JP2006220350A - Gas turbine equipment and its operation method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a multitubular gas turbine combustor having a small structure as a whole and being easily manufactured and assembled, and to provide gas turbine equipment using the same, and its operation method. <P>SOLUTION: In this gas turbine combustor 2 comprising a combustor casing attached to a main casing 6 of the gas turbine equipment, and a plurality of combustor liners 10 stored in the combustor casing 7 and defining a combustion chamber, working fluid extracted through an extracting port 13 formed on the main body casing 6, is injected into the combustor casing 7 through an injection port 14 formed on the combustor casing 7. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention relates to a gas turbine facility and an operation method thereof.

  Conventionally, the working fluid compressed by the compressor is extracted, heated in the regenerator by heat exchange with the exhaust gas of the turbine, and injected into the combustor, thereby reducing the fuel input to the combustor and improving the thermal efficiency. The technology that makes it possible is known.

  For example, in Patent Document 1 below, the bleeder structure to the regenerator is constituted by a combustor tail cylinder outer cylinder and a main body casing, and the injection structure from the regenerator is constituted by a combustor casing, whereby the combustor casing is reduced in size. A gas turbine combustor is described.

  Patent Document 2 below describes that in a multi-can gas turbine combustor, air is extracted from the combustor casing, passed through the regenerator, and injected again into the combustor casing.

Japanese Unexamined Patent Publication No. 2004-190962 (paragraph numbers 0016, 0031, etc.) Japanese Unexamined Patent Publication No. 9-329335 (paragraph 0009, FIG. 2 etc.)

  However, the gas turbine of Patent Document 1 is based on a single-can combustor, and when the gas turbine is enlarged, it tends to be difficult to manufacture a large combustor itself.

  On the other hand, Patent Document 2 describes a multi-can type combustor. However, since a plurality of pipes for injecting from the regenerator to the combustor are provided for each combustor casing, air to each combustor is provided. In addition to the possibility of deviations in the distribution, the structure around the combustor casing is complicated, and there is a concern about an increase in manufacturing and assembly costs.

  An object of the present invention is to provide a multi-can gas turbine combustor having a small overall structure and easy to manufacture and assemble, a gas turbine facility using the same, and an operating method thereof.

  In order to achieve the above object, the present invention provides a gas turbine combustor comprising a combustor casing attached to a main casing of a gas turbine facility, and a plurality of combustor liners housed in the combustor casing to form a combustion chamber. The working fluid extracted through an extraction port provided in the main body casing is injected into the combustor casing through an injection port provided in the combustion chamber casing.

  According to the present invention, it is possible to provide a multi-can gas turbine combustor having a small overall structure and easy to manufacture and assemble, a gas turbine facility using the same, and an operating method thereof.

  Embodiments of the present invention will be described below with reference to the drawings.

  FIG. 1 is a cross-sectional view of a gas turbine facility showing a first embodiment of the present invention, and FIG. 2 is a cross-sectional view of the combustor portion of FIG. 1 as viewed from the axial direction. The gas turbine equipment of this embodiment is a regenerative gas turbine for power generation that includes a compressor 1, a combustor 2, a turbine 3, and a regenerator 4, and that generates electric power by rotating a generator 5 by the output of the turbine 3. .

  Here, the combustor 2 of the present embodiment stores a plurality of substantially cylindrical combustor liners 10 that form combustion chambers by separating unburned air and burned combustion gas 105, and the combustor liners 10. The combustor casing 7, the fuel nozzle 9 at the upstream center of each combustor liner 10, the combustor cover 8 through which the fuel nozzle 9 passes, and the downstream of each combustor liner 10, the fuel gas is sent to the turbine 3. It is a multi-can type combustor having a combustor tail cylinder 12 leading to

  Further, on the outer periphery of each combustor liner 10, an air flow path is formed and a flow guide 11 for controlling the air flow is provided. The flow guide 11 has a diameter larger than that of the combustor liner 10 and is positioned in a substantially concentric cylindrical shape with respect to the combustor liner 10. The combustor casing 7 has an opening on the downstream side of the combustor liner 10. Installed on.

  Further, as shown in FIG. 2, the shape of the combustor casing 7 is a substantially double cylindrical shape, and a plurality of combustor liners 10 are formed in a substantially circumferential shape in a substantially annular space sandwiched between the two cylinders. Has been placed. Here, the substantially double cylindrical shape includes shapes having different diameters in the axial direction. Furthermore, the combustor casing 7 is provided with one injection port 14, whereby hot air 103 is injected from the regenerator 4 into the combustor casing 7.

