JP7023051B2 - Gas turbine combustor and power generation system - Google Patents

Description

The present invention relates to a gas turbine combustor and a power generation system.

For example, a gas turbine is composed of a compressor, a combustor, and a turbine. A gas turbine compresses air with a compressor to produce high-temperature, high-pressure compressed air, and a combustor supplies fuel to the compressed air for combustion, and the turbine is driven by high-temperature, high-pressure combustion gas. is doing. Further, in a gas turbine, a generator connected to the turbine can be driven to generate electricity.
In addition, there is a combined cycle power generation system in which a gasification furnace is applied to such a gas turbine. In the combined power generation system, solid fuel or liquid fuel is gasified in a gasifier, and the generated gas is sent to a gas turbine for combustion, and the generated combustion gas drives the turbine to generate electricity. Further, the high-temperature exhaust gas discharged from the gas turbine is sent to the boiler to generate steam, and the generated steam drives the steam turbine to generate power.

By the way, in the above-mentioned combined power generation system, carbon dioxide (CO ₂ ) is contained in the exhaust gas discharged from the gas turbine.
Patent Document 1 describes a combined power generation system in which a gasifier and a closed gas turbine that mixes gas fuel and oxygen with exhaust gas and burns them are combined. In this combined cycle power generation system, oxygen is mixed with the exhaust circulating gas discharged from the compressor and burned by a combustor. Further, in this combined cycle power generation system, oxygen is input immediately before the combustion region in consideration of safety and pressure loss of the combustor.

Japanese Unexamined Patent Publication No. 2011-94573

By the way, in the combined cycle power generation system described in Patent Document 1, since oxygen is input at once, the temperature of the combustion gas becomes high and the radiant intensity becomes very strong, which is not preferable. Further, if the temperature of the combustion gas is too high, there is a problem that a large amount of NOx is generated when the fuel contains a small amount of nitrogen components.

INDUSTRIAL APPLICABILITY The present invention is a gas turbine combustor and a power generation system capable of reducing the combustion gas temperature and radiation intensity and suppressing the generation of NOx even when the gas fuel contains a nitrogen component. The purpose is to provide.

According to the first aspect of the present invention, the gas turbine combustor has a combustion cylinder having a tubular shape centered on an axis, and an inert gas from the upstream side of the combustion cylinder to the outer peripheral side of the combustion cylinder. The first inert gas supply unit to be supplied, the second inert gas supply unit that supplies the inert gas from the radial outside centering on the axis of the combustion cylinder to the central portion in the combustion cylinder, and the first. (Ii) The gas fuel supply unit that supplies gas fuel radially outside the inert gas supplied from the inert gas supply unit, and the second inert gas in the combustion cylinder from the upstream side of the combustion cylinder. A first oxygen supply unit that supplies oxygen radially outward from the inert gas supplied from the supply unit, and a first oxygen supply unit that supplies oxygen into the combustion cylinder together with the inert gas from the second inert gas supply unit. It has two oxygen supply units, and the flow rate of oxygen supplied from the first oxygen supply unit is higher than the flow rate of oxygen supplied from the second oxygen supply unit.

According to such a configuration, the gas fuel and oxygen are supplied adjacent to the outside of the inert gas supplied to the central portion in the combustion cylinder, so that the mixture of the gas fuel and oxygen becomes good. .. As a result, the utilization rate of oxygen due to combustion can be brought close to 100%, the residual oxygen in the inert gas can be suppressed, and the combustion efficiency can be improved.
Further, by supplying oxygen from the second inert gas supply unit in addition to the above oxygen and supplying oxygen in two steps, the combustion gas temperature and the radiant intensity can be reduced. Further, even when the gas fuel contains a nitrogen component, the generation of NOx can be suppressed.

