JP5653774B2 - Gas turbine combustor - Google Patents

Description

  The present invention relates to a gas turbine combustor.

  In order to reduce the NOx in the gas turbine combustor, it is important not to generate a local high fuel concentration by controlling the fuel distribution, and it is necessary to make the fuel concentration uniform. For this purpose, it is important to increase the amount of main air through which most of the fuel passes and to make it uniform.

  Conventionally, a combustor that turns mainstream air from a passenger compartment 180 degrees to guide mainstream air to a main premixing nozzle has been disclosed (see, for example, Patent Document 1). In such a combustor, a punch metal (rectifier plate) is provided at the outlet portion of the compressed air flow path formed between the outer cylinder and the inner cylinder in order to eliminate the uneven distribution of the flow due to flow separation or the like. The flow in the combustion region and the fuel concentration are made uniform by taking a sufficiently long rectification distance from the combustion mixing point to the 180 degree turning point.

JP 2000-346361 A

  However, in recent years, there has been a demand for a gas turbine combustor that is smaller and lighter and has a lower manufacturing cost. Therefore, in the conventional configuration (that is, punch metal in which holes having the same hole diameter are uniformly provided in the circumferential direction and the radial direction), the rectification distance from the combustion mixing point to the 180 degree turning point is sufficiently large. Can't take long. In addition, the combustion air is inverted at the 180 ° turning point and tends to concentrate on the axial center side of the gas turbine combustor, so that the flow in the combustion region and the fuel concentration become non-uniform and NOx may increase. .

  The present invention has been made in view of such circumstances, and provides a gas turbine combustor that can be reduced in size, weight, and manufacturing cost without increasing NOx. Objective.

The present invention employs the following means in order to solve the above problems.
Gas turbine combustor according to the present invention includes an outer cylinder, an inner cylinder provided inside of the outer cylinder, and a plurality of fuel nozzles which are arranged along the inner peripheral surface of the inner cylinder in the circumferential direction, Compressed air flowing through the compressed air flow path is a gas turbine combustor that is introduced into the plurality of fuel nozzles with a flow direction substantially reversed at an end of the inner cylinder, and is disposed on an inner peripheral surface of the outer cylinder. Between the plurality of fuel nozzles, a plurality of top hat nozzles provided in the compressed air flow path along a circumferential direction, and an inlet portion of the inner cylinder through which compressed air substantially inverted at the end of the inner cylinder flows. and a so provided are current plate so as to block the space formed, the rectifying plate has a number of holes provided for penetrations in the thickness direction of the current plate, the opening of the plurality of holes rate is radially outwardly from the radially inner side of the current plate to increase gradually .

According to the gas turbine combustor according to the present invention, the opening ratio of the radially inner side of the inner cylinder to the radially outer side with respect to the compressed air that is inverted at the turning point of 180 degrees and tends to concentrate on the axial center side of the gas turbine combustor. A large number of holes are provided in the current plate so as to reduce the current.
As a result, even when the commutation distance from the combustion mixing point to the 180 degree turning point is not sufficient as in the conventional case, the flow in the combustion region and the fuel concentration can be made uniform, and NOx is increased. Therefore, it is possible to reduce the size and weight and reduce the manufacturing cost.

  In the gas turbine combustor, the plurality of holes provided in the current plate have the same inner diameter, and the number of the holes extends from the radially inner side to the radially outer side of the current plate. It is more preferable that they are arranged so as to gradually increase.

According to such a gas turbine combustor, the number of holes located on the radially inner side of the inner cylinder is small with respect to compressed air that is inverted at the 180 ° turning position and tends to concentrate on the axial center side of the gas turbine combustor. Thus, a large number of holes are provided in the current plate.
As a result, even when the commutation distance from the combustion mixing point to the 180 degree turning point is not sufficient as in the conventional case, the flow in the combustion region and the fuel concentration can be made uniform, and NOx is increased. Therefore, it is possible to reduce the size and weight and reduce the manufacturing cost.

  In the gas turbine combustor, the plurality of holes provided in the rectifying plate are arranged such that the hole diameter gradually increases from the radially inner side to the radially outer side of the rectifying plate. Further preferred.

