JP2006162117A - Gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine operable with stable combustion, improved in combustion efficiency by reducing the unburnt content in a partial load, by applying a catalyst to a combustor. <P>SOLUTION: A catalyst layer 14 is arranged over the inside from a root part of a bypass elbow 9 to a tail pipe 10, and a bypass elbow fuel nozzle 15 projecting inside the bypass elbow 9, is arranged between the bypass valve BV on its air flow upstream side. This constitution burns lean fuel via the catalyst layer 14 by jetting the fuel from the bypass elbow fuel nozzle 15 in the partial load. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention relates to a gas turbine, and more particularly to a gas turbine having a structure incorporating a catalyst.

  An outline of a conventional gas turbine will be described. FIG. 9 is a longitudinal sectional view schematically showing a schematic configuration of a combustor and its peripheral portion in a conventional gas turbine. As shown in the figure, the combustor of the gas turbine has a tail cylinder 10 having an internal space as a combustion chamber and an inner cylinder 2 having a mechanism for forming a premixed gas. The cylinder 2 communicates with the tail cylinder 10 at its rear end.

  A pilot nozzle 3 communicating with the pilot cone 5 is disposed at the axial center position of the inner cylinder 2, and a main nozzle 4 communicating with a main burner 6 serving as a premixer is disposed around the pilot nozzle 3. It is installed. In addition, a pilot swirler 7 is disposed between the pilot cone 3 and the pilot cone 5 at the outer periphery near the tip of the pilot nozzle 3, and a main swirler 8 is disposed between the outer periphery near the tip of the main nozzle 4 and the main burner 6. It is installed. The combustor 1 is configured as described above.

  The main fuel supplied to the main nozzle 4 forms a premixed gas in the main burner 6. On the other hand, the pilot fuel supplied to the pilot nozzle 3 generates a pilot flame (diffusion flame) by the pilot nozzle 3. Then, the premixed gas is injected into the tail cylinder 10 and ignited by a pilot flame in the tail cylinder 10 to generate a premixed flame in the tail cylinder 10. A bypass elbow 9 protrudes from the outer peripheral surface of the transition piece 10 toward the casing, and air is introduced into the transition piece 10 from here. In addition, a bypass valve BV that can be opened and closed in order to adjust the amount of air introduced into the tail cylinder 10 is provided at the tip thereof.

  An outer cylinder 11 is provided around the inner cylinder 2 so as to concentrically surround it. An air flow path 12 is formed between the inner cylinder 2 and the outer cylinder 11 surrounding the inner cylinder 2, and a top hat fuel nozzle 20 is erected on the inner peripheral wall of the outer cylinder 11. Then, the fuel is mixed with the air (indicated by the white arrow α) supplied through the air flow path 12, and a sufficient distance to the combustion zone formed in the wake is ensured for uniform fuel mixing. I'm trying to get it.

  Specifically, the top hat fuel injected from the top hat fuel nozzle 20 is mixed with the air supplied through the air flow path 12, and then the turning vane 19 provided from the air flow path 12 to the inner cylinder 2. And make a U-turn along the pilot nozzle 3 side. Reference numeral 17 denotes a casing of the outer cylinder 11 protruding from the casing.

  On the other hand, the transition piece 10 communicates with the turbine 13 at its rear end. The high-temperature and high-pressure combustion gas generated in the combustor 1 is ejected from the tail cylinder 10 to the turbine 13 as indicated by an arrow β. The turbine 13 has a stationary blade 13a and a moving blade 13b. Combustion gas ejected from the tail cylinder 10 passes through the stationary blade 13a to become a predetermined flow, and is further blown to the moving blade 13b to drive it. The turbine 13 is rotated.

