JP2015083897A - Combustor and rotary machine - Google Patents

Combustor and rotary machine Download PDF

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JP2015083897A
JP2015083897A JP2013222243A JP2013222243A JP2015083897A JP 2015083897 A JP2015083897 A JP 2015083897A JP 2013222243 A JP2013222243 A JP 2013222243A JP 2013222243 A JP2013222243 A JP 2013222243A JP 2015083897 A JP2015083897 A JP 2015083897A
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Japan
Prior art keywords
fuel
cavity
pair
fuel supply
circumferential direction
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JP2013222243A
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JP6116464B2 (en
Inventor
慎介 田尻
Shinsuke Tajiri
慎介 田尻
敏彦 齋藤
Toshihiko Saito
敏彦 齋藤
厚志 湯浅
Atsushi Yuasa
厚志 湯浅
耀華 薛
Yoka Setsu
耀華 薛
赤松 真児
Shinji Akamatsu
真児 赤松
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三菱日立パワーシステムズ株式会社
Mitsubishi Hitachi Power Systems Ltd
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Abstract

PROBLEM TO BE SOLVED: To reduce residence areas formed within cavities when a fuel is introduced into the cavities.SOLUTION: A combustor includes: a plurality of fuel supply passages 28 extending along an axis at intervals in a circumferential direction of the axis; cavities 43 that are connected to the fuel supply passages 28, to which a fuel flowing in the fuel supply passages 28 is introduced, and that extend in the circumferential direction; and a plurality of fuel injection passages 31 provided at intervals in the circumferential direction so as to be each connected to one axial side of one cavity 43, and injecting the fuel to an outside of the cavity 43, a guide portion 52 being formed in each cavity 43 for guiding the fuel introduced from one fuel supply passage 28 to one fuel injection passage 31.

Description

  The present invention relates to a combustor and a rotary machine including the combustor.

  As a combustor used in a gas turbine, a dual-fired combustor that can be switched to oil fuel that is liquid fuel is known together with gas fuel. As this type of combustor, there is known a combustor in which a combustion air flow path is separated from an inner flow path and an outer flow path by a cylindrical separation ring. A fuel supply passage for allowing the gas fuel and the oil fuel to flow is formed inside the separation ring. In particular, the oil fuel is injected from a plurality of fuel ejection passages formed in the circumferential direction at the downstream end portion in the axial direction. It has a configuration (for example, see Patent Document 1).

JP 2011-226772 A

  By the way, since oil fuel is heated and caulked (deterioration and carbonization due to heating of oil), the viscosity of the fuel supply path may increase and clogging may occur. As a result, the flow rate of the oil fuel may be excessive.

  Further, as shown in FIG. 15, a cavity 143 is formed between the fuel supply passage 28 formed inside the separation ring 127 and the fuel ejection passage formed at the downstream end portion in the axial direction X of the separation ring 127. A method of providing and equalizing the oil fuel is also known. However, there is a possibility that the residence region E having a low flow rate is formed in the cavity 143, and the oil fuel is heated.

  The present invention provides a combustor in which a stay region formed in a cavity is difficult to be formed when fuel is introduced into the cavity.

  According to the first aspect of the present invention, the combustor is connected to the plurality of fuel supply paths extending along the axis at intervals in the circumferential direction of the axis, and connected to the plurality of fuel supply paths, The fuel flowing through the fuel supply path is introduced and a circumferentially extending cavity is provided, and a plurality of circumferentially spaced cavities are provided and connected to one side in the axial direction of the cavity. A fuel ejection path for ejecting fuel, and a guide portion is formed in the cavity for guiding the fuel introduced from the fuel supply path to the fuel ejection path.

  According to the above configuration, since the guide portion is provided, it is difficult to form a staying area formed in the cavity when the fuel is introduced into the cavity. By reducing the residence area where the flow rate is low, heating of the oil fuel is reduced, and alteration and carbonization due to heating of the oil can be reduced.

  At least a pair of the fuel ejection paths are provided with respect to the fuel supply path, and one and the other of the pair of fuel ejection paths are arranged in a circumferential direction from each of the fuel supply paths as viewed from the direction along the axis. It is good also as a structure arrange | positioned so that an equal interval may be formed in the opposite direction.

