JP2007309225A - Gas turbine device - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To miniaturize and simplify a system, to improve reliability, and to reduce facility cost. <P>SOLUTION: This invention is a gas turbine device 20 for cooling a lubricating oil cooler, a gas turbine and driven machines, by making cooling air flow in an enclosure, by storing the gas turbine 21 having the lubricating coil cooler 29 and the driven machines 23 and 24 in the enclosure, and supplies the whole quantity of the cooling air to the gas turbine in the enclosure 25 as engine combustion air, after cooling the lubricating oil cooler, the gas turbine and the driven machines via a cooling air flow passage constituted in the enclosure 25. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a gas turbine device, and in particular, by adopting a configuration in which the entire amount of ventilation air used for heat radiation of the gas turbine and heat radiation of the driven machine is used as combustion air supply for the gas turbine, Improvement, downsizing of equipment, and abolition of ventilation and exhaust work were realized. The driven machine referred to in the present invention is a device that is driven to rotate by being connected to a rotational drive shaft of a gas turbine, for example, a device that rotates by receiving power from a speed reducer, a generator, etc. Say.

  The gas turbine includes a compressor, a turbine and a combustor that are connected to the compressor, and generates high-temperature and high-pressure gas by mixing and burning the air and fuel pressurized by the compressor in the combustor. In this gas expansion process, the turbine is rotationally driven, a part of which is used as the driving power for the compressor, while the remaining part is taken out as rotational power, and the generator and other driven machines connected to this output shaft are driven. The residual gas is discharged to the outside through the exhaust port.

  As shown in FIG. 4, the conventional gas turbine 1 is configured as a gas turbine device housed in a packaged or unitized state together with the driven machine 3 inside a soundproof enclosure 2.

  The total required air amount of the combustion air of the gas turbine 1, the cooling air mainly for the lubricating oil cooler 5, and the cooling air of the driven machine (for example, the generator) 3 is used as a common supply fan 4. As shown by the flow of the arrow, the gas turbine 1 sucks in the required amount of air with its compressor, and the lubricating oil cooler 5 sucks in the required amount with the cooling fan 8 arranged immediately before. For the cooling air, for example, a required amount of air flows through a fan built in the generator.

  Exhaust gas from the gas turbine 1 is exhausted from an exhaust duct 6, and air that has been cooled at each part is exhausted to the outside by an exhaust fan 9 through an exhaust duct 7 provided on the downstream side of the enclosure 2. Discharged.

  As described above, the cooling fan 8 and the exhaust fan 9 which are ventilation means for cooling are conventionally configured to be driven by the external power source.

  However, since the cooling fan 8 and the exhaust fan 9 use an external power source as power, the operation cannot be continued even if the gas turbine 1 itself is healthy due to an external power signal signal mistake, an operation error, or an external equipment failure. was there.

  In addition, with such a configuration, ventilation and exhaust duct work is required to discharge the cooling air, and costs and work periods corresponding to the work are required. In addition, there is a system (draft type) that draws and exhausts ventilation exhaust by the exhaust system draft of the gas turbine and discharges it together. In this case, the duct of the exhaust ventilation system is unnecessary, but the amount of exhaust gas can be reduced However, since the exhaust gas system has the same large capacity as the conventional one, there is a similar problem in that the construction cost increases as in the conventional example described above. Further, the draft type is not applicable to a system having a long exhaust system and high exhaust pressure.

  Furthermore, as the air supply system, three systems of intake air for combustion of the gas turbine 1, supply air for cooling the lubricating oil, and supply air for cooling the driven machine 3 are separately required. As a result, the required amount of intake air for the entire apparatus increases, and the apparatus itself and peripheral equipment increase in size.

  On the other hand, in the following Patent Documents 1 and 2, it is described that a part of the ventilation air for heat radiation from the turbine is mixed into the combustion air supply of the gas turbine.

  Patent Document 3 below describes that air in the cooling air passage is communicated to the gas turbine intake side when the combustion air is insufficient during deceleration of the gas turbine.

