US20130192245A1

US20130192245A1 - Gas Turbine Combustor and Operating Method Thereof

Info

Publication number: US20130192245A1
Application number: US13/743,927
Authority: US
Inventors: Keisuke Miura; Tomomi Koganezawa; Kazuki Abe; Takeo Saito
Original assignee: Hitachi Ltd
Current assignee: Mitsubishi Power Ltd
Priority date: 2012-01-27
Filing date: 2013-01-17
Publication date: 2013-08-01
Also published as: EP2620708A2; JP5458121B2; CN103225822B; EP2620708B1; JP2013155626A; CN103225822A; EP2620708A3

Abstract

A gas turbine combustor has a chamber supplied with fuel and air and a multi-burner having a plurality of burners provided with an air hole plate having a plurality of air holes, and fuel nozzles for supplying fuel to the air holes in the air hole plate; the multi-burner is made up of a center burner disposed in the center and a plurality of outer burners around the center burner, the outer burners are divided into inner fuel nozzles and outer fuel nozzles to separately supply fuel through fuel systems, and the fuel is supplied to the fuel nozzles in the center burner or to the fuel nozzles in the center burner and the inner fuel nozzles in the outer burners disposed around the center burner in a partial load condition in which the load is lower than that of when all the fuel systems are used to supply fuel.

Description

CLAIM OF PRIORITY

The present application claims priority from Japanese patent application serial No.2012-014960, filed on Jan. 27, 2012, the content of which is hereby incorporated by reference into this application.

BACKGROUND OF THE INVENTION

1. Technical Field
The present invention relates to a gas turbine combustor and an operating method of the gas turbine combustor.
2. Background Art
There is a need for gas turbines to be lower in NOx from the perspective of environmental protection.
One way to lower the NOx of a gas turbine combustor is a premixed combustor; in this case, there is a concern of a backfire phenomenon in which a flame enters a premixing device.
Japanese Patent Laid-open No. 2003-148734 shows a gas turbine combustor that has fuel nozzles for supplying fuel to a chamber and air holes for supplying air located in the downstream side of the fuel nozzles in which the ejection hole of the fuel nozzle and the air hole are disposed coaxially to make up a fuel combustion nozzle. The document discloses a technology concerning a gas turbine combustor for achieving an anti-backfiring characteristic and low NOx combustion.
In addition, Japanese Patent Laid-open No. 2011-075172 discloses a means for preventing flame attachment to an air hole exit by defining the exit location and the exit direction of the air hole. In this technology of gas turbine combustors, a distance for mixing fuel and air is increased based on the technology disclosed in Japanese Patent Laid-open No. 2003-148734 to further reduce NOx discharge.
{Patent Literature 1} Japanese Patent Laid-open No. 2003-148734
{Patent Literature 2} Japanese Patent Laid-open No. 2011-075172

SUMMARY OF THE INVENTION

A gas turbine needs to be operated stably in a wide range of operating conditions from ignition to full load operation. For this reason, a multi-burner with a plurality of burners has been widely adopted as a gas turbine combustor.
While the above Japanese Patent Laid-open No. 2003-148734 and Japanese Patent Laid-open No. 2011-075172 each disclose a multi-burner configuration, none of these known prior arts mention a technology for reducing the discharge of unburned combustibles and preventing an increase in liner metal temperature at the same time in partial load conditions of the gas turbine.
An object of the present invention is to provide a gas turbine combustor and an operating method of the gas turbine combustor to allow the gas turbine combustor equipped with a multi-burner to ensure combustion stability in the entire range of load conditions of the gas turbine and reduce the generation of unburned combustibles and an increase in liner metal temperature at the same time in partial load conditions of the gas turbine.
A gas turbine combustor of the present invention comprising: a chamber for mixing and burning supplied fuel and supplied air to generate combustion gas; an air hole plate located in an upstream side of the chamber, forming a plurality of air holes for supplying the air; a plurality of fuel nozzles for supplying the fuel to the plurality of air holes formed in the air hole plate, wherein the air holes are disposed in the downstream side of the fuel nozzles that one of the fuel nozzles is paired with one of the air holes; and a plurality of burners made up of the plurality of air holes and the plurality of fuel nozzles in pairs, characterized in that, the plurality of burners are comprised a center burner disposed on an axis of the gas turbine combustor and a plurality of outer burners installed around the center burner, the center burner is fixed to a first fuel supply system for supplying the fuel to the fuel nozzles in the center burner, the plurality of outer burners is fixed to a second fuel supply system for supplying the fuel to the fuel nozzles in outer burner's inner portions which are inner regions of specific outer burners among the outer burners, the plurality of outer burners is fixed to a third fuel supply system for supplying the fuel to the fuel nozzles in outer burner's inner portions which are inner regions of outer burners other than the specific outer burners, the plurality of outer burners is fixed to a fourth fuel supply system for supplying the fuel to the fuel nozzles in outer burner's outer portions which are outer regions of the outer burners, wherein when a gas turbine is operated in a low load or partial load condition, the fuel is supplied to the fuel nozzles in the center burner or to the fuel nozzles in the center burner and in the outer burner's inner portions which are the inner regions of the specific outer burners among the plurality of outer burners through the first to the fourth fuel supply systems selected based on the operation condition of the gas turbine.
An operating method of a gas turbine combustor of the present invention having a chamber for mixing and burning supplied fuel and supplied air to generate combustion gas; an air hole plate located in an upstream side of the chamber, forming a plurality of air holes for supplying the air; a plurality of fuel nozzles for supplying the fuel to the plurality of air holes formed in the air hole plate, wherein the air holes are disposed in a downstream side of the fuel nozzles that one of the fuel nozzles is paired with one of the air holes; and a plurality of burners made up of the plurality of air holes and the plurality of fuel nozzles in pairs, wherein the plurality of burners are comprised a center burner disposed on an axis of the gas turbine combustor and a plurality of outer burners installed around the center burner, the center burner is fixed to a first fuel supply system for supplying the fuel to the fuel nozzles in the center burner, the plurality of outer burners is fixed to a second fuel supply system for supplying the fuel to the fuel nozzles in outer burner's inner portions which are inner regions of specific outer burners among the outer burners, the plurality of outer burners is fixed to a third fuel supply system for supplying the fuel to the fuel nozzles in outer burner's inner portions which are inner regions of the outer burners other than the specific outer burners, and the plurality of outer burners is fixed to a fourth fuel supply system for supplying the fuel to the fuel nozzles in outer burner's outer portions which are outer regions of the outer burners, the operating method of a gas turbine combustor comprising the steps of: supplying the fuel through the first fuel supply system to the fuel nozzles disposed in the center burner to burn the chamber when a gas turbine is operated in a low load condition; supplying the fuel additionally through the second fuel supply system to the fuel nozzles disposed in the outer burner's inner portions which are the inner regions of the specific outer burners among the plurality of outer burners to burn the chamber when the gas turbine is operated in a partial load condition with load increased more than that of the low load gas turbine; supplying the fuel additionally through the third fuel supply system to the fuel nozzles disposed in the outer burner's inner portions which are the inner regions of all other outer burners among the plurality of outer burners except for the specific outer burners to burn the chamber when the gas turbine is operated in a partial load condition with load increased more than that of said partial load gas turbine; and supplying the fuel additionally through the fourth fuel supply system to the fuel nozzles disposed in the outer burner's outer portions which are the outer regions of all the outer burners to burn the chamber when the gas turbine is operated in a full load condition with load further increased.
According to the present invention, a gas turbine combustor and an operating method of the gas turbine combustor can be achieved to allow the gas turbine combustor equipped with a multi-burner to ensure combustion stability in the entire range of load conditions of the gas turbine and reduce the generation of unburned combustibles and an increase in liner metal temperature at the same time in partial load conditions of the gas turbine.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a system diagram of a plant showing a schematic structure of a gas turbine plant to which a gas turbine combustor according to the first embodiment of the present invention is applied.