In addition, Patent Document 1 discloses a gas turbine combustor in which a high concentration of NOx generated in a pilot combustor in a premixed combustor is reduced without impairing its reliability. This is a premixed combustion type gas turbine combustor having a pilot combustor and a main combustor, wherein the pilot combustor is a premixed catalyst combustor.
JP-A-6-174233

  Conventionally, a combustor of a gas turbine has been required to be stable and have a low environmental load in a wide range from a partial load state to a 100% load state. However, in the conventional combustor as described above, lean premixed combustion is performed in order to reduce NOx during combustion in a high load zone, and this burns uniform and lean premixed gas, Under conditions where the combustion temperature is low, such as during partial load (especially during low load), there is a tendency for more unburned matter to be generated. In addition, CO, UHC (unburned hydrocarbon), smoke, etc. are mentioned as a kind of unburned part. In terms of market needs, the reduction of unburned fuel during such partial loads is also an important point.

  In view of such problems, the present invention reduces the unburned content at the time of partial load by applying a catalyst to a combustor or the like, improves combustion efficiency, and performs stable combustion and operation. An object is to provide a gas turbine that is made possible.

  In order to achieve the above object, the present invention has a pilot nozzle disposed at the axial center position of the inner cylinder and a plurality of main nozzles disposed around the pilot nozzle and provided with a premixer on the outer periphery. The fuel injected from the main nozzle into the tail cylinder that forms a combustion chamber downstream of the inner cylinder as a premixed gas is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder, In a gas turbine having a combustor configured to generate a premixed flame in the tail cylinder, a fuel layer for supplying fuel to the catalyst layer and the catalyst layer inside a bypass pipe for introducing air into the tail cylinder It is characterized by comprising.

  In addition, it has a pilot nozzle arranged at the axial center position of the inner cylinder, and a plurality of main nozzles arranged around the pilot nozzle and provided with a premixer on the outer periphery, and from the main nozzle as premixed gas The fuel injected into the tail cylinder that forms the combustion chamber downstream of the inner cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder to generate a premixed flame in the tail cylinder. In the gas turbine provided with the combustor, the inner wall surface of the tail cylinder is coated with a catalyst.

  In addition, it has a pilot nozzle arranged at the axial center position of the inner cylinder, and a plurality of main nozzles arranged around the pilot nozzle and provided with a premixer on the outer periphery, and from the main nozzle as premixed gas The fuel injected into the tail cylinder that forms the combustion chamber downstream of the inner cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder to generate a premixed flame in the tail cylinder. In the gas turbine provided with the combustor configured as described above, a catalyst layer is provided around the premixer, and a part of the top hat fuel is supplied to the catalyst layer. In addition, the top hat fuel is supplied to the catalyst layer and the flame stabilizer provided in the premixer and the pilot nozzle in separate systems.

  In addition, it has a pilot nozzle arranged at the axial center position of the inner cylinder, and a plurality of main nozzles arranged around the pilot nozzle and provided with a premixer on the outer periphery, and from the main nozzle as premixed gas The fuel injected into the tail cylinder that forms the combustion chamber downstream of the inner cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder to generate a premixed flame in the tail cylinder. In a gas turbine including a combustor configured to perform, a fuel nozzle that applies catalyst coating to an inner wall surface of a cooling passage provided in a wall portion of the tail tube, and supplies fuel to the tail tube at a compressor outlet The premixed gas in which the fuel from the fuel nozzle is mixed with the air from the compressor flows into the tail cylinder through the cooling passage. In addition, the wall of the tail tube is impingement cooled by the premixed gas.

  In addition, it has a pilot nozzle arranged at the axial center position of the inner cylinder, and a plurality of main nozzles arranged around the pilot nozzle and provided with a premixer on the outer periphery, and from the main nozzle as premixed gas The fuel injected into the tail cylinder that forms the combustion chamber downstream of the inner cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder to generate a premixed flame in the tail cylinder. A gas turbine having a combustor configured as described above is characterized in that a catalyst coating is applied to a region of a surface of a turbine stationary blade and / or turbine rotor blade through which cooling air ejected from the inside flows.

