compressor first stage moving blade portion also becomes smaller.
[0014]
Based on the above setting results, a combination of the number of stages satisfying the number of compressor stages and the inlet area is selected from a plurality of compressors of a simple cycle designed in advance (step 109). Since the high-humidity utilization cycle has a smaller pressure ratio and a smaller compressor flow rate than the simple cycle, a part of the rear stage side of a plurality of compressors in the simple cycle is selected as will be described later. Similarly, a combination of turbines is also selected (step 110), and these are combined with a combustor to constitute a gas turbine (step 111). Further, a humidifier, a regenerator, a heat exchanger, etc. are used to utilize high humidity. A gas turbine system is configured (step 112).
[0015]
As described above, the case of the high-humidity utilization cycle has been described, but the system can be configured by the same method for the combined cycle, the combined heat and power cycle, the regeneration cycle, and the like. In the present embodiment, the temperature and flow rate at the turbine inlet are set as the setting conditions. However, the flow rate, pressure, temperature, and the like of the compressor, combustor, and turbine can also be set. It is also possible to make the main part of the gas turbine common by including a bearing and an outer cylinder.
[0016]
Next, the case where the same method is applied to a two-shaft gas turbine will be described with reference to FIG. In the case of a two-shaft gas turbine, the number of stages can be selected for the compressor in the same manner as described above. That is, the output turbine outlet temperature at which the optimum efficiency is obtained is obtained (step 121), the pressure ratio at which the required output turbine outlet temperature is obtained (step 122), and the number of compressor stages at which the required pressure ratio is obtained (step 105). Next, a combination satisfying the compressor inlet area and the number of stages is selected from a plurality of compressors designed in advance (step 109), and as a result, the compressor power is obtained (step 123).
[0017]
The compressor driven turbine selects the turbine outlet temperature so that the turbine work is balanced with this compressor power (step 124). Hereinafter, similarly, the pressure ratio which becomes the required driving turbine outlet temperature is obtained (step 125), and the number of stages of the compressor driving turbine which becomes the required pressure ratio is selected (step 106). However, since the number of stages of the turbine is smaller than that of the compressor, it is better to set the work distribution so that it can be easily used for the two-shaft turbine when designing the turbine of the simple cycle gas turbine. Similarly, regarding the compressor, when designing a compressor of a simple cycle gas turbine, it is desirable to set each stage so that it can be easily used for a desired cycle.
[0018]
Next, examples of various cycles configured by the above-described method will be described below.
[0019]
FIG. 1 is a schematic diagram of a high humidity utilization cycle. A different part from the above simple cycle will be described below. After the air 101 is cleaned by the filter 3, water 202 is sprayed from the intake humidifier 21 installed in the intake chamber 1. As a result, the temperature of the air 101 increases, but at the same time the temperature decreases. Therefore, the gas turbine output and the gas turbine efficiency increase due to the effect of increasing the compressor suction flow rate and the effect of decreasing the compression power. The compressor 6 has 14 moving and stationary blades, that is, 14 stages, and is smaller than the above-described simple cycle. This reduction in the number of stages serves to lower the pressure ratio of the system than a simple cycle. The reduction in the number of stages at this time is reduced by two stages upstream of the compressor with respect to the simple cycle.
[0020]
As a result, the compressor suction flow rate is reduced, offset by the increase in water sprayed into the high-pressure air, and the flow rate flowing into the turbine can be reduced constant or slightly. Therefore, it is not necessary to change the upstream stage of the turbine, which is difficult to develop. Also, since the downstream 14 stages use the same parts as the simple cycle, the development of compressor blades should be shared even when configuring two types of gas turbine systems, the simple cycle and the high humidity utilization cycle. Can do.
[0021]
Furthermore, when the number of upstream two stages is reduced, a member that is substantially disk-shaped and whose outer peripheral part becomes a part of the inner peripheral wall of the general annular flow path of the compressor or turbine is added to the disk part of the reduced paragraph. Inserted. For example, as shown in FIG. 8, the distance between the bearings of the gas turbines of a plurality of cycles can be obtained by inserting two stages of a dummy disk 30 without compressor blades and blade mounting grooves (having a flat outer peripheral surface) into the disk portion. And the rotor length can be the same as the simple cycle. This eliminates the need to change the structure of the intake outer cylinder 4, the compressor outer cylinder 7, and the bearings and stacking bolts (not shown), thereby shortening the design period and making the parts common. As shown in FIG. 8, the dummy disk 30 may be a member having a smooth outer peripheral portion, but as shown in FIG. 9, a compressor blade mounting member used in a simple cycle may be shared. In this case, it is desirable to attach a dummy key 31 to the blade mounting groove as shown in FIG. 9 so that the flow path shape in the compressor is smooth and the pressure loss is reduced. By using this dummy key 31, even when the usage method of the gas turbine is changed from the high-humidity utilization cycle to the simple cycle, the dummy key is removed and the compressor blades are inserted, which can be easily changed.