FIG. 2 is a partial cross-sectional view showing a detailed configuration of a fuel supply portion made up of fuel nozzle headers, fuel nozzles and an air hole plate in the gas turbine combustor according to the first embodiment of the present invention.

FIG. 3 is a front view of the air hole plate, viewed from the chamber side, in the gas turbine combustor according to the first embodiment shown in FIG. 2.

FIG. 4 is an illustration of operation modes showing an example of a fuel staging method for the gas turbine combustor according to the first embodiment shown in FIG. 2.

FIG. 5 illustrates an example of a method of supplying fuel at ignition for the gas turbine combustor according to the first embodiment shown in FIG. 1.

FIG. 6 is a front view of a variation of the air hole plate, viewed from the chamber side, in the gas turbine combustor according to the first embodiment shown in FIG. 1.

FIG. 7 is a front view of an air hole plate, viewed from the chamber side, in a gas turbine combustor according to the second embodiment of the present invention.

FIG. 8 is an illustration of operation modes showing an example of a fuel staging method for the gas turbine combustor according to the second embodiment shown in FIG. 7.

FIG. 9 is a front view of an air hole plate, viewed from the chamber side, in a gas turbine combustor according to the third embodiment of the present invention.

FIG. 10 is an illustration of operation modes showing an example of a fuel staging method for the gas turbine combustor according to the third embodiment shown in FIG. 9.

FIG. 11 is a front view of an air hole plate, viewed from the chamber side, in a gas turbine combustor according to the fourth embodiment of the present invention.

FIG. 12 is an illustration of operation modes showing an example of a fuel staging method for the gas turbine combustor according to the fourth embodiment shown in FIG. 11.

DETAILED DESCRIPTION OF THE EMBODIMENTS

Gas turbine combustors and operating methods of the gas turbine combustors according to the embodiments of the present invention will be described below with reference to accompanying drawings.