Furthermore, Patent Document 4 below describes that the intake air is heated and can be cooled.
Japanese Utility Model Publication No. 5-89848 Japanese Patent Publication No. 2005-140068 Japanese Patent Publication No. 2002-242701 Japanese Patent Publication No. 9-317496

  However, the techniques described in the above patent documents are limited to the use of the necessary ventilation. In other words, gas turbines are said to be able to obtain higher output when the intake air temperature is essentially lower, so that the technology described in each patent document incorporates more ventilation than necessary, so that the intake air temperature does not rise more than necessary. It had a configuration with a function to adjust the ventilation.

  For example, in the technique described in Patent Document 1, in order to solve the icing of the gas turbine supply air, a part of the ventilation air for heat radiation from the gas turbine is mixed with a part of the supply air for combustion of the gas turbine to increase the temperature. Since it has ventilation and its adjustment system, a ventilation device, a power source, etc. are necessary, and construction accompanying this is also unchanged.

  Further, in the technique of Patent Document 2, when the supply temperature of the gas turbine is low, the gas turbine combustion supply air is mixed into the gas turbine combustion supply air by using the ventilation air radiated from the gas turbine, and the intake temperature is increased to improve the power generation efficiency. Therefore, it is not always applied during operation, and is operated only when the intake air temperature is low.

  Furthermore, the technique of Patent Document 3 functions only when the amount of combustion air is insufficient at the time of gas turbine stop deceleration, and is not always applied during operation.

  Furthermore, in the technique of Patent Document 4, an attempt is made to improve performance by selecting overheating and cooling, and a ventilation system exists as before. The use of heat is a heat exchanger, which is complicated in terms of system.

  The present invention solves the above problems, and its purpose is to reduce the size and simplify the system by directly taking in the entire amount of air used for heat dissipation of the gas turbine and the driven machine as combustion intake air for the gas turbine. The system is designed to reduce the cost of equipment by improving ventilation and improving reliability, eliminating the need for ventilation and exhaust work.

  In order to achieve the above object, the present invention includes a gas turbine having a lubricating oil cooler and a driven machine in an enclosure, and circulating cooling air in the enclosure, whereby the lubricating oil cooler and the gas are circulated. In the gas turbine apparatus for cooling the turbine and the driven machine, the cooling oil after cooling the lubricating oil cooler, the gas turbine, and the driven machine through the cooling air flow path configured in the enclosure is used as an engine. The combustion gas is supplied to the gas turbine in the enclosure.

  According to a second aspect of the present invention, in the first aspect, the air flow path configured in the enclosure includes a first flow path that reaches the gas turbine after passing through the lubricating oil cooler, and the driven machine. It has the 2nd flow path which reaches the gas turbine after progress.

  According to a third aspect of the present invention, in the second aspect, the total flow rate of air flowing through the first flow path and the second flow path is set to be smaller than an engine combustion air amount of the gas turbine. The increase in the negative pressure generated in the enclosure due to the suction of air by the gas turbine increases the flow rate of the air flowing through the first flow path and the second flow path, thereby increasing the allowable air amount of the gas turbine. It is characterized by satisfaction.

  According to a fourth aspect of the present invention, in the second aspect of the present invention, the air flow path configured in the enclosure further includes a third flow path from outside the enclosure to the gas turbine, The flow rate in the third flow path is set so that the flow rate of the flowing air is substantially the same as the engine combustion air amount of the gas turbine.

  According to the first aspect of the present invention, since the ventilation for cooling can be used for the combustion air of the entire gas turbine device, the exhaust for ventilation and the exhaust for combustion can be unified, and the construction of the ventilation exhaust duct can be performed. Further, since the ventilation air is forced to flow by the intake operation for combustion, a fan driven by external power is unnecessary, and the total amount of intake air can be reduced, so that the apparatus is simple and compact.

  It is said that the output of the gas turbine is essentially higher when the intake air temperature is lower, but the required output can be generated even if the gas turbine inhales high-temperature air such as ventilation exhaust air. By designing to obtain an appropriate cycle efficiency, the gas turbine satisfies the allowable performance. However, although the dimensions of the gas turbine itself may be slightly larger, the entire system is advantageous in reducing overall dimensions and costs by reducing the required intake air amount and eliminating the ventilation and exhaust system. .

  According to the invention of claim 2, in addition to the operation and effect of claim 1, efficient cooling in the enclosure and subsequent intake operation are performed.