[0022]
The high-pressure air 102 compressed by the compressor 6 and flowing into the combustor 11 flows through the main body outer cylinder 10 while cooling the combustor tail cylinder 16 and is extracted from the extraction port of the main body outer cylinder. At this time, the air that cools the combustor tail cylinder 16 has low temperature and high humidity, so that the cooling effect is enhanced. Moreover, the seal plate 22 is installed between the main body outer cylinder 10 and the combustor outer cylinder 12, and the mixing of air before and after regeneration can be prevented and the regeneration effect can be maintained high. Thereafter, water 203 is sprayed from the high-pressure humidifier 23 to further increase the humidity and decrease the temperature, and then the heat is exchanged with the turbine exhaust gas 107 in the low-temperature regenerator 24 to increase the temperature. All evaporates. At this time, since the air before regeneration becomes low temperature and high humidity, the regeneration effect is enhanced. Thereafter, the high-temperature regenerator 25 exchanges heat with the higher-temperature turbine exhaust gas 107 to further increase the temperature, and flows into the combustor 11 from the inlet of the combustor outer cylinder. At this time, since all of the spray water 203 is evaporated in the low temperature regenerator 24, there is no erosion or impurity sticking in the high temperature regenerator 25, and the reliability of the high temperature regenerator is increased.
[0023]
This high-temperature, high-humidity air is used for combustion in the same way as a simple cycle gas turbine, but it contains a large amount of moisture, which lowers the local flame temperature and greatly reduces the amount of nitrogen oxides produced during combustion. be able to.
[0024]
The turbine 17 has the same four stages as the simple cycle. However, since the turbine inflow amount is designed to be slightly reduced due to the reduction in the compressor flow rate described above, the pressure and the expansion ratio are accordingly reduced. As the number of compressor stages is reduced, the pressure ratio of the system decreases, so the temperature of the turbine exhaust gas 107 increases. As a result, the temperature of the high-temperature and high-humidity air 105 is also increased. Therefore, if the temperature of the combustion gas 106 is the same, the amount of the fuel 201 can be reduced, and the gas turbine efficiency is improved. In the present embodiment, the pressure ratio is lowered by reducing the turbine inflow amount, but the pressure ratio can also be lowered by slightly reducing the attachment angle of the turbine stationary blade to increase the opening area. In this case, it is necessary to slightly modify the turbine shape, but since the flow rate can be increased, the cycle output can be increased.
[0025]
As described above, in the high-humidity gas turbine, efficiency can be improved by increasing the temperature of the turbine exhaust gas. However, as a method of increasing the temperature of the turbine exhaust gas, the method of decreasing the pressure ratio and the combustion gas temperature described above can be used. There is a way to lower. The method of lowering the pressure ratio of this embodiment can keep the combustion gas temperature constant, so that it is difficult to develop, and it is not necessary to change the combustor liner, combustor tail cylinder, and stationary and moving blades in the upstream stage of the turbine.
[0026]
The turbine exhaust gas 107 sequentially flows into the high-temperature regenerator 25 and the low-temperature regenerator 24, exchanges heat with the high-humidity air 104, decreases in temperature, and is discharged as a low-temperature exhaust gas 108. Since the final exhaust gas temperature is lower than that of the simple cycle, the thermal energy is effectively used correspondingly, and the turbine efficiency is improved.
[0027]
FIG. 3 shows an outline of a combined cycle or a combined heat and power cycle. By heat exchange with the gas turbine exhaust gas 107, the feed water 109 is changed to steam 110 by the boiler 26 and further heated by the heater 27 to obtain heated steam 111. When the steam turbine 28 is rotated using this heated steam, a combined cycle is obtained, and when the heated steam 111 is used as a steam or a heat source, a combined heat and power cycle is obtained.
[0028]
In this embodiment, the compressor has 14 stages and the turbine has 3 stages. By reducing the number of stages with respect to the simple cycle, the temperature of the turbine exhaust gas 107 can be increased while keeping the combustion gas temperature constant, so that the temperature of the heated steam 111 is also increased, and the output of the steam turbine 28 is increased in the combined cycle. Increases efficiency. In the combined heat and power cycle, the temperature, pressure or flow rate of the heating steam 111 can be increased, and the supply specification range for the heat demand can be widened.