  In addition, it has a pilot nozzle arranged at the axial center position of the inner cylinder, and a plurality of main nozzles arranged around the pilot nozzle and provided with a premixer on the outer periphery, and from the main nozzle as premixed gas The fuel injected into the tail cylinder that forms the combustion chamber downstream of the inner cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder to generate a premixed flame in the tail cylinder. A gas turbine having a combustor configured as described above is characterized in that a catalyst coating is applied to the hub side and tip side surfaces of a turbine stationary blade and / or a turbine rotor blade. In addition, the catalyst coating on the hub side and the tip side may be applied to the center side of the blades toward the rear stage of the turbine.

  According to the present invention, by applying a catalyst to a combustor or the like, a gas turbine that can reduce the unburned portion at the time of partial load, improve the combustion efficiency, and perform stable combustion and operation. Can be provided.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the part which is common in the said prior art example, and detailed description is abbreviate | omitted suitably.

  1 is a longitudinal sectional view schematically showing a schematic configuration of a combustor in a gas turbine according to a first embodiment of the present invention. In the same figure, illustration of the inside of the inner cylinder 2 is omitted. In this embodiment, the catalyst layer and the fuel nozzle are provided inside the bypass elbow. Specifically, a catalyst layer 14 is arranged from the root of the bypass elbow 9 to the inner side of the tail cylinder 10 and further to the bypass elbow 9 between the bypass valve BV on the upstream side of the air flow. A fuel nozzle 15 is disposed.

  In this configuration, fuel is ejected from the bypass elbow fuel nozzle 15 during partial load, and lean fuel is burned through the catalyst layer 14. This combustion gas is ejected into the tail cylinder 10 as indicated by the black arrow γ. In this case, on the inner cylinder 2 side, combustion is performed with pilot fuel and main fuel as well as top hat fuel as usual, but a part of the main fuel is supplied from the bypass elbow fuel nozzle 15 on the bypass elbow 9 side. Become. Specifically, the amount of fuel flowing from the bypass elbow 9 side is approximately 50% or less of the distribution, that is, the amount of fuel flowing from the inner cylinder 2 side is determined to be 50% or more.

  According to the configuration of the present embodiment, catalytic combustion can be performed on the bypass elbow 9 side for some fuels even under conditions where the combustion temperature is low, such as during partial load (particularly during low load). It is possible to reduce the unburned content in the lean premixed gas. Further, there is an effect that the unburned portion in the combustion gas from the inner cylinder 2 side is combusted in the tail cylinder 10 using the flame caused by the combustion on the bypass elbow 9 side as a fire type. In the present embodiment, since there is no change in the structure on the inner cylinder 2 side, it does not affect the low NOx performance that has been established conventionally. Further, since the concentration of the premixed gas entering the catalyst layer 14 can be changed by both the fuel injection amount from the bypass elbow fuel nozzle 15 and the opening degree of the bypass valve BV, the adjustment range is large and advantageous.

  As the structure of the catalyst layer 14, for example, a honeycomb structure is generally used, which is mainly composed of, for example, palladium (Pd), platinum (Pt), or the like on a surface of oxidation resistant stainless steel or cordierite ceramic. A catalyst having a noble metal catalyst attached thereto is mainly used.

  FIG. 2 is a diagram schematically illustrating a schematic configuration of the combustor in the gas turbine according to the second embodiment of the present invention. The figure (a) is a longitudinal cross-sectional view, and the figure (b) is a cross-sectional view of the tail tube portion. In this embodiment, the catalyst coating 16 is applied to the inner wall surface of the transition piece 10 as shown in FIG. As a result, in the relatively low temperature portion near the inner wall surface of the transition piece 10, the fuel that has not been combusted in the past and has become unburned fuel is promoted by touching this catalyst. Can be reduced.

  Further, as shown in FIG. 5B, if a configuration is provided in which a large number of minute fins 10a projecting from the inner wall surface of the transition piece 10 are provided, and the catalyst coating 16 is applied to the surface, the fin is not provided. The reaction area of the catalyst increases, and the effect of reducing the unburned content increases. In addition, it is good also as a structure which provides a groove | channel in the inner wall face of the tail cylinder 10, and provides the catalyst coating 16 on the surface instead of providing the fin 10a. Further, the range of the inner wall surface of the tail cylinder 10 to which the catalyst coating 16 is applied may be the whole as shown in FIG. 5A, or may be a partial range such as a particularly low temperature range.