  According to the third aspect of the invention, in addition to the operation and effect of the second aspect, the flow rate of the air flowing through the first and second flow paths due to the margin of the intake capacity of the gas turbine generating a negative pressure in the enclosure Is increased to satisfy the allowable amount of air in the gas turbine, so that the necessary amount of ventilation can be supplied to the inlet of the gas turbine without a shortage of air.

  According to the fourth aspect of the invention, in addition to the operation and effect of the second aspect, by setting the air flow rate in the third flow path, it is possible to reliably supply the necessary ventilation amount to the inlet of the gas turbine.

The best mode of the present invention will be described below with reference to the accompanying drawings.
FIG. 1 is a schematic cross-sectional view showing a first embodiment of a gas turbine apparatus according to the present invention. In the figure, a gas turbine device 20 includes a gas turbine 21, a generator 24 that is connected to an output shaft 22 of the gas turbine 21 via a speed reducer 23, and an enclosure 25 that houses these generators 24.

  The gas turbine 21 includes a compressor 26, a turbine 27 coaxially arranged with the compressor 26, and a combustor 28, and cools the lubricating oil circulated and supplied to each movable part of the compressor 26 and the turbine 27. A lubricating oil cooler 29 is provided in the enclosure 25.

  An air intake 30 is opened on the upstream side of the enclosure 25, and air introduced from the air intake 30 is separated from the first flow path (1) passing through the lubricating oil cooler 29 by the partition wall 31. The second flow path (2) that passes through the generator 24 and the second flow path (2) is branched and flows toward the downstream side in the enclosure 25.

  The ventilation air that has finished exchanging heat while being in contact with each portion flows in the direction indicated by the arrow, and is entirely taken in as combustion air through the intake port 26a of the compressor 26. The gas is mixed with fuel in 28 to generate a high-temperature and high-pressure gas, and the turbine 27 is rotationally driven by this gas.

  In this example, the ventilation air amount is determined by the total opening area of the flow paths (1) and (2), and at the same time, the entire ventilation amount is supplied toward the intake port of the gas turbine 21. Here, the total flow rate of air through the two flow paths (1) and (2) is set to be smaller than the amount of engine combustion air of the gas turbine 21. 25, an increase in negative pressure occurs, and this increase in negative pressure increases the flow rate of the air flowing through the first and second flow paths (1) and (2), so that the allowable air amount of the gas turbine is eventually increased. Satisfied.

  That is, in this example, even if the total amount of cooling air (that is, the amount of air from the flow paths (1) and (2)) is used, the amount of combustion air of the gas turbine 21 is set to be insufficient. In reality, however, the gas turbine 21 is selected so that there is a margin in the engine intake capacity, and the margin causes an increase in negative pressure in the enclosure 25, which results in a flow path ( Since the amount of air from 1) and (2) is increased, if the combined amount of air is an allowable amount of air for the gas turbine 21, the engine can be operated without any problem.

  The exhaust gas that has finished its work is discharged from the gas exhaust port 27a of the turbine 27 to the outside through the exhaust duct 33 provided through the downstream partition wall of the enclosure 25.

  In this case, in the conventional case, the required air volume is the sum of the air volume required for ventilation and the air volume required for combustion, whereas in this example, the air volume required for ventilation is burned as it is. The amount of air required for the gas turbine 21 can be reduced, and the shortage is covered by generating an increase in the negative pressure in the enclosure 25 due to the engine intake margin of the gas turbine 21, thereby increasing the amount of air for ventilation. Therefore, as a result, the total amount of intake air can be reduced as compared with the prior art, and the device scale can be reduced accordingly.

  In addition, ventilation air is taken in by a fan driven by an external power source, whereas in the present invention, ventilation air can be taken in by the suction inertia of the compressor 26. Therefore, both the system and structure are simple and reliable. Also improves.

  Furthermore, in the example of the breakdown of the construction cost of the gas turbine device, as shown in FIG. 2, conventionally, the ventilation duct construction cost occupies a high rate of 25% excluding management / expenses. Since the construction can be omitted, the construction cost is also low.

  FIG. 3 is a schematic cross-sectional view showing a second embodiment of the gas turbine apparatus according to the present invention. In this example, the same reference numerals as those in FIG. 1 are assigned to the components that can be considered to be the same in configuration and function as those in the first embodiment, and the description of the first embodiment is used to omit the description.