Embodiment 1

A gas turbine combustor and an operating method of the gas turbine combustor according to the first embodiment of the present invention will be described with reference to FIGS. 1 to 3.
FIG. 1 is a system diagram showing the entire structure of a gas turbine plant for power generation.
In a gas turbine plant 9 shown in FIG. 1, a gas turbine for power generation is made up of a compressor 1 for pressurizing sucked air 15 to generate high-pressure air 16, a gas turbine combustor 2 for mixing and burning gas fuel 50 and the high-pressure air 16 generated by the compressor 1 to generate high-temperature combustion gas 18, a turbine 3 driven by the high-temperature combustion gas 18 generated in the gas turbine combustor 2, a generator 8 for power generation rotated by the action of the turbine 3, and a shaft 7 for joining the compressor 1, the turbine 3 and the generator 8 together.
The gas turbine combustor 2 is housed in a casing 4. The head portion of the gas turbine combustor 2 is provided with a multi-burner 6 made up of a plurality of fuel nozzles 25, and the inside of the gas turbine combustor 2 in the downstream side of the multi-burner 6 is provided with an approximately cylindrical combustor liner 10 for separating the high-pressure air and fuel gas.
A chamber 5 is formed in the combustor liner 10 to mix and burn the high-pressure air 16 and the gas fuel 50 to generate the high-temperature combustion gas 18.
An approximately cylindrical flow sleeve 11 is disposed around the outer periphery of the combustor liner 10, and the sleeve becomes an external wall forming an air passage for passing the high-pressure air. The diameter of the flow sleeve 11 is larger than that of the combustor liner 10, and the flow sleeve 11 is disposed concentrically with the combustor liner 10.
The downstream side of the combustor liner 10 is a transition piece 12 for introducing the high-temperature combustion gas 18 generated in the chamber 5 of the gas turbine combustor 2 into the turbine 3.
A flow sleeve 13 for surrounding the transition piece 12 is disposed around the outer periphery of the transition piece 12 in the downstream side of the flow sleeve 11.
The sucked air 15 is pressurized by the compressor 1 and then becomes the high-pressure air 16. After the high-pressure air 16 fills the casing 4, it flows into a space between the transition piece 12 and the flow sleeve 13 for surrounding the transition piece 12 to cool the transition piece 12 from the external surface in the form of convection cooling.
Then, the high-pressure air 16 passes through an annular passage formed between the flow sleeve 11 and the combustor liner 10 to flow toward the head portion of the gas turbine combustor 2. The high-pressure air 16 is used for convection cooling of the combustor liner 10 as it flows.
In addition, part of the high-pressure air 16 flows into the combustor liner 10 from numerous cooling holes provided to the combustor liner 10 to be used for film cooling of the combustor liner 10.
Out of the high-pressure air 16, the remaining combustion air 17 which was not used for the film cooling of the combustor liner 10 flows into the chamber 5 from numerous air holes 32 provided in an air hole plate 31 located at the upstream side of the chamber 5 of the gas turbine combustor 2.
The combustion air 17 flowed into the combustor liner 10 from the numerous air holes 32 is burned in the chamber 5 formed in the combustor liner 10 along with fuel ejected from a plurality of fuel nozzles 25 of the multi-burner 6 to generate the high-temperature combustion gas 18.
The high-temperature combustion gas 18 generated by the burning in the chamber 5 in the combustor liner 10 is supplied to the turbine 3 through the transition piece 12 to drive the turbine 3.
After driving the turbine 3, the high-temperature combustion gas 18 is discharged from the turbine 3 as exhaust gas 19.
The drive force obtained by the turbine 3 is transferred to the compressor 1 and the generator 8 through the shaft V. Part of the drive force obtained by the turbine 3 drives the compressor 1 to pressurize air to generate high-pressure air. The other part of the drive force obtained by the turbine 3 rotates the generator 8 to generate power.
The multi-burner 6 made up of the plurality of fuel nozzles 25 in the gas turbine combustor 2 is, as shown in FIG. 1, fixed with four fuel systems for supplying the fuel 50, which are a first fuel system 51 to a fourth fuel system 54.
The first fuel system 51 to the fourth fuel system 54 are provided with fuel rate adjusting valves 61 to 64 respectively, and the flow rates of the fuel 50 supplied through the first fuel system 51 to the fourth fuel system 54 are adjusted by changing the opening rate of the respective fuel rate adjusting valves 61 to 64 based on a control signal from a control device 100 to control the output of the gas turbine plant 9.
Additionally, the upstream side of the branching point where the system is branched into four systems of the first fuel system 51 to the fourth fuel system 54 is provided with a fuel cutoff valve 60 for cutting off the supply of the fuel 50.
FIG. 2 is a cross-sectional view showing the detailed configuration of the disk-shaped air hole plate 31, a multi-burner 6 having the plurality of fuel nozzles 25, and fuel nozzle headers 23 constituting a fuel supply portion of the gas turbine combustor 2 according to the present embodiment, and FIG. 3 is the front view of the gas turbine combustor 2 in which the air hole plate 31 is viewed from the chamber 5. The detail of the multi-burner 6 of the gas turbine combustor 2 will be described below with reference to FIGS. 2 and 3.
As shown in FIGS. 2 and 3, in the gas turbine combustor 2 of the present embodiment, the multi-burner 6 provided with the plurality of fuel nozzles 25 is made up of a center burner 33 disposed corresponding to the center of the disk-shaped air hole plate 31 and six outer burners 37 disposed away from each other around the center burner 33 between the center and the outer periphery of the air hole plate 31.
The center burner 33 and the outer burners 37 are each installed with the numerous fuel nozzles 25 constituting these center burner 33 and outer burners 37 and the fuel nozzle headers 23 for distributing fuel to the fuel nozzles 25 in the upstream side of the fuel nozzles 25.
Then, the numerous air holes 32 which pass air and the fuel ejected from the fuel nozzles 25 for ejecting them to the chamber 5 of the gas turbine combustor 2 are provided to the air hole plate 31 which is installed in the downstream side of the fuel nozzles 25 and the upstream side of the chamber 5.
Furthermore, as shown in the front view of the gas turbine combustor 2 in FIG. 3, the numerous air holes 32 formed in the air hole plate 31 correspond one-to-one with the numerous fuel nozzles 25 provided to each of the center burner 33 and the six outer burners 37 around the center burner 33; the air hole plate 31 is installed so as to partition the chamber 5.
In other words, the numerous air holes 32 formed in the air hole plate 31 are made up of a plurality of air holes 32 in the first row in the center, a plurality of air holes 32 in the second row around the first row, and a plurality of air holes 32 in the third row around the second row in the center region of the air hole plate 31 corresponding to the center burner 33; the three rows of air holes 32 are arranged concentrically in the center region of the air hole plate 31.
In the same manner, six areas in the peripheral region of the air hole plate 31 corresponding to the six outer burners 37 each have a plurality of air holes 32 in the first row in the center, a plurality of air holes 32 in the second row around the first row, and a plurality of air holes 32 in the third row around the second row; the three rows of air holes 32 are formed concentrically in each area in the peripheral region of the air hole plate 31.
Furthermore, the numerous air holes 32 formed in each area in the peripheral region of the air hole plate 31 corresponding to the numerous fuel nozzles 25 installed in each of the center burner 33 and the outer burners 37 are formed diagonally with respect to the axis of the chamber 5 so that each air hole has an angle of traverse to the chamber 5 of the gas turbine combustor 2.
The numerous air holes 32 formed in the air holes plate 31 cause swirl flows 40 to be formed, which are mixed flows of fuel and air formed in the chamber 5 of the gas turbine combustor 2 in the downstream side of the center burner 33 and the outer burners 37, and the swirl flows 40 generate recirculation flows 41 which hold flames 42 formed by burning the fuel in the chamber 5 of the gas turbine combustor 2.
