JP7132096B2 - gas turbine combustor - Google Patents

Description

TECHNICAL FIELD The present invention relates to the structure of a gas turbine combustor, and more particularly to a technique effectively applied to a gas turbine combustor having a multi-cluster burner structure.

In order to improve the efficiency of gas turbines, it is necessary to increase the combustion temperature, and in response to the increase in combustion temperature, there is a demand for improving the reliability of high-temperature components that make up gas turbines.

In addition, since the amount of nitrogen oxides, so-called thermal NOx, generated increases exponentially as the combustion temperature rises, countermeasures are required. As a technology for realizing low NOx, a combustor with a porous coaxial jet burner (multi-cluster burner) structure capable of distributed lean combustion has been developed. The multi-cluster burner consists of an air hole plate with a large number of air holes and a fuel nozzle arranged coaxially with each air hole. It mixes rapidly and creates a lean premixed combustion field to reduce NOx emissions.

As a background art of this technical field, there is a technique such as Patent Document 1, for example. Patent Document 1 describes "In a multi-injection gas turbine combustor in which a plurality of burners each having a plurality of concentrically arranged fuel nozzles and air holes are arranged in the combustion part, air A wall portion that protrudes from the outer peripheral surface of the hole plate to the outer peripheral side of the inner cylinder, and a curved portion that is formed in a convex shape toward the outer cylinder and the fuel header and connected in an arc to the air hole on the outermost periphery of the air hole plate. A gas turbine combustor that reduces the deviation of the flow rate of air supplied to each air hole by providing a guide portion having a gas turbine combustor is disclosed.

JP 2017-53276 A

In the combustor having the multi-cluster burner structure, as will be described later, the amount of combustion air flowing into the air holes provided on the outer peripheral side of the air hole plate and the air holes provided on the inner peripheral side tend to differ. As a result, there is an increase in nitrogen oxide (NOx) emissions, and localized increases in the metal temperature of high-temperature parts such as the air hole plate and inner cylinder reduce the life of combustor components and reduce reliability. Concerned.

SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to provide a gas turbine combustor with a multi-cluster burner structure, in which the amount of combustion air supplied to the air holes on the outer peripheral side and the air holes on the inner peripheral side of the air hole plate is made uniform to achieve combustion characteristics. To provide a highly reliable gas turbine combustor capable of preventing deformation and damage of high-temperature parts such as an air hole plate and an inner cylinder while reducing nitrogen oxide (NOx) emissions. .

In order to solve the above problems, the present invention provides an inner cylinder that forms a combustion chamber of a gas turbine combustor, an outer cylinder that encloses the inner cylinder, and an annular flow formed by the inner cylinder and the outer cylinder. an air hole plate disposed at the downstream end of the combustion air flowing through the passage and provided with a plurality of air holes for introducing the combustion air into the combustion chamber; a plurality of fuel nozzles for ejecting fuel; a drift vane disposed downstream of the combustion air flowing through the annular flow path; and a rib disposed upstream of the combustion air from the drift vane ; The drift vane is arranged near the outer circumference of the air hole plate and on the inner circumference of the outer cylinder, and the rib is arranged on the outer circumference of the inner cylinder .

According to the present invention, in a gas turbine combustor with a multi-cluster burner structure, it is possible to reduce the amount of nitrogen oxide (NOx) emissions while preventing deformation and damage to high-temperature parts such as air hole plates and inner cylinders. A highly efficient gas turbine combustor can be realized.

Problems, configurations, and effects other than those described above will be clarified by the following description of the embodiments.