  According to the above configuration, at least a pair of fuel ejection paths are provided at symmetrical positions with respect to the fuel supply path, so that fuel can be introduced into the plurality of fuel ejection paths in a balanced manner.

  The cavity may be formed independently for each of the at least one pair of fuel ejection paths.

  The guide portion may be configured to guide the fuel introduced from the fuel supply path to one and the other of the at least one pair of fuel ejection paths.

  The guide portion may be provided between the pair of fuel ejection paths, and may be a pair of guide surfaces that branch the fuel into one of the circumferential direction and the other of the circumferential direction.

  The guide portions may be formed as a pair of guide surfaces formed at both ends in the circumferential direction of the cavity and formed so as to gradually increase the circumferential width of the cavity toward one side in the axial direction.

  According to the above configuration, the fuel introduced into the cavity from the fuel supply path is introduced into the fuel ejection path by the pair of guide surfaces without being excessively spread in the width direction. That is, it becomes difficult to form a stay area on both sides in the width direction of the cavity, and the heating of the fuel can be reduced.

  The fuel ejection path may be connected to both end faces in the circumferential direction of the cavity, and the guide portion may be the both end faces.

  According to the above configuration, the fuel introduced into the cavity from the fuel supply path is guided to both end surfaces functioning as a guide portion, so that it is difficult to form a staying area in the cavity, and oil fuel is less heated.

  A pair of inner fuel ejection passages for injecting the fuel radially inward and a pair of outer fuel ejection passages for injecting the fuel radially outward; And it is good also as a structure in which a pair of radial direction guide surface branched to a radial direction outer side is formed.

  According to the said structure, the residence which generate | occur | produces when the oil fuel introduced from a fuel supply path contact | abuts both end surfaces can be suppressed.

Both end surfaces in the circumferential direction of the cavity may have an arc shape when viewed from the direction along the axis.
According to the said structure, the stay and stagnation which generate | occur | produce when a both end surface is not made into circular arc shape can be suppressed.

  A pair of inner fuel ejection paths for injecting the fuel radially inward; and a pair of outer fuel ejection paths for injecting the fuel radially outward, wherein the cavity gradually increases toward one axial side. A pair of radially opposed surfaces having a reduced radial distance; and the guide portions are the pair of radially opposed surfaces, and the two pairs of fuel ejection paths are the pair of radially opposed surfaces. It is good also as a structure connected to each axial direction one side edge part.

  According to the above configuration, the fuel is guided by the radially opposed surfaces, so that the staying area formed in the cavity is less likely to be formed as compared with the case where the downstream end of the cavity has a planar shape.

  The combustor includes a cylindrical separation ring main body, a pipe-shaped fuel supply pipe penetrating the inside of the separation ring main body along the axis, and the inside serving as the fuel supply path, and an axis of the separation ring main body A ring manifold which is disposed at one end in the direction and forms the cavity therein, and at least one of between the fuel supply pipe and the separation ring body and between the ring manifold and the separation ring body It is preferable that a space is provided.

  According to the said structure, since space functions as a heat insulation layer, it can reduce that oil fuel is heated.

  Moreover, this invention provides a rotary machine provided with one of the said combustors.

  According to the present invention, since the guide portion is provided, it is difficult to form a stay region formed in the cavity when the fuel is introduced into the cavity. By reducing the residence area where the flow rate is low, heating of the oil fuel is reduced, and alteration and carbonization due to heating of the oil can be reduced.