  FIG. 3 is a diagram schematically illustrating a schematic configuration of the combustor in the gas turbine according to the third embodiment of the present invention. The figure (a) is a longitudinal cross-sectional view, and the figure (b) is a cross-sectional view of an inner cylinder part. In addition, only the upper half is shown in the figure. In this embodiment, the substrate portion of the inner cylinder is used as the catalyst layer. Specifically, as shown in the figure, a catalyst layer 14 is provided in a region surrounded by the inner cylinder 2 and the pilot cone 5 around the main burner 6. However, the main burner 6 is not supported by the catalyst layer 14 but is supported by a support member (not shown). In the figure, the illustration of the turning vanes is omitted.

  Then, a part of the premixed gas of the fuel from the top hat fuel nozzle 20 and the air supplied through the air flow path 12 is supplied to the catalyst layer 14 as shown by an arrow a and reacted there. Further, fuel is also supplied from the pilot nozzle 3 and the main nozzle 4 as usual, but according to the configuration of the present embodiment, even when the main premixed gas ejected from the main burner 6 is thin as in partial load, Since the gas reacted in the catalyst layer 14 from the surroundings is ejected as shown by the arrow b, the main premixed gas becomes relatively easy to burn using this as a fire type, and the unburned portion can be reduced.

  However, as shown in FIG. 5B, for example, the inner side (B side in the figure) of the pitch circle (indicated by the alternate long and short dash line) of the main burner 6 becomes relatively high due to the influence of the pilot flame. There is little generation of fuel. Therefore, by disposing the catalyst layer 14 only outside the pitch circle (A side in the figure) (the illustration of this state is omitted), it is possible to reduce costs while maintaining the effect of reducing the unburned content to some extent. Furthermore, it is possible to avoid the risk of catalyst burning in a relatively high temperature portion.

  FIG. 4 is a diagram schematically illustrating a schematic configuration of the combustor in the gas turbine according to the fourth embodiment of the present invention. In the figure, only the upper half is shown. In this embodiment, as shown in the figure, the turning vane 19 is connected to the pilot cone 5 over the entire circumference, and the main burners 6 are arranged between the inner circumference of the turning vane 19 and the outer circumference of the pilot cone 5. The configuration is set up. In this case, each main burner 6 is connected to the bottom of the turning vane 19 and opens toward the upstream side of the air flow.

  In addition to the top hat fuel nozzle 20, a catalyst layer top hat fuel nozzle 21 standing on the inner peripheral wall of the outer cylinder 11 is provided, from which fuel is injected into the turning vane 19. As indicated by an arrow c, it flows into only the catalyst layer 14. On the other hand, the fuel from the top hat fuel nozzle 20 is injected to the outside of the turning vane 19 so that the premixed gas flows into the main burner 6 and the pilot cone 5 as indicated by an arrow a. That is, the top hat fuel is supplied to the catalyst layer 14, the main burner 6, and the pilot cone 5 by separate systems.

  With the configuration as described above, it is possible to control the amount of fuel that is catalytically burned in the catalyst layer 14 only by adjusting the fuel injected from the top hat fuel nozzle 21 for the catalyst layer. In addition, considering the pressure loss due to the catalyst layer 14, the size and shape of the turning vane 19 are appropriately set, and the amount of air flowing into the main burner 6 and the pilot cone 5 and the region where the catalyst layer 14 is provided. What is necessary is just to make it the same as the case where there is no catalyst layer like the past. Thereby, in the high load zone, the combustion performance equivalent to that of the conventional combustor can be obtained by shutting off the fuel from the top hat fuel nozzle 21 for the catalyst layer.