1 is a diagram conceptually showing the configuration of a gas turbine power generation facility to which the present invention is applied; FIG. FIG. 2 is an enlarged sectional view of a combustor 3 in FIG. 1; FIG. 3 is a view of the air hole plate 33 in FIG. 2 viewed from the downstream side in the flow direction of the combustion gas 20; 3 is an enlarged cross-sectional view of the vicinity of the outer peripheral portion of the air hole plate 33 in FIG. 2; FIG. 4 is an enlarged cross-sectional view of the vicinity of the outer periphery of the air hole plate 33 according to Embodiment 1 of the present invention; FIG. FIG. 6 is a diagram showing the arrangement of the drift vanes 40 in FIG. 5; FIG. 6B is a view of the support 41 in FIG. 6A taken along line AA'. It is a figure which shows the modification of FIG. FIG. 8 is an enlarged cross-sectional view of the vicinity of the outer periphery of an air hole plate 33 according to Embodiment 2 of the present invention; FIG. 9 is a diagram showing a modification of FIG. 8;

Hereinafter, embodiments of the present invention will be described with reference to the drawings. In addition, in each drawing, the same configurations are denoted by the same reference numerals, and detailed descriptions of overlapping portions are omitted.

First, a general gas turbine power generation facility (gas turbine plant) to which the present invention is applied will be described with reference to FIGS. 1 to 4. FIG. FIG. 1 is a diagram showing a schematic configuration of gas turbine power generation equipment. FIG. 2 is an enlarged cross-sectional view showing the internal configuration of the combustor 3 of FIG. 1, and FIG. 3 is a view of the air hole plate of the combustor 3 viewed from the downstream side in the flow direction of the combustion gas. Also, FIG. 4 is an enlarged cross-sectional view of the vicinity of the outer peripheral portion of the air hole plate 33 in a conventional gas turbine combustor shown as a comparative example of the present invention.

The gas turbine power generation facility (gas turbine plant) shown in FIG. and a combustor (gas turbine combustor) 3 that generates high-temperature combustion gas 20 by mixing and burning fuel, and a gas turbine 2 that is driven by the combustion gas 20 generated by the combustor 3. , and a generator 23 which is connected to the gas turbine 2 by a drive shaft and which rotates and generates power when the gas turbine 2 is driven.

The fuel supply system that supplies fuel to the combustor 3 includes an oil fuel supply device 5 that supplies fuel containing oil, a gas fuel supply device 6 that supplies gas fuel containing hydrogen (H ₂ ), and a concentration adjustment A nitrogen supply device 7 is provided for supplying, for example, nitrogen (N ₂ ) gas as a carrier gas.

Fuel containing oil is supplied from the oil-fuel supply device 5 to the combustor 3 through the oil-fuel pipe 8 and the oil-fuel flow control valve 9 . Gas fuel containing hydrogen (H ₂ ) is supplied from the gas fuel supply device 6 through the gas fuel pipe 10, and then through the pilot burner gas fuel flow control valve 13 and the pilot burner gas fuel pipe 11 to the combustor 3. and a system supplied to the combustor 3 via the main burner gas fuel flow control valve 14 and the main burner gas fuel pipe 12 .

Nitrogen (N ₂ ) gas is supplied from the nitrogen supply device 7 through the nitrogen supply pipe 15, and then through the pilot burner nitrogen flow control valve 18 and the pilot burner nitrogen supply pipe 16 to the pilot burner gas fuel pipe 11. and a system supplied to the main burner nitrogen flow control valve 19 and the main burner nitrogen supply pipe 17, and supplied to each gas fuel pipe.

Exhaust gas 21 discharged from the gas turbine 2 is discharged into the atmosphere from a stack (smoke chamber) 22 after heat and moisture are recovered by an exhaust heat recovery boiler and a water recovery device (not shown).

Combustor (gas turbine combustor) 3, as shown in FIG. The inner cylinder 26 of the gas turbine combustor 3 that burns fuel to generate high-temperature combustion gas 20, and the high-temperature combustion gas 20 generated inside the inner cylinder 26 (combustion chamber) is delivered from the inner cylinder 26 to the gas turbine. 2, an outer cylinder 27 that houses (incorporates) the inner cylinder 26 and the transition piece 25 and is attached to the vehicle compartment 24, an end cover 28, etc. consists of

An air hole plate 33 for introducing compressed air (combustion air) 4 into the interior (combustion chamber) of the inner cylinder 26 is arranged on the upstream side of the inner cylinder 26 . A sealing member 36 is arranged to prevent leakage of the air (combustion air) 4 . The air hole plate 33 is provided with a large number of air holes 34 for introducing compressed air (combustion air) 4 .