It is the schematic of the gas turbine of 1st embodiment of this invention. It is a schematic sectional drawing of the combustor of 1st embodiment of this invention. It is a disassembled perspective view of the separation ring of 1st embodiment of this invention. It is a partially enlarged view of the exploded perspective view of the separation ring of the first embodiment of the present invention. It is a partial sectional view seen from the peripheral direction of the separation ring of the first embodiment of the present invention. It is sectional drawing seen from the radial direction of the separation ring of 1st embodiment of this invention. It is the partial cross section figure seen from the circumferential direction of the modification of the separation ring of 1st embodiment of this invention. It is sectional drawing seen from the radial direction of the separation ring of 2nd embodiment of this invention. It is sectional drawing seen from the radial direction of the separation ring of 3rd embodiment of this invention. It is sectional drawing seen from the radial direction of the separation ring of 4th embodiment of this invention. It is A arrow directional view of FIG. 10, Comprising: It is the figure seen from the axial direction of the separation ring of 4th embodiment of this invention. It is the figure seen from the axial direction of the modification of the separation ring of 4th embodiment of this invention. It is the figure seen from the axial direction of the separation ring of 5th embodiment of this invention. It is a partial sectional view seen from the peripheral direction of the separation ring of the sixth embodiment of the present invention. It is sectional drawing seen from the radial direction of the conventional split ring.

(First embodiment)
Hereinafter, a combustor 3 according to a first embodiment of the present invention will be described with reference to the drawings.
As shown in FIG. 1, a gas turbine 1 that is a rotating machine according to the present embodiment includes a compressor 2 that takes in a large amount of air and compresses it, and supplies fuel to compressed air A compressed by the compressor 2. A combustor 3 for mixing and burning, and a turbine 4 for converting thermal energy of the combustion gas G introduced from the combustor 3 into rotational energy are provided.

  Each of the compressor 2 and the turbine 4 includes a rotor 5 that is coupled so as to rotate integrally, and a stator 6 that surrounds the outer peripheral side of the rotor 5. The rotor 5 has a rotating shaft 7 and a plurality of annular blade groups 8 fixed at intervals in the axial direction. Each annular moving blade group 8 is configured to have a plurality of moving blades fixed on the outer periphery of the rotating shaft 7 at intervals in the circumferential direction.

The stator 6 includes a casing 9 and a plurality of annular stator blade groups 10 that are fixed in the casing 9 at intervals in the axial direction. The annular stationary blade group 10 has a plurality of stationary blades fixed to the inner surface of each casing 9 at intervals in the circumferential direction.
The annular stator blade groups 10 are alternately arranged with the plurality of annular rotor blade groups 8 in the axial direction.

The combustor 3 according to the present embodiment is of a dual type capable of oiling in addition to gas burning. As shown in FIG. 2, the combustor 3 is a double swirler combustor including an inner swirler 20 and an outer swirler 21 disposed inside the inner cylinder 13.
Specifically, the combustor 3 includes an inner cylinder 13 accommodated in the interior of the casing 12, and an outer cylinder 14 that covers the outer peripheral side of the inner cylinder 13 and abuts against the inner wall of the casing 12. The inner cylinder 13 is a hollow tubular member. A tail cylinder (not shown) is connected to the downstream side of the inner cylinder 13. An air flow path 15 through which the compressed air A flows is formed between the inner peripheral surface of the outer cylinder 14 and the outer peripheral surface of the inner cylinder 13. The compressed air A that has flowed into the air flow path 15 is supplied to the inside of the inner cylinder 13 by turning 180 ° at the reversing portion 16 at the bottom of the outer cylinder 14.

  A top hat nozzle 17 is provided in the compressed air A flowing through the air flow path 15 on the air flow path 15 and upstream of the reversing unit 16. The top hat nozzles 17 are arranged at equal intervals in the circumferential direction of the inner cylinder 13 and include a plurality of top hat nozzle fuel injection holes 18.

The combustor 3 includes an inner swirler 20 and an outer swirler 21 that are formed coaxially with the axial center of the inner cylinder 13. The inner swirler 20 and the outer swirler 21 are flow paths that have an annular cross section and allow the compressed air A to flow.
A large number of inner swirl vanes 22 are arranged in the circumferential direction inside the inner swirler 20 and downstream of the inner swirler 20. A plurality of inner fuel ejection holes 23 are formed in the inner swirl vane 22. Similarly, a large number of outer swirl vanes 24 are arranged in the circumferential direction inside the outer swirler 21 and downstream of the outer swirler 21. A plurality of outer fuel ejection holes 25 are formed in the outer swirl vane 24.