The six outer burners 37 installed to the gas turbine combustor 2 in the present embodiment each have numerous inner fuel nozzles 25 a and numerous outer fuel nozzles 25 b, and the second fuel system 52 to the fourth fuel system 54 are separately installed to supply fuel to the inner fuel nozzles 25 a and the outer fuel nozzles 25 b.
The center burner 33 disposed in the center region of the air hole plate 31 in the gas turbine combustor 2 of the present embodiment has the numerous fuel nozzles 25, to which fuel is supplied by the first fuel system 51 connected to the center burner 33.
The six outer burners 37 installed in the peripheral region of the air hole plate 31 each have the inner fuel nozzles 25 a, as shown in FIG. 2, corresponding to the plurality of air holes 32 in the first row in the center of each area in the peripheral region of the air hole plate 31 and the outer fuel nozzles 25 b corresponding to the plurality of air holes 32 in the second and the third rows in each area in the peripheral region of the air hole plate 31, and the second fuel system 52 to the fourth fuel system 54 are connected to the inner fuel nozzles 25 a and the outer fuel nozzles 25 b separately.
In other words, the second fuel system 52 or the third fuel system 53 is connected to the inner fuel nozzles 25 a of the outer burners 37 corresponding to the plurality of air holes 32 in the first row in the center of each area in the peripheral region of the air hole plate 31, and the branched fourth fuel system 54 is connected to the outer fuel nozzles 25 b of the outer burners 37 corresponding to the plurality of air holes 32 in the second and the third rows in each area in the peripheral region of the air hole plate 31.
In the gas turbine combustor 2 in the present embodiment, the six outer burners 37 installed in the peripheral region of the air hole plate 31 are, as shown in FIG. 3, made up of two specific outer burners 37A which are installed obliquely lower than the center burner 33 in either side (near crossfire tubes 76 to be described later) of the center burner 33 located in the center of the air hole plate 31, and the other four outer burners 37B installed above, below, and obliquely higher than the center burner 33.
The two specific outer burners 37A are divided into a group of outer burner's inner portions 37 a in the inner side and a group of outer burner's outer portions 38 around the outer burner's inner portions 37 a.
In the same manner, the four outer burners 37B are divided into a group of outer burner's inner portions 37 b in the inner side and a group of outer burner's outer portions 38 around the outer burner's inner portions 37 b.
The second fuel system 52 is connected to the inner fuel nozzles 25 a disposed in the outer burner's inner portions 37 a of the two outer burners 37A, and the third fuel system 53 is connected to the inner fuel nozzles 25 a disposed in the outer burner's inner portions 37 b of the four outer burners 37B.
In addition, the fourth fuel system 54 is branched and connected to the outer fuel nozzles 25 b disposed in the outer burner's outer portions 38 of the two specific outer burners 37A and the four outer burners 37B respectively.
Next, an operating method of the gas turbine combustor 2 according to the present embodiment will be described with reference to FIGS. 1 to 4.
The gas turbine combustor 2 in the present embodiment is operated in operation modes shown in FIG. 4. That is, in the operating method of the gas turbine combustor 2 according to the present embodiment, the opening rates of the fuel rate adjusting valves 61 to 64 installed to the first fuel system 51 to the fourth fuel system 54 are adjusted to control the supply of fuel according to an increase in the load of the gas turbine based on an operation mode command outputted from the control device 100 shown in FIG. 1.
For example, when the gas turbine is operated in a low load operation mode A where the center burner 33 of the multi-burner provided to the gas turbine combustor 2 is burned alone, the opening rate of the fuel rate adjusting valve 61 installed to the first fuel system 51 is adjusted to control the supply of fuel based on a control signal from the control device 100 and only the center burner 33 of the gas turbine combustor 2 is burned by itself.
Next, when the gas turbine is switched from the low load operation to partial load operation with increased load, the low load operation mode A where the center burner 33 in the multi-burner provided to the gas turbine combustor 2 is burned alone is switched to a partial load operation mode B where the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the two specific outer burners 37A among the outer burners 37 are burned; in this case, not only the opening rate of the fuel rate adjusting valve 61 installed to the first fuel system 51 for supplying fuel to the center burner 33 but also the opening rate of the fuel rate adjusting valve 62 installed to the second fuel system 52 is controlled based on a control signal from the control device 100 to adjust the supply of fuel supplied to the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the two outer burners 37A to burn the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the two outer burners 37A; in this way, the operation mode is switched to the partial load operation mode B with increased load.
Supplying fuel only to the center burner 33 and the outer burner's inner portions 37 a in the inner side of the two outer burners 37A can limit the number of the fuel nozzles for supplying fuel to a small number, so that a fuel air ratio can be increased locally in the outer burner's inner portions 37 a of the two outer burners 37A.
This causes diffusion flames to be formed in the chamber 5 of the gas turbine combustor 2, thereby reducing the generation of unburned combustibles even when a large amount of air is flowing around.
Furthermore, since air is flowing around the diffusion flames from the outer burner's outer portions 38 in the outer side of the two outer burners 37A, it is possible to prevent the flames formed in the chamber 5 from directly interfering with the liner, and an increase in the metal temperature can be prevented even under a condition that the local fuel air ratio gets high immediately before the operation mode is switched to an operation mode C.
In the operating method of the gas turbine combustor 2 in the present embodiment, when the load of the gas turbine is further increased, the operation mode B is switched to a partial load operation mode C where fuel is supplied not only to the center burner 33 and the outer burner's inner portions 37 a of the two outer burners 37A but also to the fuel nozzles 25 a in the outer burner's inner portions 37 b in the inner side of the four outer burners 37B to be burned; in this case, in addition to controlling the opening rates of the fuel rate adjusting valve 61 installed to the first fuel system 51 for supplying fuel to the center burner 33 and the fuel rate adjusting valve 62 installed to the second fuel system 52 for supplying fuel to the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the two outer burner 37A, the opening rate of the fuel rate adjusting valve 63 installed to the third fuel system 53 for supplying fuel to the fuel nozzles 25 a in the outer burner's inner portions 37 b in the inner side of the four outer burners 37B is controlled based on a control signal from the control device 100 to adjust the supply of fuel to be burned, and the operation mode is switched to the partial load operation mode C with increased load to supply the fuel to the center burner 33, the outer burner's inner portions 37 a of the two outer burners 37A, and the outer burner's inner portions 37 b of the four outer burners 37B to be burned.
In this operation mode C, in the same manner as the operation mode B, the fuel is supplied only to the center burner 33, the outer burner's inner portions 37 a in the inner side of the two outer burners 37A, and the outer burner's inner portions 37 b in the inner side of the four outer burners 37B to be burned, which can limit the number of the fuel nozzles for supplying fuel to a small number, so that the fuel air ratio can be increased locally in the outer burner's inner portions 37 a of the two outer burners 37A and the outer burner's inner portions 37 b of the four outer burners 37B.