The end cover 28 is provided with main gas manifolds 29 and 30 and a pilot gas manifold 31 . A main burner gas fuel pipe 12 is connected to the main gas manifolds 29 and 30, and gas fuel containing hydrogen (H ₂ ) supplied from the gas fuel supply device 6 is supplied to the main gas manifolds 29 and 30. .

A pilot burner gas fuel pipe 11 is connected to the pilot gas manifold 31 , and gas fuel containing hydrogen (H ₂ ) supplied from the gas fuel supply device 6 is supplied to the pilot gas manifold 31 .

A gas fuel nozzle 35 is connected to the main gas manifolds 29 , 30 and the pilot gas manifold 31 , and the opposite end of the gas fuel nozzle 35 is positioned upstream within each air hole 34 of the air hole plate 33 . The gas fuel supplied through the main gas manifolds 29 and 30 and the pilot gas manifold 31 is jetted from the gas fuel nozzles 35 into the air holes 34 of the air hole plate 33 . Compressed air (combustion air) 4 is introduced into the interior (combustion chamber) of the inner cylinder 26 through the gap between the air hole 34 and the gas fuel nozzle 35 .

An oil fuel nozzle 37 is arranged at the axial center position of the end cover 28 and the air hole plate 33, and the fuel containing the oil supplied from the oil fuel supply device 5 flows from the oil fuel nozzle 37 into the inner cylinder 26 ( combustion chamber). The oil-containing fuel supplied from the oil-fuel nozzle 37 is normally used as the starting oil fuel.

A mixed gas of compressed air (combustion air) 4 and fuel introduced into the interior (combustion chamber) of the inner cylinder 26 is ignited by the spark plug 32 and combusted.

In the combustor 3 of this embodiment, as shown in FIG. 3, a plurality of burners each having a plurality of gas fuel nozzles 35 and air holes 34 arranged concentrically are arranged inside the inner cylinder 26 (combustion chamber). This is a so-called multi-injection gas turbine combustor. One burner (pilot burner) 38 arranged coaxially with the combustor 3 at the center of the air hole plate 33, and six burners (main burners) 39A to 39F arranged around the pilot burner 38. there is That is, in this embodiment, the combustor 3 has a multi-burner structure with seven burners. The pilot burner 38 and the main burners 39A-39F share the air hole plate 33.

An oil-fuel nozzle 37 is arranged at the center of the pilot burner 38, and fuel including oil is supplied from the oil-fuel pipe 8 connected to the oil-fuel nozzle 37, and supplied to the inside (combustion chamber) of the inner cylinder 26. be done. A plurality of gas fuel nozzles 35 and a plurality of air holes 34 are arranged concentrically around the oil fuel nozzle 37, and hydrogen (H ₂ ) is mixed with the compressed air (combustion air) 4 introduced from the plurality of air holes 34 and supplied to the inside of the inner cylinder 26 (combustion chamber).

Each of the main burners 39A to 39F has gas fuel nozzles 35 and air holes 34 concentrically arranged in a plurality of annular rows (three rows in FIG. 3). Gas fuel containing hydrogen (H ₂ ) is supplied from the fuel pipe 12 and supplied to the inside (combustion chamber) of the inner cylinder 26 .

Problems in a conventional gas turbine combustor will be described in detail with reference to FIG. In the gas turbine combustor, as shown in FIG. 4, the compressed air (combustion air) 4 supplied from the compressor 1 passes through the air hole plate 33 in an annular flow path formed by the inner cylinder 26 and the outer cylinder 27 . It flows down toward the air holes 34 .

The combustion air 4a in the annular flow path needs to change its flow direction greatly because it flows into the air holes 34 of the air hole plate 33 in the region of the end cover 28. Due to the inertial force of the combustion air 4a, separation vortices and the like may be formed at the corners of the air holes 34a. may decrease.