  The inner swirler 20 and the outer swirler 21 are partitioned by a cylindrical separation ring 27. A plurality of fuel supply paths 28 are formed inside the separation ring 27. An oil supply line 30 for supplying oil fuel from an oil supply source 29 is connected to the fuel supply path 28.

A plurality of fuel ejection paths 31 (see FIG. 4) are formed at one end (downstream side) of the separation ring 27 in the axial direction. In the combustor 3 of this embodiment, four fuel ejection paths 31 are provided for one fuel supply path 28.
In the following description, the axial direction of the separation ring 27 and the inner cylinder 13 will be described simply as the axial direction. In addition, one side in the axial direction is described as the downstream side of the compressed air A.

  As shown in FIG. 3, the separation ring 27 includes a separation ring body 33, a piping unit 34, and a nozzle 35. The separation ring body 33 has a cylindrical shape, and a plurality of pipe insertion holes 36 are formed in the separation ring body 33 along the axis. The pipe insertion holes 36 are formed at equal intervals in the circumferential direction of the separation ring body 33. The pipe insertion hole 36 is a through hole into which the fuel supply pipe 38 of the pipe unit 34 is inserted.

The piping unit 34 includes an annular ring manifold 37 and a plurality of fuel supply pipes 38 extending along the axis of the ring manifold 37 and having one end connected to the ring manifold 37.
The nozzle 35 is an annular member attached to one end of the separation ring 27 in the axial direction. On the surface of the nozzle 35, a plurality of oil fuel injection holes 39, which are openings on the downstream side of the fuel ejection passage 31 described above, are formed.

  As shown in FIG. 4, the pipe insertion hole 36 of the separation ring body 33 is formed at the center of the separation ring body 33 in the plate thickness direction. An annular accommodation space 40 in which the ring manifold 37 of the piping unit 34 is accommodated is formed at one end in the axial direction of the piping insertion hole 36.

The ring manifold 37 of the piping unit 34 is an annular member having a U-shaped cross section, and an opening 41 is formed on one side (downstream side) in the axial direction. Ribs 42 are formed in the opening 41 of the ring manifold 37 so as to project inward in the circumferential direction and outward in the circumferential direction.
The interior of the ring manifold 37 is a cavity 43 and is divided into a plurality of parts by a cavity wall 44. In other words, the cavities 43 of this embodiment are not continuous in the circumferential direction, but are a plurality of discrete cavities 43.

The fuel supply pipe 38 has a circular tube shape, and the inside thereof is a fuel supply path 28. The fuel supply path 28 that is the inside of the fuel supply pipe 38 and the cavity 43 of the ring manifold 37 communicate with each other.
The cross-sectional shape of the nozzle 35 is a triangular shape whose width gradually decreases toward one side in the axial direction X. A plurality of fuel ejection paths 31 are formed in the nozzle 35. The fuel ejection path 31 is an injection hole that injects the oil fuel supplied from the fuel supply path 28. The other side in the axial direction X of the fuel ejection passage 31 opens into a connection surface 45 with the separation ring body 33 on the other side in the axial direction X of the nozzle 35, and the nozzle 35 is connected to the separation ring body 33 together with the piping unit 34. By being attached, it is formed to communicate with the cavity 43.

  One side of the fuel ejection path 31 in the axial direction X opens to one side of the nozzle 35 in the axial direction X to form an oil fuel injection hole 39. Specifically, the radially outer outer fuel ejection path 31 a is opened on the outer peripheral surface of the nozzle 35, and the radially inner inner fuel ejection path 31 b is opened on the inner circumferential surface of the nozzle 35.

  Further, two annular spaces 46 are formed in the nozzle 35 along the circumferential direction. The annular space 46 includes an annular groove 47 having a rectangular cross section formed on the connection surface 45 of the nozzle 35 and an annular sealing plate 48 that seals the opening of the groove 47. The groove 47 is formed in a range that does not interfere with the fuel ejection path 31 and does not affect the strength of the nozzle 35. The sealing plate 48 is welded to the nozzle 35 by an annular weld W1.