This can increase the fuel air ratio locally in the outer burners, and stable diffusion flames can be formed in the chamber 5 of the gas turbine combustor 2 to reduce the generation of unburned combustibles.
Furthermore, since air is flowing around the diffusion flames from the outer burner's outer portions 38 in the outer side of the two outer burner 37A and the four outer burners 38B, it is possible to prevent the flames formed in the chamber 5 from directly interfering with the liner, and an increase in the metal temperature can be prevented even under a condition that the local fuel air ratio gets high immediately before the operation mode is switched to an operation mode D.
In the operating method of the gas turbine combustor 2 in the present embodiment, when the load of the gas turbine is further increased to be full load operation, the operation mode C is switched to a full load operation mode D where fuel is supplied not only to the center burner 33, the fuel nozzles 25 a in the outer burner's inner portions 37 a of the two outer burners 37A, and the fuel nozzles 25 a in the outer burner's inner portions 37 b of the four outer burners 37B but also to the fuel nozzles 25 b in the outer burner's outer portions 38 of the two outer burner 37A and the four outer burners 37B through the fourth fuel system 54 to be burned.
When the partial load operation mode C is switched to the full load operation mode D, in addition to controlling the opening ratios of the fuel rate adjusting valve 61 installed to the first fuel system 51 for supplying fuel to the center burner 33, the fuel rate adjusting valve 62 installed to the second fuel system 52 for supplying fuel to the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the two outer burners 37A, and the fuel rate adjusting valve 63 installed to the third fuel system 53 for supplying fuel to the fuel nozzles 25 a in the outer burner's inner portions 37 b in the inner side of the four outer burners 37B, the opening ratio of the fuel rate adjusting valve 64 installed to the fourth fuel system 54 for supplying fuel to the fuel nozzles 25 b in the outer burner's outer portions 38 in the outer side of the two outer burners 37A and the four outer burners 37B are controlled based on a control signal from the control device 100 to adjust the supply of fuel to be burned; in this way, the operation mode is switched to the full load operation mode D with increased load, and gas turbine is operated in full load by supplying the fuel to the center burner 33, the outer burner's inner portions 37 a of the two outer burners 37A, the outer burner's inner portions 37 b of the four outer burner 37B, and the outer burner's outer portions 38 of the two outer burners 37A and the four outer burners 37B to be burned.
As described above, in the operating method of the gas turbine combustor 2 in the present embodiment, the operation modes A, B, and C are used in lower load conditions than the operation mode D where fuel is supplied to all the fuel systems 51 to 54; and in these modes, the center burner 33, the outer burner's inner portions 37 a of the two outer burner 37A, and the outer burner's inner portions 37 b of the four outer burner 37B among the six outer burners 37 are combined to be used so that the generation of unburned combustibles and an increase in the liner metal temperature can be reduced.
Next, an embodiment of an ignition method in the above operating method of the gas turbine combustor 2 according to the present embodiment will be described with reference to a schematic diagram shown in FIG. 5.
In the schematic diagram of FIG. 5 showing the ignition method of the gas turbine combustor 2, the gas turbine combustor 2 in the present embodiment includes a plurality of gas turbine combustors 2 installed in the outer periphery of the gas turbine; among which one of combustors, a gas turbine combustor 2 a is provided with an ignition plug 77, and the gas turbine combustor 2 a and a gas turbine combustor 2 b installed adjacent to the gas turbine combustor 2 a are connected by a crossfire tube 76 to propagate a flame.
In the gas turbine combustor 2 a according to the present embodiment, out of the six outer burners 37 installed around one center burner 33, the two outer burners 37A disposed obliquely lower than the center burner 33 in either side each have the outer burner's inner portion 37 a in the inner side and the outer burner's outer portion 38 in the outer side.
Furthermore, out of the six outer burners 37 installed around the center burner 33, the remaining four outer burners 37B other than the two outer burners 37A each have the outer burner's inner portion 37 b in the inner side and the outer burner's outer portion 38 in the outer side.
The two outer burners 37A provided with the outer burner's inner portion 37 a are each disposed to be closest to the respective crossfire tube 76 among the plurality of outer burners 37.
At the ignition of the gas turbine combustors 2, fuel is supplied to the center burner 33 and the outer burner's inner portions 37 a of the two outer burners 37A in the multi-burner 6 provided in the gas turbine combustor 2 a having the ignition plug 77, and the ignition plug 77 is ignited to burn the fuel supplied to the center burner 33 and the fuel nozzles 25 a in the outer burner's inner portions 37 a of the outer burners 37A; in this way, flames are formed in the center burner 33 and the outer burner's inner portions 37 a of the two outer burner 37A located near the crossfire tubes 76.
Then, when the inner pressure of the ignited gas turbine combustor 2 a is increased and flames are formed near the crossfire tubes 76, high-temperature combustion gas generated in the gas turbine combustor 2 a flows into the gas turbine combustors 2 b adjacent to the gas turbine combustor 2 a via the crossfire tubes 76.
The configuration of the outer burners 37 made up of a center burner 33, two outer burners 37A installed near the crossfire tubes 76, and four outer burners 37B in the multi-burner 6 in the adjacent gas turbine combustor 2 b is the same as that of the outer burners 37 made up of the center burner 33, the two outer burner 37A, and the four outer burners 37B in the multi-burner 6 in the gas turbine combustor 2 a. So, in the gas turbine combustor 2 b also, the fuel supplied to the fuel nozzles 25 a in the outer burner's inner portions 37 a of the two outer burners 37A located near the crossfire tubes 76 is easily ignited by the high-temperature combustion gas flowed from the gas turbine combustor 2 a via the crossfire tube 76 to form flames in the center burner 33 and the outer burner's inner portions 37 a of the outer burners 37A.
Then, when the inner pressure of the ignited gas turbine combustor 2 b is increased and flames are formed near the crossfire tubes 76, the high-temperature combustion gas generated in the gas turbine combustor 2 b flows into a gas turbine combustor 2 adjacent to the gas turbine combustor 2 b via the crossfire tube 76; in this way, fire can be propagated further to the other gas turbine combustors 2.
As another example of the gas turbine combustor of the present embodiment, a gas turbine combustor 2 is shown in FIG. 6 in which the center burner 33 is divided into a center burner's inner portion 33 a and a center burner's outer portion 33 b and the fuel system 51 for supplying fuel to the center burner 33 is divided into two systems for supplying fuel to the center burner's inner portion 33 a and to the center burner's outer portion 33 b.
In this case, even when the local fuel air ratio of the center burner 33 is low, the rate of fuel supplied to the center burner's inner portion 33 a can be made higher than the rate of fuel supplied to the center burner's outer portion 33 b to keep the local flame temperature of the center portion high, and since the center portion is the source of flame holding, the loss of flame can be prevented. This can widen a range of the operating conditions of the center burner and allows greater flexibility in using the combustor.
According to the present embodiment, a gas turbine combustor and an operating method of the gas turbine combustor can be achieved to allow the gas turbine combustor equipped with a multi-burner to ensure combustion stability in the entire range of load conditions of the gas turbine and reduce the generation of unburned combustibles and an increase in the liner metal temperature at the same time in partial load conditions of the gas turbine.