  In addition, the top hat fuel nozzle 20 may not be used but only the catalyst layer top hat fuel nozzle 21 may be used to make two systems, and fuel may be injected into the inside and outside of the turning vane 19 from here. In this case, the amount of fuel flowing into the catalyst layer 14 and the amount of fuel flowing into the main burner 6 and the pilot cone 5 are respectively controlled. As a result, it is possible to obtain the same effect as when the top hat fuel nozzle 20 is used while reducing the number of parts of the nozzle and reducing the cost.

  FIG. 5 is a longitudinal sectional view schematically showing a schematic configuration of a combustor and its peripheral portion in a gas turbine according to Embodiment 5 of the present invention. In this embodiment, a compressor outlet fuel nozzle 22 standing from the inner wall surface of the casing 17 is provided at the outlet of the compressor (not shown), and fuel is injected into the casing from here, and this premixed gas is indicated by an arrow d. As shown in the figure, the air flows into the transition piece 10 through the wall portion of the transition piece 10.

  At this time, the premixed gas flows into the tail tube 10 through a cooling passage (to be described later) provided in the wall of the tail tube 10 in the past, but in this embodiment, some of the cooling passages. A catalyst coating is applied to the inner wall surface, the premixed gas that has passed through the cooling passage is reacted with the catalyst, and the combustion gas is ejected into the tail cylinder 10. Thereby, the unburned part produced near the inner wall surface of the transition piece 10 can be reduced.

  6A and 6B are diagrams schematically showing the configuration of the cooling passage of the transition piece in the present embodiment, where FIG. 6A is a transverse sectional view and FIG. 6B is a longitudinal sectional view. As shown in the figure, inside the wall portion of the transition piece 10, a cooling passage 10a extending in the axial direction is provided in parallel, for example, over the entire circumference. A catalyst coating 16 is applied to the inner wall surface of a part of the cooling passages 10a.

  In this case, as shown in FIG. 5A, the cooling passage 10a may be alternately arranged with and without coating, or for example, one with several coatings. It is good also as such a structure. Thereby, since the cooling passage 10a without a coating can be provided with a cooling function, it is possible to prevent the wall portion of the tail tube 10 from becoming too high due to catalytic combustion.

  As shown in FIG. 5B, the premixed gas from the compressor enters through the cooling air inlet 10b opened in the outer peripheral surface of the tail cylinder 10 and passes through the cooling passage 10a as shown by the arrow d. The cooling air outlet 10c opened on the inner peripheral surface of the transition piece 10 is configured to flow into the transition piece 10. At this time, as shown in the figure, if the catalyst coating 16 is applied to the inner wall surface of the cooling passage 10a, the premixed gas passing therethrough reacts with the catalyst and burns. If the catalyst coating 16 is not applied, the premixed gas passing therethrough does not react and cools the wall of the tail tube 10.

  Further, by combining this embodiment with the first embodiment, more fuel can be catalytically combusted. In this case, in the configuration of the first embodiment shown in FIG. 1, only the catalyst layer 14 may be disposed in the bypass elbow 9, and the bypass elbow fuel nozzle 15 is unnecessary. Here, the premixed gas from the compressor that has flowed into the bypass elbow 9 reacts in the catalyst layer 14.

  Further, as shown in a cross-sectional view in FIG. 7, the transition piece 10 may be impingement cooled. Specifically, the outer side of the transition piece 10 is covered with a manifold 23, an impingement hole 23a is formed in the outer peripheral surface of the manifold 23, and the premixed gas from the compressor is passed through the impingement hole 23a in the manifold 23 as indicated by an arrow e. To introduce. The introduced premixed gas abuts the outer peripheral surface of the tail tube 10 and cools it (impingement cooling), then enters from the cooling air inlet 10b opened in the outer peripheral surface of the tail tube 10 and passes through the cooling passage 10a. It exits from the cooling air outlet 10 c opened on the inner peripheral surface of the transition piece 10 and flows into the transition piece 10.