  As shown in FIG. 5, the fuel supply path 28, the cavity 43, and the fuel ejection path 31 communicate with each other. That is, the oil fuel supplied from the fuel supply path 28 once flows into the cavity 43, and then is injected from the fuel ejection path 31 to the one side in the axial direction X outside the cavity 43. The fuel ejection path 31 has an inner fuel ejection path 31b that faces the inner side in the radial direction R and an outer fuel ejection path 31a that faces the outer side in the radial direction R, and the oil fuel is downstream of the compressed air A. Thus, the fuel is injected in the radial direction R inner side and the radial direction R outer side.

  Although not shown in FIG. 5, four fuel ejection paths 31 are formed for one fuel supply path 28, and the oil fuel supplied from one fuel supply path 28 has four fuel ejection paths. Injected from the path 31. That is, a pair of inner fuel ejection paths 31 b and a pair of outer fuel ejection paths 31 a are formed for one fuel supply path 28.

A constant space 50 is formed between the fuel supply pipe 38 and the separation ring body 33. In other words, a uniform gap is formed in the circumferential direction of the fuel supply pipe 38 between the inner peripheral surface of the pipe insertion hole 36 of the separation ring body 33 and the outer peripheral surface of the fuel supply pipe 38. Similarly, a space 50 is also formed between the ring manifold 37 and the separation ring body 33. Spacers 51 are appropriately disposed between the fuel supply pipe 38 and the separation ring body 33 and between the ring manifold 37 and the separation ring body 33.
The separation ring main body 33 and the piping unit 34 are joined by welding the rib 42 of the ring manifold 37 and one end of the separation ring main body 33 in the axial direction (the welded portion is indicated by W2). The separation ring main body 33 and the nozzle 35 are joined by a welded portion indicated by a symbol W3.

As shown in FIG. 6, the cavity 43 formed inside the ring manifold 37 is partitioned into a plurality of portions by a cavity wall 44. The cavity 43 is partitioned so that one section is independently assigned to one fuel supply path 28.
Two (a pair) of outer fuel ejection paths 31 a are provided for one fuel supply path 28. Although not confirmed from FIG. 6, two (a pair) of inner fuel ejection paths 31 b are also provided for one fuel supply path 28.

  One and the other of the pair of inner fuel ejection paths 31b are arranged so as to form an equal interval from the fuel supply path 28 in the opposite direction of the circumferential direction when viewed from the axial direction X. Similarly, one and the other of the pair of outer fuel ejection passages 31a are arranged so as to form equal intervals in the opposite direction of the circumferential direction from the fuel supply passage 28 when viewed from the axial direction X. That is, the fuel supply path 28 and the fuel ejection path 31 are not arranged on a straight line.

Inside the cavity 43, between the pair of fuel ejection paths 31 spaced in the circumferential direction C, the oil fuel introduced from the fuel supply path 28 is guided to the pair of fuel ejection paths 31 spaced in the circumferential direction C. A guide 52 is formed. The oil fuel is guided by the guide portion 52 as indicated by the symbol F.
The guide part 52 is composed of a pair of first guide surfaces 53. The first guide surface 53 is a slope that guides the oil fuel introduced from the fuel supply passage 28 toward the fuel ejection passage 31, and is connected by a ridge line 54 on the upstream side. In other words, the guide part 52 is formed of a pair of first guide surfaces 53 that gradually increase from the upstream ridge line 54 toward the downstream side.

Next, the operation of the combustor 3 of the present embodiment will be described.
First, the compressed air A discharged from the outlet of the compressor 2 into the vehicle compartment 12 flows into an air flow path 15 formed between the outer cylinder 14 and the inner cylinder 13. The compressed air A that has flowed into the air flow path 15 flows along the inner wall of the outer cylinder 14.

Next, the compressed air A rotates 180 ° at the reversing unit 16. The compressed air A is supplied with gas fuel from the inner fuel injection hole 23 and the outer fuel injection hole 25 while being swirled by the inner swirler 20 and the outer swirler 21 of the combustor 3.
During the oiling operation, the oil fuel is supplied to the compressed air A through the oil fuel injection hole 39.