According to such a gas turbine combustor, the hole diameter of the hole located on the inner side in the radial direction of the inner cylinder is small with respect to the compressed air which is inverted at the turning point of 180 degrees and tends to concentrate on the axial center side of the gas turbine combustor. Thus, a large number of holes are provided in the current plate.
As a result, even when the commutation distance from the combustion mixing point to the 180 degree turning point is not sufficient as in the conventional case, the flow in the combustion region and the fuel concentration can be made uniform, and NOx is increased. Therefore, it is possible to reduce the size and weight and reduce the manufacturing cost.

  In the gas turbine combustor, a plurality of the fuel nozzles are installed at an axial center of the gas turbine combustor to perform diffusion combustion, and a plurality of fuel nozzles are installed at intervals in the circumferential direction on the outer peripheral side of the pilot nozzle. A main nozzle that performs premixed combustion is more preferable.

According to such a gas turbine combustor, a large number of holes are provided in the rectifying plate so that the gas turbine combustor does not concentrate on the pilot nozzle on the axial center side of the gas turbine combustor by being inverted at the 180 ° turning point.
As a result, even when the commutation distance from the combustion mixing point to the 180 degree turning point is not sufficient as in the conventional case, the flow in the combustion region and the fuel concentration can be made uniform, and NOx is increased. Therefore, it is possible to reduce the size and weight and reduce the manufacturing cost.

  In the gas turbine combustor, the rectifying plates are individually provided for the plurality of fuel nozzles, and the center of the through hole through which the fuel nozzle is inserted is substantially the axis of the fuel nozzle to be inserted. More preferably, they are concentric.

  According to such a gas turbine combustor, the flow in the combustion region and the fuel concentration can be made uniform, and the size and weight can be reduced and the manufacturing cost can be reduced without increasing NOx. it can.

  A gas turbine according to the present invention includes any one of the above gas turbine combustors.

  The gas turbine according to the present invention includes the gas turbine combustor that can be reduced in size and weight and reduced in manufacturing cost without increasing NOx. The weight can be reduced and the manufacturing cost can be reduced.

  According to the gas turbine combustor according to the present invention, it is possible to reduce the size and weight and to reduce the manufacturing cost without increasing NOx.

It is a schematic block diagram of the gas turbine provided with the gas turbine combustor which concerns on this invention. It is a schematic block diagram of the gas turbine combustor which concerns on this invention. It is principal part sectional drawing of the gas turbine combustor which concerns on 1st Embodiment of this invention. It is the front view which looked at the baffle plate shown in FIG. 3 from the lower right in FIG. It is a front view of the baffle plate applied to the gas turbine combustor which concerns on 2nd Embodiment of this invention. It is a front view of the baffle plate applied to another gas turbine combustor. It is a front view of the baffle plate applied to another gas turbine combustor.

[First Embodiment]
Hereinafter, a gas turbine combustor according to a first embodiment of the present invention will be described with reference to FIGS. 1 to 4.
FIG. 1 is a schematic configuration diagram of a gas turbine equipped with a gas turbine combustor according to the present invention, FIG. 2 is a schematic configuration diagram of a gas turbine combustor according to the present invention, and FIG. 3 is a diagram of the gas turbine combustor according to the present embodiment. 4 is a front view of the current plate shown in FIG. 3 as viewed from the lower right in FIG.

As shown in FIG. 1, the gas turbine 10 according to the present embodiment includes a compressor 11, a gas turbine combustor 12, a turbine 13, and an exhaust chamber 14. The machine is connected.
The compressor 11 has an air intake port 15 for taking in air, and a plurality of stationary blades 17 and moving blades 18 are alternately arranged in a compressor casing 16, and an extraction manifold 19 is provided on the outside thereof. ing.

The gas turbine combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it with a burner.
In the turbine 13, a plurality of stationary blades 21 and moving blades 22 are alternately arranged in a turbine casing 20.
The exhaust chamber 14 has an exhaust diffuser 23 that is continuous with the turbine 13. In addition, a rotor (turbine shaft) 24 is positioned so as to penetrate through the center of the compressor 11, the gas turbine combustor 12, the turbine 13, and the exhaust chamber 14, and the end on the compressor 11 side is supported by a bearing portion 25. The end portion on the exhaust chamber 14 side is rotatably supported by a bearing portion 26 while being rotatably supported. A plurality of disk plates are fixed to the rotor 24, and the rotor blades 18 and 22 are connected to the disk plates, and an end of the rotor 24 on the side of the air intake 15 is connected to a generator (not shown). The drive shaft is connected.