In the gas turbine combustor, the second inert gas supply unit may supply the inert gas into the combustion cylinder via a scoop penetrating the outer peripheral surface of the combustion cylinder in the radial direction.
Further, the gas turbine combustor has a combustion cylinder having a tubular shape centered on the axis and a first inert gas supply unit that supplies inert gas from the upstream side of the combustion cylinder to the outer peripheral side of the combustion cylinder. And, from the radial outside centering on the axis of the combustion cylinder, the inert gas is supplied to the central portion in the combustion cylinder via a scoop penetrating the outer peripheral surface of the combustion cylinder in the radial direction. (Ii) From the inert gas supply unit, the gas fuel supply unit that supplies gas fuel radially outside the inert gas supplied from the second inert gas supply unit, and the upstream side of the combustion cylinder, the said The combustion cylinder together with the inert gas through the scoop and the first oxygen supply unit that supplies oxygen radially outward from the inert gas supplied from the second inert gas supply unit in the combustion cylinder. It has a secondary oxygen supply unit that supplies oxygen to the central portion of the inside, and the secondary oxygen supply unit has a second nozzle extending along the central axis of the scoop inside the scoop. The second nozzle may inject the oxygen in the scoop.

According to such a configuration, the second inert gas supply unit can be configured with a simple configuration, and the structure can be simplified.

The gas turbine combustor may include a third oxygen supply unit that supplies oxygen from the radial center on the upstream side of the combustion cylinder toward the downstream side.

According to such a configuration, the combustion gas temperature and the radiant intensity can be further reduced by supplying oxygen in three stages.

The gas turbine combustor has a pilot nozzle provided on the upstream side of the combustion cylinder and injects gas fuel from the radial center toward the downstream side, and the third oxygen supply unit is the tip of the pilot nozzle. Oxygen may be supplied from.

According to such a configuration, the flame retention property at the time of starting the gas turbine can be improved.

In the gas turbine combustor, the flow rate of oxygen supplied from the first oxygen supply unit is the flow rate of oxygen supplied from the second oxygen supply unit and the flow rate of oxygen supplied from the third oxygen supply unit. It may be more than the sum of.
Further, the gas turbine combustor has a combustion cylinder having a tubular shape centered on the axis and a first inert gas supply unit that supplies inert gas from the upstream side of the combustion cylinder to the outer peripheral side of the combustion cylinder. A second inert gas supply unit that supplies an inert gas to the central portion of the combustion cylinder from the radial outside centering on the axis of the combustion cylinder, and a second inert gas supply unit that supplies the inert gas. The gas fuel supply unit that supplies gas fuel radially outside the inert gas, and the inert gas supplied from the second inert gas supply unit in the combustion cylinder from the upstream side of the combustion cylinder. It has a first oxygen supply unit that supplies oxygen radially outside the gas, and a second oxygen supply unit that supplies oxygen from the second inert gas supply unit together with the inert gas into the combustion cylinder. A tertiary oxygen supply unit that supplies oxygen from the radial center on the upstream side of the combustion cylinder to the downstream side is provided, and the flow rate of oxygen supplied from the primary oxygen supply unit is the secondary oxygen. It may be larger than the sum of the flow rate of oxygen supplied from the supply unit and the flow rate of oxygen supplied from the third oxygen supply unit .

According to such a configuration, the oxygen supplied from the primary oxygen supply unit has a stronger influence on the combustion gas temperature and the radiant intensity, so that the combustion gas temperature and the radiant intensity can be easily adjusted.

In the gas turbine combustor, the inert gas may contain carbon dioxide.

According to such a configuration, the inert gas contains carbon dioxide, and the emission of carbon dioxide can be suppressed by circulating the generated inert gas containing carbon dioxide.

According to the second aspect of the present invention, the power generation system includes a gasification furnace that gasifies solid fuel or liquid fuel to generate gas fuel, an oxygen production device that produces oxygen, and exhaust gas compressed by a compressor. A gas turbine that drives a turbine with combustion gas generated by burning an air-fuel mixture supplied with gas fuel and oxygen in any of the above gas turbine combustors, and a generator that generates power with the driving force of the gas turbine. In a power generation system including a circulation path for returning the exhaust gas from the gas turbine to the compressor, the first inert gas supply unit supplies the exhaust circulation gas circulating in the circulation path as the inert gas. Then, the second inert gas supply unit supplies the exhaust circulating gas circulating in the circulation path as the inert gas.