[0029]
In addition, the compressor and turbine share the upstream stage components for the simple cycle, and the combustion gas temperature is constant. Therefore, the combustor liner, combustor tail, and turbine upstream stage Wings do not need to change. Since these parts are used at high temperatures, they are developed using heat-resistant materials and advanced cooling techniques. Therefore, if the parts can be shared in each cycle, the development cost is greatly reduced. In addition, the reliability of high-temperature parts, such as the lifespan, is confirmed by endurance tests under conditions that simulate actual loads or actual loads, but reliability test data can be used because common parts can be used in various cycles. This improves the reliability of high-temperature parts. As in the case of FIG. 2, the compressor stage number can be reduced by inserting a dummy disk into two downstream stages and making the rotor length the same. However, in this embodiment, as another case, the rotor length is reduced according to the stage number reduction. To reduce the number of parts and reduce the overall length.
[0030]
FIG. 4 shows an outline of the regeneration cycle. By heat exchange with the gas turbine exhaust gas 107, the temperature of the high-pressure air 103 is raised and the high-temperature air 113 is used for combustion. In this embodiment, the compressor has 14 stages and the turbine has 3 stages. By reducing the number of stages with respect to the simple cycle, the temperature of the turbine exhaust gas 107 can be increased while the combustion gas temperature is kept constant. As a result, the temperature of the high-temperature air 113 is also increased. Therefore, if the temperature of the combustion gas 106 is the same, the amount of the fuel 201 can be reduced, and the gas turbine efficiency is improved. Moreover, since the temperature of the high-pressure air 103 is reduced by reducing the pressure ratio, the temperature of the low-temperature exhaust gas 108 is also reduced, and the thermal energy is effectively used by that much, and the gas turbine efficiency is improved.
[0031]
In addition, the compressor and turbine share the upstream stage components for the simple cycle, and the combustion gas temperature is constant. Therefore, the combustor liner, combustor tail, and turbine upstream stage Wings do not need to change. This advantage is the same as in the combined cycle described above.
[0032]
FIG. 5 shows an outline of a two-shaft gas turbine in which the shafts of the compressor driving turbine and the output extracting turbine 29 are separated. Since the upstream two-stage turbine of the other cycle is designed to obtain the power required to drive the two-shaft compressor, the upstream two-stage turbine of the two-shaft gas turbine is Parts can be shared with the upstream two-stage turbine. In addition, the output take-out turbine can freely set the rotational speed and the like in accordance with the specifications of the generator, compressor, pump, and the like serving as loads.
[0033]
As described above, the common use of gas turbine parts is any one of the various cycles such as the simple cycle, the combined cycle, the combined heat and power cycle, the regeneration cycle, the high-humidity utilization cycle, and the two-shaft gas turbine cycle. This is possible by combining two or more types of cycles.
[0034]
Furthermore, in the above gas turbine, the pressure ratio, temperature, and flow rate matching can be finely adjusted by making minor changes to the compressor first stage or final stage after changing the number of stages, or the turbine final stage after changing the number of stages. It is also possible to improve. In this case as well, most of the stages of the compressor and turbine are configured with the same parts as before changing the number of stages. Therefore, heat resistant materials are used because of the high operating temperature and most of the compressor blade rows that are difficult to develop. As for the blades on the upstream side of the turbine developed using advanced cooling technology, the development can be made common, the cost is reduced, the number of parts used for maintenance is reduced, and management is facilitated. In addition, the reliability of high-temperature parts, such as the lifespan, is confirmed by endurance tests under conditions that simulate actual loads or actual loads, but reliability test data can be used because common parts can be used in various cycles. This improves the reliability of high-temperature parts.
[0035]
According to this embodiment shown in FIGS. 1 to 9 described above, in various cycles such as a simple cycle, a combined cycle, a combined heat and power cycle, a regeneration cycle, a high-humidity utilization cycle, a two-shaft gas turbine cycle, etc., a compressor, a combustion Parts such as combustors and turbines, in particular, high-temperature parts such as combustor liners, combustor tails, and turbine stationary and moving blades, can reduce development and production costs and parts management costs.
[0036]
In addition, by using a compressor or turbine with a smaller number of stages compared to a simple cycle, by configuring various cycles such as a combined cycle, a combined heat and power cycle, a regeneration cycle, a high-humidity utilization cycle, a two-shaft gas turbine cycle, Compared with the simple cycle, the pressure ratio can be lowered and the combustion gas temperature can be made constant, so that it is not necessary to change the high-temperature parts such as the combustor liner, combustor tail cylinder, turbine stationary blade and moving blade.
[0037]
When designing compressors and turbines that are suitable for various cycles, when moving compressors or turbines with movable blades and adjusting them to achieve the optimal compression ratio and compressor / turbine flow rates, the corresponding parts The score increases and the cost increases. In addition to this, in particular, when a movable part is provided in a high temperature part such as a turbine, careful verification for reliability is required. However, in this embodiment, it is possible to adjust the compression ratio and the flow rates of the compressor and the turbine that are optimal for each cycle without providing movable blades.