Embodiment 2

A gas turbine combustor 2 according to the second embodiment of the present invention will be described with reference to FIGS. 7 and 8.
The gas turbine combustor 2 in the present embodiment has the same basic configuration and effect as the gas turbine combustor 2 in the first embodiment shown in FIGS. 1 to 5, thus redundant descriptions are omitted and only a difference will be explained.
FIG. 7 shows the gas turbine combustor 2 in the present embodiment; it is a front view of burners viewed from a chamber. Each burner is divided into sections to which fuel is supplied by the same fuel system.
In the gas turbine combustor 2 in the present embodiment shown in FIG. 7, six outer burners 37 installed in the peripheral region of the air hole plate 31 are, as shown in FIG. 7, made up of three outer burners 37A including the outer burner 37A located at the top and the two specific outer burners 37A installed obliquely lower than the center burner 33 in either side (near the crossfire tubes 76) of the center burner 33 located in the center of the air hole plate 31, and three outer burners 37B installed in the other locations, that is, directly below and obliquely higher than the center burner 33. These outer burners 37A and outer burners 37B are disposed alternately.
In the present embodiment, the inner fuel nozzles 25 a disposed in the outer burner's inner portion 37 a of the outer burner 37A disposed at the top are connected with a branched second fuel system 52.
The gas turbine combustor 2 in the present embodiment is operated in the operation modes shown in FIG. 8. A difference with those of the gas turbine combustor 2 in the first embodiment shown in FIG. 4 is when the gas turbine is switched from the operation mode A to the operation mode B, that is, from low load operation to partial load operation with increased load.
In this case, not only the opening rate of the fuel rate adjusting valve 61 installed to the first fuel system 51 for supplying fuel to the center burner 33 but also the opening rate of the fuel rate adjusting valve 62 installed to the second fuel system 52 is controlled based on a control signal from the control device 100 to adjust the supply of fuel supplied to the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the three outer burners 37A to burn the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the three outer burners 37A; in this way, the operation mode is switched to the partial load operation mode B with increased load.
Supplying fuel only to the center burner 33 and the outer burner's inner portions 37 a located in the inner side of the three outer burners 37A such as above can limit the number of the fuel nozzles for supplying fuel to a small number so that a fuel air ratio can be increased locally in the outer burner's inner portions 37 a of the three outer burner 37A.
This causes diffusion flames to be formed in the chamber 5 of the gas turbine combustor 2, thereby reducing the generation of unburned combustibles even when a large amount of air is flowing around.
Furthermore, since air is flowing around the diffusion flames from the outer burner's outer portions 38 located in the outer side of the three outer burners 37A, it is possible to prevent the flames formed in the chamber 5 from directly interfering with the liner, and an increase in the metal temperature can be prevented even under a condition that the local fuel air ratio gets high immediately before the operation mode is switched to an operation mode C.
Moreover, in the gas turbine combustor 2 in the present embodiment at the occurrence of combustion dynamics, a deviation can be set for the rate of fuel supplied to the outer burner's inner portions 37 a and the outer burner's inner portions 37 b and the temperatures of combustion gas in the neighboring burners can be changed to change the combustion speed of flames formed.
This will shift fluctuating frequencies so that the amplification of pressure fluctuation in the entire gas turbine combustor 2 can be prevented. In the gas turbine combustor 2 in the present embodiment, the three outer burners 37A and the three outer burners 37B are disposed alternately to configure the six outer burners 37, allowing more effective control of the amplification of pressure fluctuation.
According to the present embodiment, a gas turbine combustor and an operating method of the gas turbine combustor can be achieved to allow the gas turbine combustor equipped with a multi-burner to ensure combustion stability in the entire range of load conditions of the gas turbine and reduce the generation of unburned combustibles and an increase in the liner metal temperature at the same time in partial load conditions of the gas turbine.