Combustible gas including, for example, natural gas or hydrogen (H ₂ ) is supplied to each air hole 34 from a gas fuel nozzle 35 via a fuel manifold (main gas manifold 29). The gas flow rate of the gas fuel supplied from 35 is supplied to each gas fuel nozzle 35 substantially equally regardless of the position of the gas fuel nozzle 35 .

For this reason, the mixture density of the fuel gas and combustion air formed in the air hole 34a on the outer peripheral side of the air hole plate 33 with a small inflow air flow rate is It is higher than the peripheral air holes 34b.

When the fuel concentration inside the air hole 34 increases, the local temperature of the combustion flame formed downstream thereof becomes high, resulting in a large increase in nitrogen oxide (NOx) emissions.

In addition, since the temperature of the combustion gas rises, the temperature of metals such as the air hole plate 33 and the inner cylinder 26, which constitute the combustor 3, increases locally. Conceivable.

Further, in the air hole 34a into which the air flow rate is small, the air flow rate is lower than the flow velocities 4d to 4f as in flow velocities 4b and 4c, and the fuel concentration is increased. In some cases, the reliability of the air hole plate 33 is impaired due to the reverse flow of the flame.

Therefore, it is necessary to make the flow rate of air flowing into each air hole uniform in each air hole in order to realize low NOx combustion that reduces the environmental load while maintaining the reliability of the combustor.

Next, a combustor (gas turbine combustor) according to Example 1 of the present invention will be described with reference to FIGS. 5 to 6B. FIG. 5 is an enlarged sectional view showing the vicinity of the outer peripheral portion of the air hole plate 33 in the combustor 3 of this embodiment. 6A is a view showing the arrangement of the drift vanes 40 in FIG. 5, and FIG. 6B is a view of the support 41 in FIG. 6A taken along line A-A'.

In this embodiment, in an annular flow path 43 formed by the inner cylinder 26 and the outer cylinder 27 , a plurality of supports 41 are arranged in the circumferential direction extending from the inner peripheral side of the outer cylinder 27 , and extend in the axial direction of the inner cylinder 26 . At the same time, a deviation (deflection) vane 40, which is a member that divides the annular flow path 43 into an inner peripheral side flow path and an outer peripheral side flow path, is installed, and upstream of the deviation (deflection) vane 40, the radial direction of the inner cylinder 26 A rib 42 extending to the outer peripheral side is arranged to form a gap in the axial direction with the drift (deflection) vane 40 .

In other words, the gas turbine combustor of this embodiment is formed of an inner cylinder 26 forming a combustion chamber 47 of the gas turbine combustor, an outer cylinder 27 enclosing the inner cylinder 26 , and the inner cylinder 26 and the outer cylinder 27 . an air hole plate 33 provided with a plurality of air holes 34 for introducing the combustion air 4 into the combustion chamber 47; A plurality of gas fuel nozzles 35 disposed on the side of the combustion chamber 47 for ejecting fuel into the combustion chamber 47 , a drift (deflection) vane 40 disposed downstream of the combustion air 4 flowing through the annular passage 43 , and a ) with ribs 42 arranged upstream of the combustion air 4 relative to the vanes 40;

A drift (deflection) vane 40 is arranged near the outer periphery of the air hole plate 33 . The drift (deflection) vanes 40 are arranged on the inner peripheral side of the outer cylinder 27 , and the ribs 42 are arranged on the outer peripheral side of the inner cylinder 26 . As shown in FIG. 6A, the drift (deflection) vanes 40 are fixed to the casing 27 by a plurality of supports 41 .