According to the present invention, the gas fuel and oxygen are supplied adjacent to each other outside the inert gas supplied to the central portion in the combustion cylinder, so that the gas fuel and oxygen are mixed well. As a result, the utilization rate of oxygen due to combustion can be brought close to 100%, the residual oxygen in the inert gas can be suppressed, and the combustion efficiency can be improved.
Further, by supplying oxygen from the second inert gas supply unit in addition to the above oxygen and supplying oxygen in two steps, the combustion gas temperature and the radiant intensity can be reduced. Further, even when the gas fuel contains a nitrogen component, the generation of NOx can be suppressed.

It is a schematic diagram of the power generation system of embodiment of this invention. It is a schematic diagram of the combustor of the embodiment of this invention. It is a detailed view of the combustor of embodiment of this invention. FIG. 3 is a sectional view taken along line IV-IV of FIG. 3, which is a view of the combustor viewed from the downstream side.

Hereinafter, the gas turbine combustor and the power generation system according to the embodiment of the present invention will be described in detail with reference to the drawings.
As shown in FIG. 1, the power generation system 1 of the present embodiment is the first to generate electricity by the driving force of the gasifier 11, the gas purification device 12, the oxygen production device 13, the gas turbine 14, and the gas turbine 14. It is a combined power generation system including a generator 15, an exhaust heat recovery boiler 16 (HRSG), a steam turbine 17, and a second generator 18.

The gasification furnace 11 incompletely burns pulverized coal (coal) as a solid fuel to generate unburned gas (H ₂ , CO, CO ₂ , N ₂ , etc.). The gas refining apparatus 12 purifies the gas fuel F ₍ H2, CO) by removing impurities by performing purification treatment or the like from the unburned gas generated in the gasification furnace 11. That is, by passing the unburned gas generated in the gasification furnace 11 through various devices of the gas refining device 12, sulfur compounds, nitrogen compounds and other harmful substances can be removed by the heat of the gas refining device 12. The gasification furnace 11 may be configured to gasify the liquid fuel.

The oxygen producing apparatus 13 produces a high concentration of pure oxygen from the atmosphere. The oxygen production apparatus 13 has, for example, techniques such as a cold fractional distillation method (liquefied fractional distillation method), a pressure sweep adsorption (PSA) method using a zeolite adsorbent, and a pressure sweep adsorption (PSA) method using a carbon molecular sieve. It is possible to adopt a device using.

The gas turbine 14 has a compressor 21, a combustor 22, and a turbine 23. The compressor 21 and the turbine 23 are connected via a turbine shaft 24. The gas turbine 14 and the first generator 15 are connected to each other via a turbine shaft 24.

The compressor 21 of the gas turbine 14 and the combustor 22 are connected by an exhaust circulation gas supply line 25.
The combustor 22 and the gas refiner 12 are connected by a gas fuel supply line 26.
The combustor 22 and the oxygen production device 13 are connected by an oxygen supply line 27. The combustor 22 and the turbine 23 are connected by a combustion gas supply line 28.

The exhaust heat recovery boiler 16 has, for example, a high-pressure boiler, a medium-pressure boiler, and a low-pressure boiler. The exhaust heat recovery boiler 16 can generate steam in each boiler by the exhaust gas discharged from the gas turbine 14.
The turbine 23 and the exhaust heat recovery boiler 16 are connected by an exhaust gas discharge line 29. Exhaust gas E (CO ₂ + H ₂ O) discharged from the turbine 23 is introduced into the exhaust gas discharge line 29. The exhaust heat recovery boiler 16 and the compressor 21 of the gas turbine 14 are connected by an exhaust gas return line 30. The exhaust gas recovery line 31 is branched from the exhaust gas return line 30.

The steam turbine 17 is driven by being supplied with the steam generated by the exhaust heat recovery boiler 16, and can operate the connected second generator 18. The steam supplied to the steam turbine 17 is sent to a condenser (not shown) to be condensed, and then sent to the exhaust heat recovery boiler 16 by a condenser pump. In this case, the gas turbine 14 and the steam turbine 17 may be arranged coaxially to share one generator.