  An air intake 30 is opened on the upstream side of the enclosure 25, and air introduced from the air intake 30 is separated from the first flow path (1) passing through the lubricating oil cooler 29 by the partition wall 31. The enclosure 25 is branched into a second flow path (2) that passes through the inside and outside of the generator 24 and a third flow path (3) that flows directly in contact with the periphery of the gas turbine 21 without passing through them. Each of them circulates toward the downstream side.

  In order to prevent the air flowing into the enclosure from the third flow path (3) from flowing directly into the compressor 26, a baffle plate 32 is disposed between the intake port 26a and the gas turbine. After flowing in contact with the outer periphery of each part constituting 21, it is preferable to flow into the intake port 26 a.

  The total opening area of each of the flow paths (1) to (3) determines the amount of ventilation air and simultaneously supplies the entire amount of ventilation to the inlet of the gas turbine 21. In addition, since the opening area of the first flow path (1) passing through the lubricating oil cooler 29 and the second flow path (2) passing through the inside and outside of the generator 24 is determined according to each, By adjusting the area of the third flow path (3), the total amount of air necessary for driving the gas turbine 21 can be derived.

That is, in this example, even if the total amount of cooling air (that is, the amount of air from the flow paths (1) and (2)) is used, the amount of combustion air of the gas turbine 21 is insufficient. In order to compensate for the shortage, the flow rate in the third flow path (3) is appropriately adjusted. Furthermore, although the generator 24 requires the same amount of cooling air depending on the manufacturer even if the output is the same, it can be set to adjust and absorb this difference in the amount of air in the third flow path (3). . Therefore, the amount of combustion air (working air amount) of the gas turbine applied to the present invention must be a gas turbine having a capacity equal to or larger than the amount of cooling air.
Of course, as described in the first embodiment, a system in which the third flow path is not closed or provided in the range of the enclosure internal pressure that allows the gas turbine performance is also possible.

  In the conventional case, the required air volume is the sum of the air volume required for ventilation and the air volume required for combustion, whereas in this example, the air volume required for ventilation is required for combustion as it is. The amount of intake air can be reduced as compared with the prior art, and the scale of the apparatus can be reduced accordingly. The same effect as the embodiment can be obtained.

1 is a schematic cross-sectional view showing a first embodiment of a gas turbine apparatus according to the present invention. It is a bar graph which shows the breakdown of the construction cost of the conventional gas turbine apparatus. It is typical sectional drawing which shows 2nd Embodiment of the gas turbine apparatus which concerns on this invention. It is explanatory drawing which shows the flow of the air for ventilation of a conventional turbine apparatus, and the air for combustion.

Explanation of symbols

(1) First flow path (2) Second flow path (3) Third flow path 20 Turbine device 21 Gas turbine 23, 24 Driven machine (23 reducer, 24 generator)
25 Enclosure 26 Compressor 27 Turbine 28 Combustor 29 Lubricating oil cooler 30 Air intake opening 31 Partition wall for partitioning the first, second, and third flow paths (1), (2), (3) 33 Exhaust duct

Claims (4)

A gas turbine that cools the lubricating oil cooler, the gas turbine, and the driven machine by housing the gas turbine having the lubricating oil cooler and the driven machine in an enclosure and circulating cooling air in the enclosure. In the device
Cooling air after cooling the lubricating oil cooler, the gas turbine, and the driven machine is supplied to the gas turbine in the enclosure as engine combustion air through a cooling air flow path configured in the enclosure. A gas turbine device. An air flow path configured in the enclosure includes a first flow path that reaches the gas turbine after passing through the lubricating oil cooler, and a second flow path that reaches the gas turbine after passing through the driven machine The gas turbine apparatus according to claim 1, wherein: The sum of the flow rates of air flowing through the first flow path and the second flow path is set to be smaller than the engine combustion air amount of the gas turbine;
An increase in the negative pressure generated in the enclosure due to the suction of air by the gas turbine increases the flow rate of the air flowing through the first flow path and the second flow path to satisfy the allowable air amount of the gas turbine. The gas turbine apparatus according to claim 2, wherein The air flow path configured in the enclosure further includes a third flow path from the outside of the enclosure to the gas turbine, and the flow rate of air flowing through the air flow path is the amount of engine combustion air of the gas turbine. The gas turbine apparatus according to claim 2, wherein a flow rate in the third flow path is set so as to be substantially the same.

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