Compressed air (combustion air) 4 flowing down an annular flow path 43 formed by the inner cylinder 26 and the outer cylinder 27 is deflected by the ribs 42 in the flow direction like the combustion air 4-1, and is deflected by deflecting vanes. The combustion air 4-2 flows into an annular flow path 44 formed by 40 and the outer cylinder 27, and the combustion air 4-2 flows in from the gap between the deflection vanes 40 and the ribs 42 in the axial direction. The respective air distributions of the combustion air 4-1 and the combustion air 4-2 are set from the structural specifications of the drift (deflection) vanes 40, the support 41, and the ribs 42, the axial clearances between the drift (deflection) vanes 40 and the ribs 42, and the like. It is possible to

In this embodiment, an example in which the flow rate of the combustion air 4-1 is greater than that of the combustion air 4-2 will be described. The combustion air 4-1 whose flow direction is changed radially outward by the ribs 42 flows near the inner peripheral wall of the outer cylinder 27 and flows into the flow path 46 formed by the end cover 28 and the air hole plate 33.

In the flow path 46, the flow 4a flowing down the flow path (annular flow path) 44 and the flow 4-2a flowing down the flow path (annular flow path) 45 join together. The combustion air 4a is divided into flows 4a-1, 4a-2, and 4a-3 due to the pressure difference with the (combustion chamber) 47 (exactly, the inlet/outlet of each air hole 34) and flows into each air hole 34. FIG.

4 described above, the main component of the combustion air 4a tends to flow in a region close to the inner cylinder 26, the flow velocity of the combustion air is high at the upstream end of the inner cylinder 26, and Since the combustion air flows into the air holes 34 at the ends, the flow direction of the combustion air is deviated. There is a risk that the flow rate of air flowing into the air holes 34a on the outer peripheral side of the air hole plate 33 will decrease.

However, in the present embodiment, since the main component of the combustion air flow 4a flowing through the flow path (annular flow path) 44 is positioned radially outward from the outer peripheral side of the air hole plate 33, 4a-1 branched from the combustion air 4a The flow tends to flow into the air holes 34a against the inertial force of the combustion air 4a.

As a result, the air flow rates 4b to 4f flowing into the respective air holes 34 can be substantially the same (uniform).

When the air flow rates 4b to 4f flowing into each air hole 34 become substantially the same (uniform), the fuel gas flow rate supplied from the gas fuel nozzle 35 arranged upstream of each air hole 34 becomes substantially the same (uniform). As a result, the mixture concentration of fuel and air in each air hole 34 becomes uniform, the temperature distribution of the combustion flame becomes uniform, and there are no locally high areas, and the amount of nitrogen oxides (NOx) generated can be suppressed. , the metal temperature of the air hole plate 33 and the inner cylinder 26 does not rise locally, and it is possible to suppress the reduction in the service life of the parts concerned.

In addition, the jet speed of the air-fuel mixture jetted from each air hole 34 to the combustion chamber (inside of the inner cylinder) 47 becomes almost the same (uniform), and there are no air holes whose jet speed decreases. It is possible to suppress the backflow phenomenon of the flame to the air holes 34 due to the speed reduction, and to suppress the decrease in the service life of the air hole plate 33 .

Furthermore, even if a flame is generated inside the air hole 34 by combustible substances contained in the combustion air 4 and the fuel gas, since there is no air hole in which the air-fuel mixture flow velocity is low, Since the flame generated in 1 flows down to the outside of the air hole 34 and does not stagnate inside the air hole 34, it is possible to suppress the life of the air hole plate 33 from being shortened.

On the other hand, the combustion air 4-2 that has flowed into the flow path (annular flow path) 45 formed by the inner cylinder 26 and the deflection vanes 40 has a cross-sectional area of the flow path 45 and a The flow rate of -2 makes it possible to control the flow velocity of the combustion air 4-2a, and the combustion air 4-2a is supplied to the sealing member 36 disposed on the outer peripheral side of the air hole plate 33 and the inlet end of the inner cylinder 26. Therefore, it becomes possible to supply air for cooling the sealing member 36 .

In this embodiment, the ribs 42 are provided on the inner cylinder 26 for the purpose of deflecting the flow of the combustion air 4. However, by providing the ribs 42 on the inner cylinder 26, the cylindrical inner cylinder 26 It can also be expected to have the effect of increasing the strength of

As shown in FIGS. 6A and 6B, a plurality of supports 41 arranged in the circumferential direction are streamlined so as not to cause large turbulence in the flow of the combustion air 4 (4-1). is more preferred.