The exhaust gas circulation gas supply line 25, the combustion gas supply line 28, the exhaust gas discharge line 29, and the exhaust gas return line 30 form a circulation path for the exhaust gas E. In the following description, the gas discharged from the turbine 23 is referred to as an exhaust gas E, and the gas compressed by the compressor 21 and supplied to the combustor 22 by the exhaust circulating gas supply line 25 is referred to as an exhaust circulating gas E. .. Exhaust gas E and exhaust circulating gas E are different in temperature and pressure, but are of the same quality. The exhaust gas E and the exhaust circulating gas E function as the inert gas.

Next, the operation of the power generation system 1 of the present embodiment will be described.
In the gasification furnace 11, oxygen, nitrogen, and pulverized coal are supplied, and the pulverized coal is burned inside to generate unburned gas. The unburned gas is cooled by a heat exchanger and then the char is removed, and then the sulfur compound, the nitrogen compound and other harmful substances are removed by the gas refining apparatus 12 to purify the gas fuel F.

In the gas turbine 14, the exhaust gas E taken into the compressor 21 through the exhaust gas return line 30 is compressed to become a high-temperature and high-pressure compressed gas (exhaust circulating gas E). The compressed gas is sent to the combustor 22 as the exhaust circulating gas E via the exhaust circulating gas supply line 25. The gas fuel F refined by the gas purification device 12 is sent to the combustor 22 via the gas fuel supply line 26, and the oxygen (O ₂ ) produced by the oxygen production device 13 is sent to the combustor 22 through the oxygen supply line 27. Will be sent to.

In the combustor 22, the mixed gas of the exhaust circulating gas E, the gas fuel F, and oxygen is ignited and burned. The high-temperature and high-pressure combustion gas generated by the combustor 22 is sent to the turbine 23 via the combustion gas supply line 28, and drives and rotates the turbine shaft 24 by passing through a plurality of stationary blades and moving blades (not shown). .. As a result, the first generator 15 operates to generate electricity.

The exhaust gas E discharged from the turbine 23 is sent to the exhaust heat recovery boiler 16 via the exhaust gas discharge line 29. In the exhaust heat recovery boiler 16, steam is generated by the high-temperature and high-pressure exhaust gas E. The generated steam is sent to the steam turbine 17, and by driving the steam turbine 17, the second generator 18 operates to generate electricity. The exhaust gas heat recovered by the exhaust heat recovery boiler 16 is returned to the compressor 21 via the exhaust gas return line 30, and a part of the exhaust gas is recovered through the exhaust gas recovery line 31.

In the power generation system 1 of the present embodiment configured in this way, the exhaust circulating gas E, the gas fuel F, and oxygen are supplied to the combustor 22 for combustion, so that the gas fuel F and oxygen are sufficiently mixed for efficiency. It is necessary to burn it.

As shown in FIG. 2, the combustor 22 has a cylindrical inner cylinder 2 centered on the axis A and an outer cylinder 3 provided coaxially with the axis A of the inner cylinder 2 on the outer peripheral side of the inner cylinder 2. A combustion cylinder 4 connected to the downstream side Da2 of the inner cylinder 2 and further extending to the downstream side Da2, a pilot nozzle 5 and a main nozzle 6 arranged in the inner cylinder 2, and a combustion cylinder 4 are formed so as to penetrate through the combustion cylinder 4. The scoop 7 is provided with a plurality of oxygen supply units 32 (see FIG. 3) for supplying oxygen into the combustion cylinder 4.
In the following description, the direction in which the axis A of the inner cylinder 2 extends is referred to as the axis direction Da. Further, the direction orthogonal to the axis A is the radial direction, the side away from the axis A in this radial direction is called the radial outside, and the side approaching the axis A in this radial direction is called the radial inside. Further, in the axial direction Da, the left side of FIGS. 2 and 3 is referred to as upstream Da1, and the right side of FIGS. 2 and 3 is referred to as downstream Da2.
Further, in FIGS. 2 and 3, oxygen is indicated by a solid arrow, exhaust circulation gas E is indicated by a one-dot chain arrow, and gas fuel F is indicated by a two-dot chain arrow.