  In this case, the wall of the transition piece 10 can be cooled by the impingement cooling, so that it is not necessary to perform cooling in the cooling passage 10a. Therefore, since the catalyst coating 16 can be applied to the inner wall surface of all the cooling passages 10a and catalytic combustion can be performed here, it is possible to further improve the combustion efficiency and reduce the unburned content.

  FIG. 8 is a longitudinal sectional view schematically showing a schematic configuration of a combustor and its peripheral portion in a gas turbine according to Embodiment 6 of the present invention. In this embodiment, the catalyst coating 16 is applied to the surfaces of the stationary blade 13a and the moving blade 13b of the turbine 13. Thereby, the unburned matter generated when the turbine inlet temperature is low is reacted inside the turbine 13 to improve the combustion efficiency at the turbine outlet.

  Specifically, for example, as shown in FIG. 5A, there is a method in which a catalyst coating 16 is applied to the entire surface of the stationary blade 13a and the moving blade 13b. However, in this case, there is a possibility that the catalyst is deteriorated and damaged particularly in a portion exposed to high-temperature combustion gas. Therefore, although not shown in the figure, if the catalyst coating 16 is concentrated on the surface area of each blade where the cooling air ejected from the inside flows, this area is cooled by the cooling air, so that the catalyst deteriorates. , No damage.

  Further, as shown in FIG. 5B, a catalyst coating 16 may be applied to the blade surfaces on the hub side (turbine rotating shaft side) and the tip side (turbine outer peripheral side) where the combustion gas temperature is relatively low. Further, as shown in FIG. 5C, the catalyst coatings 16 on the hub side and tip side of each blade are applied to the center side of the blades toward the rear stage of the turbine where the combustion gas temperature decreases. It is also good. With such a configuration, deterioration and damage of the catalyst can be prevented in advance, durability can be improved, and cost can be reduced by eliminating waste of the catalyst.

  In addition, if the catalyst coating 16 is applied to the entire surface of only the blades at the rear stage of the turbine where the combustion gas temperature is low, the catalyst can be easily applied. In addition, when the gas turbine is initially operated, the entire surface of each blade is coated with the catalyst coating 16, and after operating for a while, only a portion where the deterioration and damage of the catalyst are relatively small is repaired. From this operation, the catalyst can be used effectively without waste. In the above-described configuration of the present embodiment, the catalyst coating 16 may be applied to either the stationary blade 13a or the moving blade 13b.

  Note that the bypass pipe in the claims corresponds to the bypass elbow in the embodiment, and the flame holder corresponds to the pilot cone.

1 is a longitudinal sectional view schematically showing a schematic configuration of a combustor in a gas turbine of Example 1. FIG. The figure which shows typically schematic structure of the combustor in the gas turbine of Example 2. FIG. The figure which shows typically schematic structure of the combustor in the gas turbine of Example 3. FIG. The figure which shows typically schematic structure of the combustor in the gas turbine of Example 4. FIG. FIG. 6 is a longitudinal sectional view schematically showing a schematic configuration of a combustor and its peripheral portion in a gas turbine of Example 5. The figure which shows typically the structure of the cooling channel | path of a transition piece. The cross-sectional view which shows the structure which impingement cools a tail cylinder. The longitudinal cross-sectional view which shows typically schematic structure of the combustor in the gas turbine of Example 6, and its peripheral part. The longitudinal cross-sectional view which shows typically schematic structure of the combustor in the conventional gas turbine, and its peripheral part.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Combustor 2 Inner cylinder 3 Pilot nozzle 4 Main nozzle 5 Pilot cone 6 Main burner 7 Pilot swirler 8 Main swirler 9 Bypass elbow 10 Outer cylinder 11 Outer cylinder 12 Air flow path 13 Turbine 14 Catalyst layer 15 Bypass elbow fuel nozzle 16 Catalyst coating 17 Cabin casing 19 Turning vane 20 Top hat fuel nozzle 21 Top hat fuel nozzle for catalyst layer 22 Compressor outlet fuel nozzle 23 Manifold BV bypass valve