[0038]
Therefore, it is possible to prepare a product lineup that can respond to output, efficiency, and heat demand while keeping these high-temperature parts that require labor, cost, and time for development in common. At that time, since high temperature components are common to all products, reliability evaluation such as life can be performed in an integrated manner, and a more reliable product group can be constructed.
[0039]
In addition, since the rotor length can be made the same in each cycle by inserting a dummy disk and a dummy key when the number of compressor stages is reduced, the structure of the intake outer cylinder 4, the compressor outer cylinder 7, the bearing, and the stacking bolt No change is required, shortening the design period and sharing parts.
[0040]
【The invention's effect】
According to the present invention, it is possible to provide a method for manufacturing a gas turbine equipment that can be applied to various cycles.
[Brief description of the drawings]
FIG. 1 shows a high-humidity gas turbine according to an embodiment of the present invention.
FIG. 2 is a simple cycle gas turbine.
FIG. 3 is a combined or combined heat and power cycle gas turbine.
FIG. 4 is a regeneration cycle gas turbine.
FIG. 5 is a two-shaft gas turbine.
FIG. 6 is a stage number setting flow according to an embodiment of the present invention.
FIG. 7 is a flowchart for setting the number of stages of a two-shaft gas turbine according to an embodiment of the present invention.
FIG. 8 shows an example of a dummy disk.
FIG. 9 shows an example of a dummy key.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Intake chamber, 2 ... Louver, 3 ... Filter, 4 ... Intake outer cylinder, 5 ... Intake guide blade, 6 ... Compressor, 7 ... Compressor outer cylinder, 8 ... Compressor moving blade, 9 ... Compressor stationary blade, DESCRIPTION OF SYMBOLS 10 ... Main body outer cylinder, 11 ... Combustor, 12 ... Combustor outer cylinder, 13 ... Combustor cover, 14 ... Fuel nozzle, 15 ... Combustor liner, 16 ... Combustor tail cylinder, 17 ... Turbine, 18 ... Outside the turbine Tube 19, turbine vane, 20 turbine blade, 21 intake air humidifier, 22 seal plate, 23 high pressure humidifier, 24 low temperature regenerator, 25 high temperature regenerator, 26 boiler, 27 heating 28 ... Steam turbine, 29 ... Output turbine, 30 ... Dummy disk, 31 ... Dummy key, 101 ... Air, 102 ... High pressure air, 103 ... Extracted air after cooling the tail cylinder, 104 ... Low temperature high humidity air, 105 ... High temperature Humid air 106 ... Combustion gas 107 ... Turbine exhaust gas, 108 ... cold gas, 109 ... boiler feed water, 110 ... steam, 111 ... heating steam, 112 ... condensed water, 201 ... fuel, 202 ... intake water spray, 203 ... high-pressure water spray.

Claims (4)

A manufacturing method for a gas turbine equipment for perforated multiple stage compressor and turbine, by changing the number of stages in advance designed compressor and turbine becomes applicable criteria to a plurality of cycles, the said reference compressor or if less of causing reduction of the number of stages of the turbine, and its outer peripheral portion to the reduced paragraph also the compressor fitted with a member forming the inner peripheral wall of the annular channel of the turbine, compressor or turbine decreased paragraph configured, manufacturing method for a gas turbine equipment, characterized in that formed by combining the compressor 及 beauty turbine. A manufacturing method for a gas turbine equipment for perforated multiple stage compressor and turbine, by changing the number of stages in advance designed compressor and turbine becomes applicable criteria to a plurality of cycles, depending on the desired cycle , pressure ratio of the compressor and the gas turbine becomes turbine outlet temperature necessary to the desired cycle, and, in accordance with the compressor inlet area to the turbine flow rate and the compressor flow rate required the desired cycle, with the reference When the number of stages of the compressor and turbine is set and the number of stages of the reference compressor or turbine is reduced according to the setting, the outer periphery of the disk portion of the reduced paragraph is the annular shape of the compressor or turbine. A compressor or turbine having a reduced number of paragraphs is formed by attaching a member forming an inner peripheral wall of the flow path, and the compressor and turbine having the set number of stages are configured. Manufacturing method for a gas turbine equipment, characterized in that configured by combining. In a gas turbine facility equipped with a multi-stage compressor and turbine,
The compressor and turbine are a compressor and a turbine configured to by changing the number of stages it becomes applicable to various cycles, a stepped-down portion which is manually formed to the number of stages which are suitable for the desired cycle, the number of stages changes a member attached to the disc portion of the reduced paragraph, the outer peripheral portion thereof a disk shape or the compressor and having the members forming part of the inner peripheral wall of the annular channel of the turbine Gas turbine equipment. 4. The gas turbine equipment according to claim 3, wherein the member is a dummy disk having an outer peripheral surface formed into a flat surface , and is configured to be inserted into a disk portion of the compressor or the turbine. .

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