An exhaust circulation gas flow path R is formed between the outer cylinder 3 and the inner cylinder 2 so as to be inverted at the end 2a of the inner cylinder 2 and to introduce the exhaust circulation gas E toward the downstream side Da2. That is, the exhaust circulation gas E is introduced into the exhaust circulation gas flow path R via the exhaust circulation gas supply line 25.
The exhaust gas E flowing into the combustor 22 from between the outer cylinder 3 and the combustion cylinder 4 turns 180 ° at the end wall of the outer cylinder 3 (not shown) and is supplied to the inside of the inner cylinder 2 (main nozzle 6). Will be done.

The combustion cylinder 4 has a tubular shape centered on the axis A, and has a plurality of openings 33 through which the exhaust gas E flows through the downstream Da2. The exhaust gas E flowing from the opening 33 functions as a film fluid.

The scoop 7 is a tubular member that penetrates the outer peripheral surface of the combustion cylinder 4 from the radial outside toward the center of the combustion cylinder 4. Four scoops 7 are provided at equal intervals in the circumferential direction. The number of scoops 7 is not limited to this, and may be, for example, eight.

The pilot nozzle 5 is provided on the upstream side Da1 of the combustion cylinder 4 along the axis A of the inner cylinder 2. The pilot nozzle 5 injects the gas fuel F supplied from the gas refining device 12 from the tip side to the downstream side Da2 and ignites the gas fuel F to generate a flame. That is, a part of the gas fuel F introduced into the combustor 22 via the gas fuel supply line 26 is supplied to the pilot nozzle 5.
The main nozzle 6 is a ring-shaped nozzle that is provided on the radial inside of the inner cylinder 2 and is provided on the radial outside of the pilot nozzle 5 and is coaxial with the inner cylinder 2.

The oxygen supply line 27 into which oxygen is introduced from the oxygen production apparatus 13 is branched into three. The oxygen supply line 27 includes a first oxygen supply line 27a that supplies oxygen to the first oxygen supply unit 32a (see FIG. 3, first nozzle 37) and a second oxygen supply unit 32b (see FIG. 3, second nozzle 38). ) Is branched into a second oxygen supply line 27b and a third oxygen supply line 27c that supplies oxygen to the third oxygen supply unit 32c (see FIG. 3, pilot nozzle 5).
The first oxygen supply line 27a, the second oxygen supply line 27b, and the third oxygen supply line 27c are provided with a regulating valve 42 for adjusting the flow rate of oxygen flowing through the lines.

The gas fuel F supplied from the gas purification apparatus 12 is introduced into the pilot nozzle 5 and the main nozzle 6.
The exhaust gas circulation gas E supplied from the exhaust gas circulation gas supply line 25 is introduced into the scoop 7 together with the exhaust gas circulation gas flow path R. That is, the scoop 7 is a second inert gas supply unit (second exhaust circulation gas supply unit) that supplies the exhaust circulation gas E to the central portion of the combustion cylinder 4 from the radial outside centering on the axis A of the inner cylinder 2. ) Functions. In the combustor 22 of the present embodiment, the exhaust circulation gas E is introduced from the scoop 7 into the center of the combustion cylinder 4 and flows in front of and behind the flow direction of the combustion gas (upstream side Da1 and downstream side Da2).

As shown in FIG. 3, the main nozzle 6 of the present embodiment has a first ring 8 which is an annular member provided on the radial outer side of the pilot nozzle 5 and an annular member provided on the radial outer side of the first ring 8. It has a second ring 9 which is a member.
The main nozzle 6 is provided between the pilot nozzle 5 and the first ring 8 and has an exhaust circulation gas injection nozzle portion 34 for injecting the exhaust circulation gas E. Similarly, the main nozzle 6 is provided between the second ring 9 and the inner cylinder 2, and has an exhaust circulation gas injection nozzle portion 34 for injecting the exhaust circulation gas E. That is, a part of the exhaust circulation gas E supplied from the exhaust circulation gas supply line 25 is introduced into the exhaust circulation gas injection nozzle unit 34.
The exhaust circulation gas injection nozzle portion 34 is provided with a swirl 36 (swivel vane). The swirl 36 applies a turning force to the flow in the exhaust circulating gas injection nozzle portion 34.

The exhaust circulating gas injection nozzle portion 34 of the main nozzle 6 is a first inert gas supply unit (1st inert gas supply unit) that supplies the exhaust circulating gas E, which is an inert gas, from the upstream side Da1 of the combustion cylinder 4 to the outer peripheral portion side in the combustion cylinder 4. It functions as the first exhaust circulation gas supply unit).