FIG. 7 shows an example in which a drift (deflection) vane 40 is installed on the inner cylinder 26 side, and corresponds to the modification of FIG. 5, the drift (deflection) vanes 40 and the support 41 are provided on the inner peripheral side of the outer cylinder 27, whereas they are provided on the outer peripheral side of the inner cylinder 26 in FIG. That is, both the drift (deflection) vanes 40 and the ribs 42 are arranged on the outer peripheral side of the inner cylinder 26 . A drift (deflection) vane 40 is fixed to the inner cylinder 26 by a plurality of supports 41 .

Even if the drift (deflection) vanes 40, supports 41, and ribs 42 are installed on the inner cylinder 26 side as shown in FIG. ) By appropriately setting the axial gaps between the vanes 40 and the ribs 42, it is possible to set the respective air distributions of the combustion air 4-1 and the combustion air 4-2.

As described above, according to the gas turbine combustor of this embodiment, the combustion characteristics are improved by equalizing the amount of combustion air supplied to the air holes on the outer peripheral side and the air holes on the inner peripheral side of the air hole plate. It is possible to prevent deformation and damage to high-temperature parts such as air hole plates and inner cylinders while reducing nitrogen oxide (NOx) emissions.

In addition, in the first embodiment, the fuel gas containing hydrogen is targeted, and the main focus is on the burner in which the pilot burner is provided with an oil fuel nozzle for burning oil fuel. However, the multi-cluster burner does not contain hydrogen. Since low NOx stable combustion is possible even for fuel gas, even if the present invention is applied to a combustor without oil fuel nozzles, the actions and effects described in the embodiments can be obtained.

A combustor (gas turbine combustor) according to a second embodiment of the present invention will be described with reference to FIG. FIG. 8 is an enlarged sectional view showing the vicinity of the outer peripheral portion of the air hole plate 33 in the combustor 3 of this embodiment.

In this embodiment, an annular flow path 43 formed by the inner cylinder 26 and the outer cylinder 27 is provided with a biased flow (deflection) vane 48 for deflecting the flow direction of the compressed air (combustion air) 4. A rib 49 extending radially outwardly of the inner cylinder 26 is arranged on the upstream side of the vane 48 to form a gap in the axial direction with the drift (deflect) vane 48 , and the upstream end of the inner cylinder 26 (the downstream end of the combustion air 4 ) is arranged. ) is provided with a turn vane 50 for deflecting the air flow, and a spacer 51 for deflecting the combustion air is provided at a corner portion formed at the junction of the outer cylinder 27 and the end cover 28 .

The turn vanes 50 are arranged on the downstream side of the combustion air 4 from the drift (deflection) vanes 48 and on the outer peripheral side of the inner cylinder 26 .

In this embodiment, the deflection vanes 48 arranged in the annular flow path 43 are provided with an inclination angle α with respect to the inner cylinder 26 so that the combustion air 4-1 is deflected toward the outer peripheral side of the annular flow path 43. In this example, the ribs 49 installed on the inner cylinder 26 are also inclined.

As shown in FIG. 8, since the drift (deflection) vanes 48 are installed at an angle, the main components of the combustion air 4a flowing through the flow path (annular flow path) 44 are more concentrated in the outer cylinder than in the first embodiment. Since the air flows down through the region near the inner wall side of the air hole plate 33, the air easily flows into the air holes 34a arranged on the outer peripheral side of the air hole plate 33.

By controlling the inclination angle α of the drift (deflection) vanes 48, it becomes possible to control the combustion air flow rate flowing into each air hole 34, and the margin for designing and developing the combustor 3 is increased. For example, it is possible to change the hole diameter of the air hole 34 at the corresponding position as the deflected combustion air flow rate increases or decreases. Since the degree of freedom for selecting the flow rate, ejection speed, and direction of the mixed gas ejected from the air holes is increased depending on the hole diameter specifications of the air holes 34, a combustion method for suppressing nitrogen oxides (NOx) and an air hole plate 33 , are effective for controlling the metal temperature of the inner cylinder 26 .