On the other hand, the main casing 6 to which the combustor casing 7 is attached is provided with one extraction port 13, whereby the high-pressure air 101 is extracted from the main casing 6 to the regenerator 4. In the present embodiment, the main body casing 6 stores not only the combustor tail cylinder 12 but also the compressor 1 and the turbine 3, but the compressor casing for storing the compressor 1 and the turbine for storing the turbine 3 are also stored. The casing may be separated.

  Next, the flow of air as a working medium in the gas turbine equipment configured as described above will be described. First, the atmosphere 100 is compressed by the compressor 1 to become high-pressure air 101, and after the high-pressure air 101 is filled in the main body casing 6, the air is extracted outside the main body casing 6 through the extraction port 13 of the main body casing 6. . Here, when the high-pressure air 101 flows through the plurality of combustor transitions 12, the combustor transition 12 is convectively cooled from the outer wall surface. Further, the air 102 extracted outside the main body casing 6 is heated by heat exchange with the turbine exhaust gas 106 in the regenerator 4 to become high-temperature air 103, and is combusted by the combustor casing via the injection port 14 of the combustor casing 7. 7 is injected.

The injected high-temperature air 103 diffuses in the circumferential direction, radial direction, and axial direction of the combustor casing 7 and fills the combustor casing 7. Thereafter, the gas flows from the opening of the flow guide 11 through the substantially annular space between the flow guide 11 and the combustor liner 10 and flows from the downstream side to the upstream side in the axial direction of the combustor liner 10 (see FIG. 1). 104), which is also used for convective cooling of the combustor liner 10. A part of the high-temperature air 103 flows into the combustor liner 10 from the cooling holes provided in the combustor liner 10 and is used for film cooling. The remaining high-temperature air 103 flows as combustion air into the combustor liner 10 from combustion holes provided in the combustor liner 10 or air holes provided in the fuel nozzle 9, and is ejected from the fuel nozzle 9. It is used for combustion as the combustion gas 105 together with the fuel 200. This combustion gas 105 is sent to the turbine 3 through the combustor tail cylinder 12, and after the low-pressure turbine exhaust gas 106 exiting the turbine 3 is recovered by the regenerator 4, it is exhausted (107 in FIG. 1). .

  Furthermore, the structure of the partition member 15 installed in the part to which the combustor liner 10 and the combustor tail cylinder 12 are connected is demonstrated using FIG. The partition member 15 functions to separate the space inside the main body casing 6 and the combustor casing 7, and mainly includes a flange portion 15a, a partition portion 15b, and a seal cylindrical portion 15c. Here, the flange portion 15 a is for fixing the partition wall member 15 to the main body casing 6, and a bolt is passed through a hole provided in the flange portion 15 a and fixed to a bolt hole provided in the main body casing 6. . Further, the partition wall portion 15b is for separating the space in the main body casing 6 and the combustor casing 7, so that most of the air filled in the main body casing 6 is sent to the regenerator 4, Heat recovery can be performed efficiently. The seal cylinder portion 15c is positioned in a substantially concentric cylinder shape with respect to the combustor tail cylinder 12, and a leaf spring seal 16 is attached in the cylinder circumferential direction. Here, an interval between the seal cylindrical portion 15c and the combustor tail cylinder 12 is set such that the sealability by the leaf spring seal 16 can maintain a predetermined condition in consideration of the difference in thermal expansion between the start of the gas turbine and the steady operation. Is set. Even if the combustor tail cylinder 12 is thermally extended to the upstream side of the combustor 2 during normal operation, the seal cylinder portion 15c is substantially concentric with the combustor tail cylinder 12, so that the combustor tail cylinder 12 It is possible to seal without restricting the thermal elongation of.

  Moreover, since the partition member 15 has a structure that can be inserted and removed from the outside of the main casing 6, the combustor 2 can be easily disassembled and assembled. The assembly method of the combustor 2 will be specifically described. First, the combustor tail cylinder 12 is attached to the main body casing 6, and then the partition wall member 15 is fixed to the main body casing 6 with respect to each combustor tail cylinder 12. To do. Next, after attaching the combustor casing 7 to the main body casing 6 and inserting and attaching the flow guide 11 to the combustor casing 7, the combustor liner 10 is disposed in the combustor casing 7 from the upstream side of the combustor 2. Finally, the combustor cover 8 and the combustion nozzle 9 are installed. In addition, what is necessary is just to perform the decomposition | disassembly method of the combustor 2 in the reverse procedure to the above.