The main nozzle 6 is provided between the first ring 8 and the second ring 9, and has a fuel injection nozzle portion 35 for injecting gas fuel F. A plurality of fuel injection holes 35a are formed at the tip of the fuel injection nozzle portion 35. That is, a part of the gas fuel F supplied from the gas fuel supply line 26 is introduced into the fuel injection nozzle unit 35. The fuel injection nozzle unit 35 functions as a gas fuel supply unit that supplies the gas fuel F into the combustion cylinder 4.

A plurality of fuel injection holes 5a and a plurality of oxygen injection holes 5b are formed at the tip of the pilot nozzle 5. As shown in FIG. 4, the plurality of fuel injection holes 5a are formed at intervals in the circumferential direction about the axis A. The plurality of oxygen injection holes 5b are formed inside the plurality of fuel injection holes 5a in the radial direction at intervals in the circumferential direction.

The oxygen supply unit 32 of the present embodiment includes a first oxygen supply unit 32a that supplies oxygen from Da1 on the upstream side of the swirl 36 in the exhaust circulation gas flow path R formed between the outer cylinder 3 and the inner cylinder 2. , A second oxygen supply unit 32b that supplies oxygen from the scoop 7, and a pilot nozzle 5 that functions as a third oxygen supply unit 32c.

The first oxygen supply unit 32a has a first nozzle 37 extending from the downstream side Da2 toward the upstream side Da1 between the inner cylinder 2 and the outer cylinder 3 (diameteral gap).
The first nozzle 37 is connected to the first oxygen supply line 27a. A plurality of oxygen injection holes 40 are formed at the tip of the first nozzle. The oxygen injection hole 40 is directed so as to inject oxygen from the tip end portion of the first nozzle 37 mainly in a direction orthogonal to the extending direction of the first nozzle 37.

The second oxygen supply unit 32b has a second nozzle 38 extending along the central axis of the scoop 7 on the inner peripheral side of the scoop 7. The configuration of the second nozzle 38 is the same as that of the first nozzle 37. The oxygen injected from the oxygen injection hole 40 of the second nozzle 38 is introduced into the central portion of the combustion cylinder 4 together with the exhaust circulation gas E introduced through the scoop 7.

The third oxygen supply unit 32c is a pilot nozzle 5. That is, the oxygen supplied to the pilot nozzle 5 via the third oxygen supply line 27c is injected from the oxygen injection hole 5b formed at the tip of the pilot nozzle 5. That is, the oxygen introduced into the pilot nozzle 5 via the third oxygen supply line 27c is supplied from the radial center of the upstream side Da1 of the combustion cylinder 4 toward the downstream side Da2.

In the combustor 22 of the present embodiment, the flow rate of oxygen supplied from the first oxygen supply unit 32a (first nozzle 37) is the flow rate of oxygen supplied from the second oxygen supply unit 32b (second nozzle 38). It is adjusted so as to be larger than the sum of the flow rate of oxygen supplied from the pilot nozzle 5 which is the third oxygen supply unit 32c.

In the combustor 22 of the present embodiment, the gas fuel F injected from the fuel injection nozzle unit 35 (gas fuel supply unit) of the main nozzle 6 is exhaust circulation supplied from the scoop 7 (second inert gas supply unit). It is supplied radially outside the gas E.
Further, the oxygen injected from the first nozzle 37 is introduced into the main nozzle 6 and then mixed with the exhaust circulation gas E at the exhaust circulation gas injection nozzle unit 34. This air-fuel mixture is supplied radially outward from the exhaust circulation gas E supplied to the central portion of the combustion cylinder 4 via the scoop 7.

According to the combustor 22 of the present embodiment, the gas fuel F and oxygen are supplied adjacent to each other outside the exhaust circulation gas E (inert gas) supplied to the central portion in the combustion cylinder 4. The mixture of the gas fuel F and oxygen becomes good. As a result, the utilization rate of oxygen due to combustion can be brought close to 100%, the residual oxygen in the exhaust circulating gas E can be suppressed, and the combustion efficiency can be improved.
Further, in addition to the above oxygen, oxygen is supplied from the scoop 7 through the second nozzle 38 of the second oxygen supply unit 32b, and oxygen is supplied in two steps to control the combustion gas temperature and radiant intensity. It can be reduced. Further, even when the gas fuel F contains a nitrogen component, the generation of NOx can be suppressed.