  In the gas turbine 10 configured as described above, the air taken in from the air intake port 15 of the compressor 11 is compressed by passing through the plurality of stationary blades 17 and the moving blades 18 to compress at a high temperature and high pressure. It becomes air and is combusted by supplying a predetermined fuel to the compressed air in the gas turbine combustor 12. The high-temperature and high-pressure combustion gas that is the working fluid generated by the gas turbine combustor 12 passes through the plurality of stationary blades 21 and the moving blades 22 constituting the turbine 13 to drive and rotate the rotor 24. While the generator connected to the rotor 24 is driven, the exhaust gas is converted into static pressure by the exhaust diffuser 23 in the exhaust chamber 14 and then released to the atmosphere.

  As shown in FIG. 2, in the gas turbine combustor 12, a combustor inner cylinder 32 is supported inside a combustor outer cylinder 31 at a predetermined interval, and a combustor tail is disposed at the tip of the combustor inner cylinder 32. The cylinder 33 is connected to form a combustor casing. In the combustor inner cylinder 32, a pilot nozzle (fuel nozzle) 34 is disposed at the center thereof, and a plurality of pilot nozzles 34 are surrounded on the inner peripheral surface of the combustor inner cylinder 32 along the circumferential direction. The main nozzle (premixing nozzle: fuel nozzle) 35 is disposed, and a pilot cone 36 is attached to the tip of the pilot nozzle 34. A plurality of top hat nozzles 37 are arranged on the inner peripheral surface of the combustor outer cylinder 31 along the circumferential direction.

  If it demonstrates in detail using FIG. 3, the combustor outer cylinder 31 will be comprised by the outer cylinder cover part 42 closely_contact | adhering to the base end part of the outer cylinder main body 41, and being fastened by the some fastening bolt 43, This A base end portion of the combustor inner cylinder 32 is fitted to the outer cylinder lid portion 42, and a compressed air flow path 44 is formed between the outer cylinder lid portion 42 and the combustor inner cylinder 32. A pilot nozzle 34 is disposed at the center of the combustor inner cylinder 32, and a plurality of main nozzles 35 are disposed so as to surround the pilot nozzle 34. Communicates with the main burner 45.

  A top hat portion 47 is fitted into the outer cylinder lid portion 42 and fastened by a plurality of fastening bolts 48, and the top hat nozzle 37 described above is provided in the top hat portion 47. That is, a fuel cavity 49 is formed in the base end portion of the top hat portion 47 along the circumferential direction, and a plurality of fuel passages 50 are formed from the fuel cavity 49 toward the distal end side. A peg 52 is connected to the tip.

  A pilot fuel line (not shown) is connected to the fuel port 53 of the pilot nozzle 34, the main fuel line is connected to the fuel port 54 of the main nozzle 35, and the top hat fuel line is connected to the fuel port 55 of the top hat nozzle 37. Yes.

  In the gas turbine combustor 12 configured in this way, as shown in FIGS. 2 and 3, when the air flow of the high-temperature and high-pressure compressed air flows into the compressed air flow path 44, the compressed air is at the top. It is mixed with the fuel injected from the hat nozzle 37, and this fuel mixture flows into the combustor inner cylinder 32. In the combustor inner cylinder 32, the fuel mixture is mixed with the fuel injected from the main nozzle 35 by the main burner 45, and flows into the combustor tail cylinder 33 as a swirling flow of the premixed gas. Further, the fuel mixture is mixed with fuel injected from the pilot nozzle 34, ignited and burned by a not-shown type fire, and is burned into the combustor tail cylinder 33 as combustion gas. At this time, a part of the combustion gas is ejected so as to diffuse into the combustor tail cylinder 33 with a flame so that the premixed gas flowing into the combustor tail cylinder 33 from each main nozzle 35 is ignited. Burned. That is, flame holding for stable combustion of the lean premixed fuel from the main nozzle 35 can be performed by the diffusion flame by the pilot fuel injected from the pilot nozzle 34.