  According to the configuration of this embodiment described above, the following effects are achieved. First, an extraction port 13 for extracting air to the regenerator 4 and an injection port 14 for injecting from the regenerator 4 are separately provided in the main body casing 6 and the combustor casing 7, respectively. There is no need to provide the bleed port 13, and the combustor casing 7 can be downsized.

  In addition, the internal space of the substantially double cylindrical combustor casing 7 is a common space for each combustor liner 10, and air is distributed substantially uniformly to each combustor liner 10 in this space. Therefore, the flow rate of the air flowing into each combustor liner 10 can be made substantially uniform. At that time, the flow guide 11 is provided on the outer periphery of the combustor liner 10, and the flow in the combustor casing 7 is separated from mainly the circumferential flow and mainly the axial flow. It can be further enhanced. In addition, if the flow velocity in at least a part between the combustor liner 10 and the flow guide 11 is set to be faster than the flow velocity in the combustor casing 7, the function of equalizing the flow rate is further enhanced. Thus, when it becomes difficult for deviation to occur in the distribution of air, partial increase in temperature and increase in nitrogen oxides (NOx) can be suppressed.

  Further, since the opening of the flow guide 11 is provided on the downstream side of the combustor liner 10, the air used for combustion on the upstream side of the combustor 2 can be used for convective cooling of the combustor liner 10. As a result, the air consumed for film cooling of the combustor liner 10 is reduced, the flame temperature on the upstream side of the combustor 2 is lowered correspondingly, and the NOx generation amount can be suppressed and the liner metal temperature can be reduced.

  In addition, since the combustor 2 of this embodiment can be sequentially decomposed from the upstream side, it is easy to inspect, repair, and replace combustor parts that are likely to have a reduced life due to high temperatures of the combustion air. be able to. Further, even when a regeneration cycle is applied to a multi-can gas turbine, each combustion is performed through one injection port 14 without providing complicated piping for distributing air to each combustor liner 10. Since air can be supplied to the combustor liner 10, the combustor 2 is small in overall structure and easy to manufacture. If the injection port 14 is provided for each of the plurality of combustor liners 10, there is a deviation in the distribution of air flowing into each combustor liner 10 depending on the length of the piping, the number of branches, and the number of bends. There is a possibility that the temperature of the combustor 2 may be partially increased and the amount of NOx generated may be increased.

  Furthermore, since the combustor 2 of the present embodiment is a multi-can type, the individual combustor liners 10 can be downsized even if the gas turbine is enlarged as compared with the single can type. Therefore, the buckling strength of the combustor liner 10 can be maintained high and development costs can be suppressed.

  In the present embodiment, the number of injection ports 14 is one, but a number smaller than the number of combustor liners 10, for example, two or four injection ports 14 may be provided in the combustor casing 7.

  FIG. 4 is a sectional view of the vicinity of the combustor tail cylinder 12 of the gas turbine equipment showing the second embodiment of the present invention. Since the gas turbine equipment in the present embodiment is basically the same configuration as the first embodiment, the difference from the first embodiment, that is, the point that the cooling function of the combustor tail cylinder 12 is enhanced will be described. To do.

  In this embodiment, a tail cylinder outer cylinder 17 is arranged on the outer peripheral side of the combustor tail cylinder 12, and is fixed to the main body casing 6 by a flange portion 18 provided on the tail cylinder outer cylinder 17. Further, since the air flow from the downstream side to the upstream side of the combustor tail cylinder 12 is blocked by the flange portion 18 among the air flows on the outer peripheral side of the tail cylinder outer cylinder 17, the compressor 1 transfers to the extraction port 13. It is possible to prevent the high-pressure air 101 from flowing in directly. Therefore, the space between the combustor tail cylinder 12 and the tail cylinder outer cylinder 17 serves as a flow path for the high-pressure air 101a, and the high-pressure air 101a flows from the downstream side of the combustor tail cylinder 12 as shown in FIG. Will flow out upstream. Further, the outflowed air flows through between the adjacent combustor tail cylinders 12 and collects at the extraction port 13. At this time, the combustor tail cylinder 12 is convectively cooled by the high-pressure air 101a flowing on the outer periphery thereof, but the high-pressure air 101a in the flow path on the outer periphery of the combustor tail cylinder 12 flows in one direction over almost the entire surface. Effective cooling is possible without stagnation of the flow.

  In this embodiment, the opening on the inflow side and the outflow side of the cooling flow path is such that the length of the tail cylinder outer cylinder 17 is shorter than the length of the combustor tail cylinder 12, and both ends of the tail cylinder outer cylinder 17 are arranged. However, the opening may be formed by providing a hole having a predetermined shape in the tail cylinder outer cylinder 17 without forming the gap in this way.