Further, by supplying the exhaust circulating gas E into the combustion cylinder 4 via the scoop 7 as the second inert gas supply unit, the second inert gas supply unit can be configured with a simple configuration. Can be simplified.

Further, by providing a pilot nozzle 5 as a third oxygen supply unit 32c for supplying oxygen from the radial center of the upstream side Da1 of the combustion cylinder 4 toward the downstream side Da2, oxygen is supplied in three stages. It is possible to further reduce the combustion gas temperature and the radiant intensity.

Further, by supplying oxygen from the tip of the pilot nozzle 5 as the third oxygen supply unit 32c, the flame retention property at the time of starting the gas turbine 14 can be improved.

Further, the flow rate of oxygen supplied from the first oxygen supply unit 32a (first nozzle 37) is the flow rate of oxygen supplied from the second oxygen supply unit 32b (second nozzle 38) and the third oxygen supply unit 32c. It is adjusted so as to be larger than the sum of the flow rate of oxygen supplied from a certain pilot nozzle 5. As a result, the oxygen supplied from the first oxygen supply unit 32a (first nozzle 37) has a stronger influence on the combustion gas temperature and the radiant intensity, so that the combustion gas temperature and the radiant intensity can be easily adjusted. ..

Further, the exhaust circulating gas E, which is an inert gas, contains carbon dioxide, and by circulating the exhaust circulating gas E, the amount of carbon dioxide emissions can be suppressed.

Although the embodiment of the present invention has been described in detail with reference to the drawings, the specific configuration is not limited to this embodiment and includes design changes and the like within a range not deviating from the gist of the present invention. ..
The main nozzle 6 of the present embodiment is composed of a plurality of rings, but the present invention is not limited to this. For example, the main nozzle may be composed of a plurality of axial nozzles.

Further, although the combustor 22 of the present embodiment has the pilot nozzle 5, it is not always necessary to provide the pilot nozzle.

1 Power generation system 2 Inner cylinder 3 Outer cylinder 4 Combustion cylinder 5 Pilot nozzle 6 Main nozzle 7 Scoop (second inert gas supply unit, second exhaust circulation gas supply unit)
8 1st ring 9 2nd ring 11 Gasifier 12 Gas purification device 13 Oxygen production device 14 Gas turbine 15 1st generator 16 Exhaust heat recovery boiler 17 Steam turbine 18 2nd generator 21 Compressor 22 Combustor 23 Turbine 24 Turbine shaft 25 Exhaust circulation gas supply line 26 Gas fuel supply line 27 Oxygen supply line 28 Combustion gas supply line 29 Exhaust gas discharge line 30 Exhaust gas return line 31 Exhaust gas recovery line 32 Oxygen supply unit 32a First oxygen supply unit 32b Second Oxygen supply section 32c Third oxygen supply section 33 Opening section 34 Exhaust circulation gas injection nozzle section (first inert gas supply section, first exhaust circulation gas supply section)
35 Fuel injection nozzle (gas fuel supply)
36 Swala 37 1st nozzle 38 2nd nozzle 40 Oxygen injection hole 42 Control valve A Axial line E Exhaust circulation gas (inert gas)
F gas fuel D axis

Claims (9)