Further, in this embodiment, since the turn vanes 50 for deflecting the air flow are installed at the upstream end of the inner cylinder 26 (the downstream end of the combustion air 4), the air flow 4- 2, since the flow rate of the air flow 4-2a is determined by the flow rate of the air flowing into the flow path (annular flow path) 45, the flow velocity of the air that is easily deflected by the turn vanes 50 can be controlled by the gap between the deflection vanes 48 and the ribs 49. . For example, as shown in FIG. 8, by arranging the ribs 49 at an angle downstream of the combustion air 4, the gap between the drift (deflection) vanes 48 and the ribs 49 is controlled.

In addition, due to the flow velocity of the air flow 4-2a and the structure of the turn vanes 50, air can be appropriately introduced into the seal member 36 installed at the connection portion between the inner cylinder 26 and the air hole plate 33. It is possible to efficiently cool the inner surface of the inner cylinder 26 at the hole outlet.

Furthermore, in this embodiment, an end cover 28 is arranged downstream of the combustion air 4 from the air hole plate 33 and connected to the outer cylinder 27 , and the combustion air 4 is disposed at the junction of the outer cylinder 27 and the end cover 28 A spacer 51 is arranged to deflect the . Since the spacer 51 that deflects the combustion air is arranged at the corner formed at the joint of the outer cylinder 27 and the end cover 28, the air flow 4a that flows down the flow path (annular flow path) 44 hits the wall surface of the spacer 51. It is conceivable to prevent an increase in pressure loss by suppressing the occurrence of eddy currents that are likely to occur at corners.

FIG. 9 shows an example in which the drift (deflection) vane 40 is installed without providing the inclination angle α, and corresponds to the modification of FIG. In FIG. 8, the drift (deflection) vanes 48 are installed with an inclination angle α, whereas in FIG. 9 the drift (deflection) vanes 40 are installed substantially parallel to the inner cylinder 26 and the outer cylinder 27. . As shown in FIG. 9, even when the drift (deflection) vane 40 is installed without providing the inclination angle α, the structural specifications of the drift (deflection) vane 40, the support 41, and the rib 42 and the drift (deflection) vane 40 It is possible to set the air distribution of each of the combustion air 4-1 and the combustion air 4-2 by appropriately setting the axial clearances of the ribs 42 and the like.

As described above, according to the gas turbine combustor of this embodiment, by arranging the deflection vanes 48, the ribs 49, the turn vanes 50, and the spacers 51, air flows into the air holes 34 of the air hole plate 33. By controlling the air flow distribution according to the performance required of the combustor 3, it is possible to achieve both low NOx combustion and stable combustion. Become.

In addition, the present invention is not limited to the above-described embodiments, and includes various modifications. For example, the above-described embodiments have been described in detail in order to explain the present invention in an easy-to-understand manner, and are not necessarily limited to those having all the described configurations. In addition, it is possible to replace part of the configuration of one embodiment with the configuration of another embodiment, and it is also possible to add the configuration of another embodiment to the configuration of one embodiment. Moreover, it is possible to add, delete, or replace a part of the configuration of each embodiment with another configuration.