  In the present embodiment, as shown in FIG. 5, a plurality of bypass holes 19 are provided in the flange portion 18 of the tail cylinder outer cylinder 17. For this reason, a part of the high-pressure air 101 filled in the main body casing 6 flows into the extraction port 13 through the bypass hole 19. Since the bypass flow 101b passing through the bypass hole 19 does not contribute to the cooling of the combustor tail cylinder 12, compared to the case where all of the high-pressure air 101 discharged from the compressor 1 is used for cooling the combustor tail cylinder 12, Since the combustor tail cylinder 12 is not excessively cooled and the thermal energy of the combustion gas 105 is prevented from being lowered, the gas turbine equipment can be operated efficiently.

  Moreover, compared to the case where all the air flows through the space between the combustor tail cylinder 12 and the tail cylinder outer cylinder 17, the flow velocity does not become excessively fast, so the pressure loss is reduced and the thermal efficiency is improved. . Further, since it is not necessary to enlarge the outer cylinder 17 or to provide a branching / merging pipe outside the main body casing 6 in order to reduce the flow velocity, the size is reduced, the number of parts is reduced, the structure is simplified, and the disassembly is performed. Easy assembly and cost reduction can be expected.

  FIG. 6 is a sectional view of the gas turbine equipment showing the third embodiment of the present invention. The present embodiment basically has the same configuration as that of the first embodiment, but is different in that a humidification / regeneration gas turbine is employed. This will be specifically described below.

  In the present embodiment, first, high-pressure water is mixed with the extraction air 102 extracted from the extraction port 13 of the main body casing 6 by the humidifier 20 to obtain high-humidity air. Next, after water droplets in the air are completely evaporated by the low temperature regenerator 21, heat is exchanged with the turbine exhaust gas 106 in the regenerator 4 to form high temperature and high humidity air, which is injected into the combustor casing 7 from the injection port 14. To do. At this time, since the combustion air contains moisture of a normal concentration or more, the flame temperature on the upstream side of the combustor 2 is lowered, and generation of NOx can be suppressed. That is, even if the working fluid used for combustion is a high-temperature regenerative gas turbine, the amount of NOx emissions can be kept low. Further, in the humidification / regeneration type cycle, since the amount of air injected into the combustor 2 is increased by the amount of moisture contained in the air, the structure of the combustor 2 tends to be larger than the regeneration cycle. However, if the configuration as in the first embodiment is employed, the structure of the combustor 2 can be kept small.

  The multi-can regenerative gas turbines of the first to third embodiments can be used for power generation, compressor drive, pump drive, etc., and can be combined with an exhaust heat recovery boiler to generate power and generate steam. It can also be used for generation. The fuel 200 used in the gas turbine facility is a fuel that can be used in the gas turbine facility, such as a gas fuel such as natural gas or coal gasification gas, or a liquid fuel such as kerosene, via, heavy oil, or alcohol. Any type. Further, in the first to third embodiments, air is used as the working fluid of the gas turbine equipment, but nitrogen, water vapor, carbon dioxide, or a mixture thereof may be used.

It is sectional drawing of the gas turbine installation which shows the 1st Example of this invention. It is the figure which looked at the cross section of the combustor part of FIG. 1 from the axial direction. It is a figure which shows the structure of the partition member installed in the connection part of the combustor liner and combustor tail cylinder of FIG. It is sectional drawing of the combustor tail cylinder vicinity of the gas turbine equipment which shows the 2nd Example of this invention. It is the figure which expanded the flange part of the tail cylinder outer cylinder of FIG. It is sectional drawing of the gas turbine installation which shows the 3rd Example of this invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 ... Compressor, 2 ... Combustor, 3 ... Turbine, 4 ... Regenerator, 5 ... Generator, 6 ... Main body casing, 7 ... Combustor casing, 8 ... Combustor cover, 9 ... Fuel nozzle, 10 ... Combustor Liner,
DESCRIPTION OF SYMBOLS 11 ... Flow guide, 12 ... Combustor tail tube, 13 ... Extraction port, 14 ... Injection port, 15 ... Partition member, 16 ... Leaf spring seal, 17 ... Outer tube outer cylinder, 18 ... Flange part, 19 ... Bypass hole, 20 DESCRIPTION OF SYMBOLS ... Humidifier, 21 ... Low temperature regenerator, 22 ... Water pump, 100 ... Atmosphere, 101 ... High pressure air, 102 ... Extracted air, 103 ... High temperature air, 104 ... Liner cooling air, 105 ... Combustion gas, 106 ... Turbine exhaust 107 ... exhaust gas, 200 ... fuel, 301 ... low pressure water, 302 ... high pressure water.