According to the above-described embodiment, four fuel ejection paths 31 are provided for one fuel supply path 28, so that oil fuel is injected from the fuel ejection path 31 due to a difference in pressure in the fuel supply path 28. The amount variation can be reduced.
Further, by providing the cavity 43 between the fuel supply path 28 and the fuel ejection path 31, the oil fuel is equalized in the cavity 43. Thereby, the dispersion | variation in the injection amount of the oil fuel from the fuel ejection path 31 can be reduced more.

  In addition, since the guide portion 52 is provided in the cavity 43 between the pair of fuel ejection paths 31, a staying area formed in the cavity 43 when oil fuel is introduced into the cavity 43. It becomes difficult to form. By reducing the residence area where the flow rate is low, heating of the oil fuel is reduced, and coking can be reduced.

In addition, a space 50 that functions as a heat insulating layer is formed between the fuel supply pipe 38 that defines the fuel supply path 28 and the separation ring body 33, and between the ring manifold 37 and the separation ring body 33. The oil fuel can be reduced from being heated.
Further, by forming a space functioning as a heat insulating layer in the nozzle 35, heat input to the oil fuel from the downstream side can be reduced.

  In addition, at least a pair of fuel ejection paths 31 are provided with respect to the fuel supply path 28, and one and the other of the pair of fuel ejection paths 31 are equally spaced from each fuel supply path 28 in the opposite direction of the circumferential direction. It is arranged to form. Thereby, since at least a pair of fuel ejection paths 31 are provided at symmetrical positions with respect to the fuel supply path 28, the fuel can be introduced into the plurality of fuel ejection paths 31 in a well-balanced manner.

In the above embodiment, when the separation ring 27 is assembled, the pipe unit 34 is joined to the separation ring body 33 and then the nozzle 35 is joined to the separation ring body 33. However, the present invention is not limited to this. For example, as shown in FIG. 7, after the nozzle 35 and the piping unit 34 are welded (the welded portion is indicated by W <b> 4), the separation ring main body 33 and the nozzle 35 may be welded.
According to the said structure, the range of the space 50 which functions as a heat insulation layer can be increased.

(Second embodiment)
Hereinafter, the separation ring 27 of the combustor 3 according to the second embodiment of the present invention will be described with reference to the drawings. In the present embodiment, differences from the first embodiment described above will be mainly described, and description of similar parts will be omitted.
As shown in FIG. 8, the guide portions 52 of the present embodiment are formed at both end portions in the circumferential direction C of the cavity 43, and gradually increase the width in the circumferential direction C of the cavity 43 toward one side in the axial direction X. It is the 2nd guide surface 56 which is a pair of slope formed in this way.

  According to the above-described embodiment, the oil fuel introduced into the cavity 43 from the fuel supply passage 28 is not excessively spread in the circumferential direction C by the guide portion 52 configured by the second guide surface 56, and the fuel ejection passage 31. To be introduced. That is, it becomes difficult to form a staying area on both sides of the cavity 43 in the circumferential direction C, and heating of the oil fuel is reduced.

(Third embodiment)
Hereinafter, the separation ring 27 of the combustor 3 according to the third embodiment of the present invention will be described with reference to the drawings. In the present embodiment, differences from the first embodiment described above will be mainly described, and description of similar parts will be omitted.
As shown in FIG. 9, the cavity 43 of the present embodiment is not defined by the cavity wall 44 (see FIGS. 4 and 6), and extends in the circumferential direction C. The guide unit 52 of the present embodiment includes a pair of first guide surfaces 53 and a pair of second guide surfaces 56.

Similar to the first guide surface 53 of the first embodiment, the first guide surface 53 is a slope that guides the oil fuel introduced from the fuel supply path 28 toward the fuel ejection path 31, and the ridge line 54 on the upstream side. Connected at. In other words, the guide part 52 is formed of a pair of first guide surfaces 53 that gradually increase from the upstream ridge line 54 toward the downstream side.
The second guide surfaces 56 are a pair of inclined surfaces formed at both ends in the circumferential direction C of the cavity 43 and formed so as to gradually increase the width in the circumferential direction C of the cavity 43 toward one side in the axial direction X. is there.

  Like the said embodiment, the guide part 52 of this embodiment is applicable also to the cavity 43 formed continuously in the circumferential direction.