DESCRIPTION OF SYMBOLS 1... Compressor 2... Gas turbine 3... Combustor (gas turbine combustor)
4, 4a Compressed air (combustion air)
5 Oil fuel supply device 6 Gas fuel supply device 7 Nitrogen supply device 8 Oil fuel pipe 9 Oil fuel flow control valve 10 Gas fuel pipe 11 Pilot burner gas fuel pipe 12 Main burner gas fuel pipe 13 Pilot burner gas fuel flow control valve 14 Main burner gas fuel flow control valve 15 Nitrogen supply pipe 16 Pilot burner nitrogen supply pipe 17 Main burner nitrogen supply pipe 18 Pilot burner nitrogen flow control valve 19 Main burner nitrogen flow control Valve 20 Combustion gas 21 Exhaust gas 22 Chimney (smoke chamber)
DESCRIPTION OF SYMBOLS 23... Generator 24... Vehicle interior 25... Transition pipe 26... Inner cylinder 27... Outer cylinder 28... End cover 29, 30... Main gas manifold 31... Pilot gas manifold 32... Spark plug 33... Air hole plate 34, 34a, 34b ... Air hole 35 ... Gas fuel nozzle 36 ... Seal member 37 ... Oil fuel nozzle 38 ... Pilot burner 39A to 39F ... Main burner 40, 48 ... Deviation (deflection) vane 41 ... Support 42, 49 ... Rib 43 ... Annular flow path 44 , 45, 46... Flow path 47... Combustion chamber (inside of inner cylinder)
50... Turn vane 51... Spacer

Claims (7)

an inner cylinder forming a combustion chamber of a gas turbine combustor;
an outer cylinder enclosing the inner cylinder;
an air hole plate disposed at the downstream end of the combustion air flowing through the annular flow path formed by the inner cylinder and the outer cylinder, and provided with a plurality of air holes for introducing the combustion air into the combustion chamber;
a plurality of fuel nozzles located upstream of the plurality of air holes and ejecting fuel into the combustion chamber;
a drift vane disposed downstream of the combustion air flowing through the annular flow path;
a rib arranged upstream of the combustion air from the drift vane;
with
The drift vane is arranged near the outer periphery of the air hole plate and on the inner periphery of the outer cylinder,
A gas turbine combustor , wherein the rib is arranged on the outer peripheral side of the inner cylinder . A gas turbine combustor according to claim 1 , comprising:
A gas turbine combustor, wherein the drift vanes are fixed to the outer cylinder by a plurality of supports. A gas turbine combustor according to claim 2 ,
A gas turbine combustor, wherein the support has a streamlined shape. an inner cylinder forming a combustion chamber of a gas turbine combustor;
an outer cylinder enclosing the inner cylinder;
an air hole plate disposed at the downstream end of the combustion air flowing through the annular flow path formed by the inner cylinder and the outer cylinder, and provided with a plurality of air holes for introducing the combustion air into the combustion chamber;
a plurality of fuel nozzles located upstream of the plurality of air holes and ejecting fuel into the combustion chamber;
a drift vane disposed downstream of the combustion air flowing through the annular flow path;
a rib arranged upstream of the combustion air from the drift vane;
with
The drift vanes are arranged near the outer periphery of the air hole plate and on the outer periphery side of the inner cylinder, and are fixed to the inner cylinder by a plurality of streamlined supports,
A gas turbine combustor , wherein the rib is arranged on the outer peripheral side of the inner cylinder . an inner cylinder forming a combustion chamber of a gas turbine combustor;
an outer cylinder enclosing the inner cylinder;
an air hole plate disposed at the downstream end of the combustion air flowing through the annular flow path formed by the inner cylinder and the outer cylinder, and provided with a plurality of air holes for introducing the combustion air into the combustion chamber;
a plurality of fuel nozzles located upstream of the plurality of air holes and ejecting fuel into the combustion chamber;
a drift vane disposed downstream of the combustion air flowing through the annular flow path;
a rib arranged upstream of the combustion air from the drift vane;
with
A turn vane is arranged downstream of the drift vane in the combustion air and on the outer peripheral side of the inner cylinder ,
A gas turbine combustor according to claim 1, wherein the drift vanes are arranged at an inclination angle so that the combustion air flowing through the annular flow path is deflected toward the outer circumference of the annular flow path . A gas turbine combustor according to claim 5 ,
an end cover arranged downstream of the combustion air from the air hole plate and connected to the outer cylinder;
A gas turbine combustor, wherein a spacer for deflecting combustion air is arranged at a junction between the outer cylinder and the end cover. A gas turbine combustor according to claim 6 ,
A gas turbine combustor, wherein the ribs are arranged at an angle downstream of the combustion air.

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