Claims (9)

A pilot nozzle disposed at an axial center position of the inner cylinder, and a plurality of main nozzles disposed around the pilot nozzle and provided with a premixer on the outer periphery, and the inner nozzle serves as a premixed gas from the main nozzle. The fuel injected into the tail cylinder that forms the combustion chamber downstream of the cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder, so that a premixed flame is generated in the tail cylinder. In a gas turbine equipped with a combustor,
A gas turbine comprising a catalyst layer and a fuel nozzle for supplying fuel to the catalyst layer inside a bypass pipe for introducing air into the transition piece. A pilot nozzle disposed at an axial center position of the inner cylinder, and a plurality of main nozzles disposed around the pilot nozzle and provided with a premixer on the outer periphery, and the inner nozzle serves as a premixed gas from the main nozzle. The fuel injected into the tail cylinder that forms the combustion chamber downstream of the cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder, so that a premixed flame is generated in the tail cylinder. In a gas turbine equipped with a combustor,
A gas turbine, wherein a catalyst coating is applied to an inner wall surface of the tail cylinder. A pilot nozzle disposed at an axial center position of the inner cylinder, and a plurality of main nozzles disposed around the pilot nozzle and provided with a premixer on the outer periphery, and the inner nozzle serves as a premixed gas from the main nozzle. The fuel injected into the tail cylinder that forms the combustion chamber downstream of the cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder, so that a premixed flame is generated in the tail cylinder. In a gas turbine equipped with a combustor,
A gas turbine, wherein a catalyst layer is provided around the premixer, and a part of the top hat fuel is supplied to the catalyst layer.   The top hat fuel is supplied to the catalyst layer and the flame holder provided in the premixer and the pilot nozzle in different systems, respectively. gas turbine. A pilot nozzle disposed at an axial center position of the inner cylinder, and a plurality of main nozzles disposed around the pilot nozzle and provided with a premixer on the outer periphery, and the inner nozzle serves as a premixed gas from the main nozzle. The fuel injected into the tail cylinder that forms the combustion chamber downstream of the cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder, so that a premixed flame is generated in the tail cylinder. In a gas turbine equipped with a combustor,
A catalyst coating is applied to the inner wall surface of the cooling passage provided in the wall portion of the transition piece, a fuel nozzle for supplying fuel to the transition piece is provided at the outlet of the compressor, and the fuel nozzle is supplied to the air from the compressor. A gas turbine characterized in that the premixed gas mixed with the fuel from the gas flows into the tail tube through the cooling passage.   The gas turbine according to claim 5, wherein impingement cooling is performed on the wall portion of the transition piece by the premixed gas. A pilot nozzle disposed at an axial center position of the inner cylinder, and a plurality of main nozzles disposed around the pilot nozzle and provided with a premixer on the outer periphery, and the inner nozzle serves as a premixed gas from the main nozzle. The fuel injected into the tail cylinder that forms the combustion chamber downstream of the cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder, so that a premixed flame is generated in the tail cylinder. In a gas turbine equipped with a combustor,
A gas turbine characterized in that in a turbine stationary blade and / or a turbine blade, a catalyst coating is applied to a surface region through which cooling air ejected from the inside flows. A pilot nozzle disposed at an axial center position of the inner cylinder, and a plurality of main nozzles disposed around the pilot nozzle and provided with a premixer on the outer periphery, and the inner nozzle serves as a premixed gas from the main nozzle. The fuel injected into the tail cylinder that forms the combustion chamber downstream of the cylinder is ignited by the diffusion flame generated by the pilot nozzle in the tail cylinder, so that a premixed flame is generated in the tail cylinder. In a gas turbine equipped with a combustor,
A gas turbine characterized in that a catalyst coating is applied to the hub side and tip side surfaces of a turbine stationary blade and / or a turbine rotor blade.   The gas turbine according to claim 8, wherein the catalyst coating on the hub side and the tip side is applied so as to extend toward the center side of the blades toward the rear stage of the turbine.

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