Embodiment 3

A gas turbine combustor 2 according to the third embodiment of the present invention will be described with reference to FIGS. 9 and 10.
The gas turbine combustor 2 in the present embodiment has the same basic configuration and effect as the gas turbine combustor 2 in the first embodiment shown in FIGS. 1 to 5, thus redundant descriptions are omitted and only a difference will be explained.
FIG. 9 is a gas turbine combustor 2 in the present embodiment; it is a front view of burners viewed from a chamber. Each burner is divided into sections to which fuel is supplied by the same fuel system.
In the gas turbine combustor 2 in the present embodiment shown in FIG. 9, six outer burners 37 installed in the peripheral region of the air hole plate 31 are, as shown in FIG. 9, made up of three outer burners 37A including the outer burner 37A located at the bottom and the specific two outer burners 37A installed obliquely lower than the center burner 33 in either side (near the crossfire tubes 76) of the center burner 33 located in the center of the air hole plate 31, and three outer burners 37B installed higher than the center burner 33, that is, directly above and obliquely higher than the center burner 33.
The gas turbine combustor 2 in the present embodiment is operated in the operation modes shown in FIG. 10. A difference with those of the gas turbine combustor 2 in the first embodiment shown in FIG. 4 is when the gas turbine is switched from the operation mode A to the operation mode B, that is, from low load operation to partial load operation with increased load.
In this case, not only the opening rate of the fuel rate adjusting valve 61 installed to the first fuel system 51 for supplying fuel to the center burner 33 but also the opening rate of the fuel rate adjusting valve 62 installed to the second fuel system 52 is controlled based on a control signal from the control device 100 to adjust the supply of fuel supplied to the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the three outer burners 37A to burn the fuel nozzles 25 a in the outer burner's inner portions 37 a in the inner side of the three outer burners 37A; in this way, the operation mode is switched to the partial load operation mode B with increased load.
Supplying fuel only to the center burner 33 and the outer burner's inner portions 37 a in the inner side of the three outer burners 37A such as this can further reduce the generation of unburned combustibles since flames are formed close to each other and cooling of the frames by the surrounding air is decreased.
According to the present embodiment, a gas turbine combustor and an operating method of the gas turbine combustor can be achieved to allow the gas turbine combustor equipped with a multi-burner to ensure combustion stability in the entire range of load conditions of the gas turbine and reduce the generation of unburned combustibles and an increase in the liner metal temperature at the same time in partial load conditions of the gas turbine.

Embodiment 4

A gas turbine combustor 2 according to the fourth embodiment of the present invention will be described with reference to FIGS. 11 and 12.
The gas turbine combustor 2 in the present embodiment has the same basic configuration and effect as the gas turbine combustor 2 in the first embodiment shown in FIGS. 1 to 5, thus redundant descriptions are omitted and only a difference will be explained.
The gas turbine combustor according to the fourth embodiment of the present invention is shown in FIG. 11. FIG. 11 showing the gas turbine combustor 2 of the present embodiment is a front view of the burners viewed from the chamber. Each burner is divided into sections to which fuel is supplied by the same fuel system.
In the gas turbine combustor 2 in the present embodiment shown in FIG. 11, six outer burners 37 installed in the peripheral region of the air hole plate 31 are, as shown in FIG. 11, made up of two specific outer burners 37A installed obliquely lower than the center burner 33 in either side (near the crossfire tubes 76) of the center burner 33 located in the center of the air hole plate 31 and four outer burners 37B including the two outer burners 37B installed above and below the center burner 33 and the two outer burners 37B installed obliquely higher than the center burner 33.
Furthermore, the burners in the gas turbine combustor 2 in the present embodiment including the center burner 33, the two outer burners 37A, and the four outer burners 37B each have air holes arranged in four circular rows and fuel nozzles disposed in four rows corresponding to the air holes. Among the air holes, the air holes in the two rows from the center in the outer burners 37A are controlled as the same group and the air holes in the two rows from the center in the outer burners 37B are also controlled as the same group.
The gas turbine combustor 2 in the present embodiment is operated in the operation modes shown in FIG. 12 in the same manner as the operation modes of the gas turbine combustor 2 in the first embodiment shown in FIG. 4.
While a gas turbine combustor for a high-output gas turbine tends to be large in size, the gas turbine combustor 2 in the present embodiment can increase the area of boundary between fuel and air by increasing the number of nozzles without enlarging the air holes and the fuel nozzles to promote the mixture of fuel and air. Then, uniform premixed combustion can be achieved to obtain low NOx combustion.
When the size of one burner is enlarged and the number of rows is increased, having only the center row as a flame holding point may cause instability in holding flames.
However, the gas turbine combustor 2 in the present embodiment has two rows of air holes in the outer burner's inner portions 37 a of the outer burners 37A and the outer burner's inner portions 37 b of the outer burners 37B to enlarge the flame holding area, thus flames can be held stably.
As in the gas turbine combustor 2 in the present embodiment, having the two rows of air holes in the outer burner's inner portions 37 of the outer burners 37A and the outer burner's inner portions 37 b of the outer burners 37B will lower the local fuel air ratios in partial load conditions, but since the fuel rate of the entire gas turbine is increased and the fuel is burned diffusely, the discharge of unburned combustibles can be reduced.
According to the present embodiment, a gas turbine combustor and an operating method of the gas turbine combustor can be achieved to allow the gas turbine combustor equipped with a multi-burner to ensure combustion stability in the entire range of load conditions of the gas turbine and reduce the generation of unburned combustibles and an increase in the liner metal temperature at the same time in partial load conditions of the gas turbine.
The present invention is applicable to a gas turbine combustor equipped with a multi-burner and an operating method of the gas turbine combustor.