As shown in FIG. 3, a rectifying plate (perforated plate) 61 is provided at the inlet of the combustor inner cylinder 32.
As shown in FIG. 4, the current plate 61 is a plate-like member that has a circular shape when viewed from the front (from the back).
A central portion of the rectifying plate 61 has a circular shape when viewed from the front (rear view), and is provided with one first through hole 62 that penetrates in the plate thickness direction and through which the pilot nozzle 34 is inserted. The inner peripheral surface 63 of the through hole 62 is matched (contacted) with the outer peripheral surface of the pilot nozzle 34, that is, the inner diameter of the inner peripheral surface 63 is the same as the outer diameter of the outer peripheral surface of the pilot nozzle 34. It is formed in this way.

  In addition, a second through hole 64 that has a circular shape in front view (rear view) around the through hole 62 and that penetrates in the plate thickness direction and through which the main nozzle 35 is inserted is provided along the circumferential direction. A plurality (eight in this embodiment) are provided with a (constant) interval (in this embodiment, every 45 degrees). The inner peripheral surface 65 of the through hole 64 is matched with (is in contact with) the outer peripheral surface of the main nozzle 35, that is, the inner diameter of the inner peripheral surface 65 is the same as the outer diameter of the outer peripheral surface of the main nozzle 35. It is formed in this way.

  The rectifying plate 61 is provided with a large number of holes 66 penetrating in the plate thickness direction along the circumferential direction and the radial direction. These holes 66 all have the same inner diameter (hole diameter), and the number (density) of the holes 66 rectifies from the radially inner side to the radially outer side of the rectifying plate 61, that is, from the inner peripheral surface 63 of the through hole 62. It is provided so as to gradually increase toward the outer peripheral surface 67 of the plate 61 (from sparse to dense). That is, the aperture ratio of the through hole 62 (ratio of the area of the through hole to the area of the current plate) gradually increases from the inner peripheral surface 63 toward the outer peripheral surface 67.

According to the gas turbine combustor 12 according to the present embodiment, the compressed air is easily concentrated on the pilot nozzle side that is inverted at the 180-degree turning point and is located on the axial center side of the gas turbine combustor 12, that is, the center of the inner cylinder. On the other hand, a large number of holes 66 are provided in the rectifying plate 61 so that the number of holes 66 located on the radially inner side of the inner cylinder is reduced.
As a result, even when the commutation distance from the combustion mixing point to the 180 degree turning point is not sufficient as in the conventional case, the flow in the combustion region and the fuel concentration can be made uniform, and NOx is increased. Therefore, it is possible to reduce the size and weight and reduce the manufacturing cost.

  The gas turbine 10 including the gas turbine combustor 12 according to the present embodiment includes the gas turbine combustor that can be reduced in size, weight, and manufacturing cost without increasing NOx. Therefore, the gas turbine can be reduced in size and weight, and the manufacturing cost can be reduced.

[Second Embodiment]
A gas turbine combustor according to a second embodiment of the present invention will be described with reference to FIG. FIG. 5 is a front view of a current plate applied to the gas turbine combustor according to the present embodiment.
The gas turbine combustor according to the present embodiment is different from that of the first embodiment described above in that a rectifying plate 71 is provided instead of the rectifying plate 61. Since other components are the same as those of the first embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above.

  As shown in FIG. 5, the rectifying plate 71 is provided with a large number of holes 76 penetrating in the plate thickness direction along the circumferential direction and the radial direction. The inner diameters (hole diameters) of these holes 76 gradually increase from the radially inner side to the radially outer side of the rectifying plate 61, that is, from the inner peripheral surface 63 of the through hole 62 toward the outer peripheral surface 67 of the rectifying plate 71. The number (density) gradually increases from the radially inner side of the rectifying plate 71 toward the radially outer side, that is, from the inner peripheral surface 63 of the through hole 62 toward the outer peripheral surface 67 of the rectifying plate 61 ( (From sparse to dense). That is, the aperture ratio of the through hole 62 gradually increases from the inner peripheral surface 63 toward the outer peripheral surface 67.