Claims (10)

  A gas turbine combustor comprising a combustor casing attached to a main casing of a gas turbine equipment and a plurality of combustor liners that are housed in the combustor casing to form a combustion chamber, wherein an extraction port provided in the main casing is provided with The gas turbine combustor is characterized in that the working fluid bleed through is injected into the combustor casing via an injection port provided in the combustion chamber casing.   In a gas turbine combustor comprising a combustor casing attached to a main casing of a gas turbine facility and a plurality of combustor liners stored in the combustor casing to form a combustion chamber, the working fluid compressed by a compressor is The air is extracted out of the main body casing through the extraction port of the main body casing, the working fluid exchanges heat with the exhaust gas of the turbine, and the working fluid is injected into the combustor casing from the injection port of the combustor casing. The working fluid diffuses in the combustor casing, and the working fluid flows between the combustor liners and the flow guides provided on the outer periphery thereof from the downstream side to the upstream side in the axial direction of the combustor liners. A gas turbine combustor wherein at least a portion of the working fluid is supplied into each combustor liner for combustion.   In a gas turbine combustor comprising a combustor casing attached to a main casing of a gas turbine equipment and a plurality of combustor liners that are stored in the combustion casing to form a combustion chamber, the shape of the combustor casing is substantially double. A plurality of combustor liners are arranged in a substantially circular space sandwiched between the two cylinders in a substantially circular shape, and the combustion gas generated in each combustor liner and each combustor liner is used as a turbine. A partition member that separates the space in the combustor casing from the space in the main body casing is provided at a portion to which the combustor tail pipe leading to the air is connected, and the air compressed by the compressor passes through the extraction port of the main body casing. Introduced into the regenerator, where the air exchanges heat with the exhaust gas of the turbine, and the air enters the combustor casing via the injection port of the combustor casing. In the combustor casing, the air diffuses in the circumferential direction, the radial direction and the axial direction, and the shaft of each combustor liner is provided between each combustor liner and the flow guide provided on the outer periphery thereof. The gas turbine combustor, wherein the air flows in a direction from a downstream side to an upstream side, and at least a part of the air is supplied as combustion air into each combustor liner.   4. The gas turbine combustor according to claim 3, wherein air is distributed substantially uniformly to each combustor liner in the space in the combustor casing.   4. The gas turbine combustor according to claim 3, wherein substantially uniform air flow flows into each combustor liner.   6. The gas turbine combustor according to claim 3, wherein air extracted from the extraction port is humidified.   6. The tail cylinder outer cylinder is disposed on the outer peripheral side of the combustor tail cylinder according to claim 3, and the downstream side of the combustor tail cylinder among the air flows on the outer peripheral side of the tail cylinder outer cylinder. A gas turbine combustor characterized in that the flow toward the upstream side is blocked.   In any one of Claims 3 thru | or 5, a transition piece outer cylinder is arrange | positioned at the outer peripheral side of the said combustor tail cylinder, and the flange part which attaches this tail cylinder outer cylinder to the said main body casing is on the outer peripheral side of the said tail cylinder outer cylinder. A gas turbine combustor provided, wherein the flange portion has a bypass hole.   A compressor that compresses the working fluid; a regenerator that exchanges heat between the working fluid compressed by the compressor and the turbine exhaust gas; a combustor that burns the working fluid and fuel that has passed through the regenerator; and the combustor In the gas turbine equipment comprising a turbine driven by the combustion gas generated in the above, the combustor is mounted on a main casing of the gas turbine equipment, and is stored in the combustor casing to form a combustion chamber. A plurality of combustor liners, and a plurality of combustor tail cylinders that are stored in the main body casing and guide combustion gas generated in each combustor liner to the turbine, and the working fluid compressed by the compressor A port for extracting air from inside the main body casing is provided in the main body casing, and a port for injecting the working fluid heat-exchanged by the regenerator into the combustor casing. Gas turbine installation, characterized in that There are provided in the combustor casing. The compressor compresses the working fluid and heats it by exchanging heat between the compressed working fluid and the turbine exhaust gas. The heated working fluid and fuel are combusted to generate combustion gas, and the combustion gas drives the turbine. In the operating method of the gas turbine equipment, the working fluid compressed by the compressor is extracted out of the main casing through the extraction port of the main casing, and the working fluid heated by the heat exchange is injected into the combustor casing. It is injected into the combustion casing through a port, the working fluid is diffused in the combustor casing, and at least a part of the working fluid is supplied to a plurality of combustor liners arranged substantially circumferentially. A method for operating a gas turbine facility.

Images