Claims

1. A gas turbine combustor comprising: a chamber for mixing and burning supplied fuel and supplied air to generate combustion gas;

an air hole plate located in an upstream side of the chamber, forming a plurality of air holes for supplying the air;

a plurality of fuel nozzles for supplying the fuel to the plurality of air holes formed in the air hole plate,

wherein the air holes are disposed in the downstream side of the fuel nozzles that one of the fuel nozzles is paired with one of the air holes; and

a plurality of burners made up of the plurality of air holes and the plurality of fuel nozzles in pairs,

characterized in that,

the plurality of burners are comprised a center burner disposed on an axis of the gas turbine combustor and a plurality of outer burners installed around the center burner,

the center burner is fixed to a first fuel supply system for supplying the fuel to the fuel nozzles in the center burner,

the plurality of outer burners is fixed to a second fuel supply system for supplying the fuel to the fuel nozzles in outer burner's inner portions which are inner regions of specific outer burners among the outer burners,

the plurality of outer burners is fixed to a third fuel supply system for supplying the fuel to the fuel nozzles in outer burner's inner portions which are inner regions of outer burners other than the specific outer burners,

the plurality of outer burners is fixed to a fourth fuel supply system for supplying the fuel to the fuel nozzles in outer burner's outer portions which are outer regions of the outer burners,

wherein when a gas turbine is operated in a low load or partial load condition, the fuel is supplied to the fuel nozzles in the center burner or to the fuel nozzles in the center burner and in the outer burner's inner portions which are the inner regions of the specific outer burners among the plurality of outer burners through the first to the fourth fuel supply systems selected based on the operation condition of the gas turbine.

2. The gas turbine combustor according to claim 1,

wherein the plurality of outer burners are arranged in two groups of the specific outer burners having first outer burner's inner portions supplied with the fuel through the second fuel supply system and the other outer burners having second outer burner's inner portions supplied with the fuel through the third fuel supply system,

every one of the plurality of outer burners has the outer burner's outer portion in the outer side of the outer burner, and the outer burner's outer portions make up a group to be supplied with the fuel through the fourth fuel supply system.

3. The gas turbine combustor according to claim 2,

wherein the specific outer burners having the first outer burner's inner portions supplied with the fuel through the second fuel supply system are the outer burners disposed near crossfire tubes connecting neighboring gas turbine combustors among the plurality of outer burners installed.

4. The gas turbine combustor according to claim 2,

wherein the specific outer burners having the first outer burner's inner portions supplied with the fuel through the second fuel supply system and the other outer burners having the second outer burner's inner portions supplied with the fuel through the third fuel supply system are disposed alternately.

5. The gas turbine combustor according to claim 2,

wherein a plurality of the gas turbine combustors are installed, and

when the gas turbine combustors are ignited, the fuel is supplied to the center burner installed to the gas turbine combustor to be ignited and the outer burner's inner portions which are the inner regions of the outer burners disposed near the crossfire tubes connecting the gas turbine combustor to be ignited and the gas turbine combustors adjacent to the gas turbine combustor to be ignited.

6 An operating method of a gas turbine combustor having a chamber for mixing and burning supplied fuel and supplied air to generate combustion gas; an air hole plate located in an upstream side of the chamber, forming a plurality of air holes for supplying the air; a plurality of fuel nozzles for supplying the fuel to the plurality of air holes formed in the air hole plate, wherein the air holes are disposed in a downstream side of the fuel nozzles that one of the fuel nozzles is paired with one of the air holes; and a plurality of burners made up of the plurality of air holes and the plurality of fuel nozzles in pairs, wherein the plurality of burners are comprised a center burner disposed on an axis of the gas turbine combustor and a plurality of outer burners installed around the center burner,

the plurality of outer burners is fixed to a third fuel supply system for supplying the fuel to the fuel nozzles in outer burner's inner portions which are inner regions of the outer burners other than the specific outer burners, and

the operating method of a gas turbine combustor comprising the steps of:

supplying the fuel through the first fuel supply system to the fuel nozzles disposed in the center burner to burn the chamber when a gas turbine is operated in a low load condition;

supplying the fuel additionally through the second fuel supply system to the fuel nozzles disposed in the outer burner's inner portions which are the inner regions of the specific outer burners among the plurality of outer burners to burn the chamber when the gas turbine is operated in a partial load condition with load increased more than that of the low load gas turbine;

supplying the fuel additionally through the third fuel supply system to the fuel nozzles disposed in the outer burner's inner portions which are the inner regions of all other outer burners among the plurality of outer burners except for the specific outer burners to burn the chamber when the gas turbine is operated in a partial load condition with load increased more than that of said partial load gas turbine; and

supplying the fuel additionally through the fourth fuel supply system to the fuel nozzles disposed in the outer burner's outer portions which are the outer regions of all the outer burners to burn the chamber when the gas turbine is operated in a full load condition with load further increased.