According to the gas turbine combustor according to the present embodiment, with respect to the compressed air that is easily concentrated on the pilot turbine side positioned at the axial center side of the gas turbine combustor, that is, at the center of the inner cylinder, by being inverted at the 180 degree turning point. A large number of holes 76 are provided in the rectifying plate 71 so that the hole diameter of the hole 76 located on the radially inner side of the inner cylinder is reduced.
As a result, even when the commutation distance from the combustion mixing point to the 180 degree turning point is not sufficient as in the conventional case, the flow in the combustion region and the fuel concentration can be made uniform, and NOx is increased. Therefore, it is possible to reduce the size and weight and reduce the manufacturing cost.

  The gas turbine 10 including the gas turbine combustor 12 according to the present embodiment includes the gas turbine combustor that can be reduced in size, weight, and manufacturing cost without increasing NOx. Therefore, the gas turbine can be reduced in size and weight, and the manufacturing cost can be reduced.

Note that the present invention is not limited to the above-described embodiment, and can be modified and changed as necessary.
For example, when the technical idea according to the first embodiment described above is applied to the gas turbine combustor disclosed in Japanese Patent Application Laid-Open Nos. 2010-181142 and 2009-139084, FIG. When the rectifying plate 81 is used and the technical idea according to the second embodiment described above is applied to the gas turbine combustor disclosed in Japanese Unexamined Patent Application Publication Nos. 2010-181142 and 2009-139084. 7, the current plate 91 shown in FIG. 7 is used.
Reference numeral 82 in FIG. 6 and reference numeral 92 in FIG. 7 are through holes through which fuel nozzles (not shown) are inserted.
The rectifying plates 81 and 91 have through holes 82 and 92 individually provided for a plurality of fuel nozzles (five in FIG. 6 and FIG. 7), and the center of each through hole 82 and 92 is provided. Is substantially concentric with the axis of the fuel nozzle to be inserted.

10 Gas turbine 12 Gas turbine combustor 32 Combustor inner cylinder (inner cylinder)
34 Pilot nozzle (fuel nozzle)
35 Main nozzle (fuel nozzle)
42 Outer cylinder lid (outer cylinder)
44 Compressed air passage 61 Rectifier plate 66 Hole 71 Rectifier plate 76 Hole 81 Rectifier plate 91 Rectifier plate

Claims (5)

An outer cylinder,
An inner cylinder provided inside the outer cylinder;
A compressed air flow path formed between the outer cylinder and the inner cylinder;
A plurality of fuel nozzles arranged in the circumferential direction along the inner peripheral surface of the inner cylinder,
The compressed air flowing through the compressed air flow path is a gas turbine combustor that is introduced into the plurality of fuel nozzles with a flow direction substantially reversed at an end of the inner cylinder,
A plurality of top hat nozzles provided in the compressed air flow path along the circumferential direction on the inner peripheral surface of the outer cylinder;
A rectifying plate provided at an inlet portion of the inner cylinder through which compressed air substantially inverted at an end portion of the inner cylinder flows is provided so as to block a space formed between the plurality of fuel nozzles;
The rectifying plate is provided with a number of holes penetrating in the thickness direction of the rectifying plate,
The multiple holes are arranged such that the number thereof gradually increases from the radially inner side to the radially outer side of the current plate,
The gas turbine combustor according to claim 1, wherein the aperture ratio of the plurality of holes gradually increases from the radially inner side to the radially outer side of the rectifying plate.   Gas turbine combustion characterized in that a number of holes provided in the rectifying plate are arranged so that the hole diameter gradually increases from the radially inner side to the radially outer side of the rectifying plate. The gas turbine combustor of claim 1, wherein the gas turbine combustor is characterized by The plurality of fuel nozzles are:
A pilot nozzle installed at the axial center of the gas turbine combustor to perform diffusion combustion;
3. The gas turbine combustor according to claim 1, wherein a plurality of the nozzles are installed on the outer peripheral side of the pilot nozzle at intervals in the circumferential direction and are premixed combustion main nozzles. 4. The rectifying plate is individually provided for the plurality of fuel nozzles, and the center of the through hole through which the fuel nozzle is inserted is substantially concentric with the axis of the fuel nozzle to be inserted. The gas turbine combustor according to any one of claims 1 to 3 , wherein the gas turbine combustor is characterized by the following. A gas turbine comprising the gas turbine combustor according to any one of claims 1 to 4 .

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