A combustion cylinder that has a tubular shape centered on the axis,
The first inert gas supply unit that supplies the inert gas from the upstream side of the combustion cylinder to the outer peripheral side of the combustion cylinder,
A second inert gas supply unit that supplies the inert gas to the central portion of the combustion cylinder from the radial outside centered on the axis of the combustion cylinder.
A gas fuel supply unit that supplies gas fuel radially outside the inert gas supplied from the second inert gas supply unit, and a gas fuel supply unit.
A first oxygen supply unit that supplies oxygen radially outward from the inert gas supplied from the second inert gas supply unit in the combustion cylinder from the upstream side of the combustion cylinder.
It has a second oxygen supply unit that supplies oxygen from the second inert gas supply unit to the combustion cylinder together with the inert gas.
A gas turbine combustor in which the flow rate of oxygen supplied from the first oxygen supply unit is larger than the flow rate of oxygen supplied from the second oxygen supply unit. The gas turbine combustor according to claim 1, wherein the second inert gas supply unit supplies the inert gas into the combustion cylinder via a scoop penetrating the outer peripheral surface of the combustion cylinder in the radial direction. A combustion cylinder that has a tubular shape centered on the axis,
The first inert gas supply unit that supplies the inert gas from the upstream side of the combustion cylinder to the outer peripheral side of the combustion cylinder,
The second failure to supply the inert gas from the radial outside centered on the axis of the combustion cylinder to the central portion of the combustion cylinder via a scoop penetrating the outer peripheral surface of the combustion cylinder in the radial direction. The active gas supply unit and
A gas fuel supply unit that supplies gas fuel radially outside the inert gas supplied from the second inert gas supply unit, and a gas fuel supply unit.
A first oxygen supply unit that supplies oxygen radially outward from the inert gas supplied from the second inert gas supply unit in the combustion cylinder from the upstream side of the combustion cylinder.
It has a secondary oxygen supply unit that supplies oxygen to the central portion in the combustion cylinder together with the inert gas via the scoop .
The second oxygen supply unit has a second nozzle extending inside the scoop along the central axis of the scoop.
The second nozzle is a gas turbine combustor that injects the oxygen in the scoop . The gas turbine combustor according to any one of claims 1 to 3, further comprising a third oxygen supply unit that supplies oxygen from the radial center on the upstream side of the combustion cylinder toward the downstream side. The claim that the flow rate of oxygen supplied from the first oxygen supply unit is larger than the sum of the flow rate of oxygen supplied from the second oxygen supply unit and the flow rate of oxygen supplied from the third oxygen supply unit. 4. The gas turbine combustor according to 4. A combustion cylinder that has a tubular shape centered on the axis,
The first inert gas supply unit that supplies the inert gas from the upstream side of the combustion cylinder to the outer peripheral side of the combustion cylinder,
A second inert gas supply unit that supplies the inert gas to the central portion of the combustion cylinder from the radial outside centered on the axis of the combustion cylinder.
A gas fuel supply unit that supplies gas fuel radially outside the inert gas supplied from the second inert gas supply unit, and a gas fuel supply unit.
A first oxygen supply unit that supplies oxygen radially outward from the inert gas supplied from the second inert gas supply unit in the combustion cylinder from the upstream side of the combustion cylinder.
It has a second oxygen supply unit that supplies oxygen from the second inert gas supply unit to the combustion cylinder together with the inert gas.
A third oxygen supply unit that supplies oxygen from the radial center on the upstream side of the combustion cylinder toward the downstream side is provided.
The flow rate of oxygen supplied from the first oxygen supply unit is larger than the sum of the flow rate of oxygen supplied from the second oxygen supply unit and the flow rate of oxygen supplied from the third oxygen supply unit. Combustor. It has a pilot nozzle provided on the upstream side of the combustion cylinder and injects gas fuel from the radial center toward the downstream side.
The gas turbine combustor according to any one of claims 4 to 6, wherein the third oxygen supply unit supplies oxygen from the tip of the pilot nozzle. The gas turbine combustor according to any one of claims 1 to 7, wherein the inert gas contains carbon dioxide. A gasifier that gasifies solid fuel or liquid fuel to produce gas fuel,
Oxygen production equipment that produces oxygen and
The turbine is driven by the combustion gas generated by burning the air-fuel mixture obtained by supplying gas fuel and oxygen to the exhaust gas compressed by the compressor with the gas turbine combustor according to any one of claims 1 to 8. Gas turbine and
A generator that generates electricity from the driving force of a gas turbine,
In a power generation system comprising a circulation path for returning exhaust gas from the gas turbine to the compressor.
The first inert gas supply unit supplies the exhaust circulating gas circulating in the circulation path as the inert gas.
The second inert gas supply unit is a power generation system that supplies the exhaust circulating gas circulating in the circulation path as the inert gas.

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