(Fourth embodiment)
Hereinafter, the separation ring 27 of the combustor 3 according to the fourth embodiment of the present invention will be described with reference to the drawings. In the present embodiment, differences from the first embodiment described above will be mainly described, and description of similar parts will be omitted.
As shown in FIGS. 10 and 11, the fuel ejection path 31 of the present embodiment is connected to both end faces 58 of the cavity 43 in the circumferential direction C. In other words, the fuel ejection path 31 is formed on an extension line of the both end surfaces 58 so that the oil fuel flowing along the both end surfaces 58 of the cavity 43 is easily introduced. Thereby, both end surfaces 58 of the cavity 43 function as the guide portion 52.

  According to the above-described embodiment, the oil fuel introduced into the cavity 43 from the fuel supply path 28 is guided to the both end surfaces 58 functioning as the guide portion 52, so that it is difficult to form a staying area in the cavity 43. Less heating.

  In addition, as shown in FIG. 12, it is preferable to form a pair of radial direction guide surfaces 59 which branch an oil fuel into radial direction R inner side and radial direction R outer side in the both end surfaces 58 of the said embodiment. By forming such a radial guide surface 59, it is possible to suppress stagnation that occurs when the oil fuel introduced from the fuel supply path 28 contacts both end surfaces 58.

(Fifth embodiment)
Hereinafter, the separation ring 27 of the combustor 3 according to the fifth embodiment of the present invention will be described with reference to the drawings. In this embodiment, the differences from the above-described fourth embodiment will be mainly described, and the description of the same parts will be omitted.
As shown in FIG. 13, both end faces of the present embodiment are arcuate end faces 60 that form an arc shape when viewed from the direction along the axis. Specifically, it has a shape with rounded corners as indicated by a two-dot chain line.
According to the above-described embodiment, it is possible to suppress stagnation and stagnation as indicated by the symbol E in FIG. 13 that occurs when both end surfaces 58 are not arcuate.

(Sixth embodiment)
Hereinafter, the separation ring 27 of the combustor 3 according to the fifth embodiment of the present invention will be described with reference to the drawings. In the present embodiment, differences from the first embodiment described above will be mainly described, and description of similar parts will be omitted.
As shown in FIG. 14, the cavity 43 of this embodiment is formed by a cavity 43 defined by the ring manifold 37 and a nozzle cavity 62 formed in the nozzle 35.

  The nozzle cavity 62 is a groove having a triangular cross section formed along the circumferential direction of the nozzle 35, and includes a pair of radially opposed surfaces 63. The dimension in the radial direction R of the nozzle cavity 62 is substantially the same as the dimension in the radial direction R of the cavity 43 of the ring manifold 37. The nozzle cavity 62 is formed so that the width in the radial direction gradually decreases toward one side in the axial direction X. That is, the nozzle cavity 62 has a pair of radially opposed surfaces 63 formed so as to gradually approach toward one side in the axial direction X.

  The pair of outer fuel ejection paths 31 a and the pair of inner fuel ejection paths 31 b are connected to the respective axial direction X one side ends of the pair of radial facing surfaces 63. In other words, the cavity 43 of the present embodiment is convex toward the downstream side, and the two pairs of fuel ejection paths 31 are connected to the vicinity of the downstream end of the ring cavity 43.

  According to the above-described embodiment, the oil fuel is guided by the radial facing surface 63, so that the residence region formed in the cavity 43 is less than that in the case where the downstream end of the cavity 43 has a planar shape. It becomes difficult to form.

1 Gas turbine (rotary machine)
DESCRIPTION OF SYMBOLS 2 Compressor 3 Combustor 4 Turbine 5 Rotor 6 Stator 7 Rotating shaft 8 Annular blade group 9 Casing 10 Annular stator blade group 12 Car interior 13 Inner cylinder 14 Outer cylinder 15 Air flow path 16 Reversing part 17 Top hat nozzle 18 Top hat Nozzle fuel injection hole 20 Inner swirler 21 Outer swirler 22 Inner swirl vane 23 Inner fuel injection hole 24 Outer swirl vane 25 Outer fuel injection hole 27 Separation ring 28 Fuel supply path 29 Oil supply source 30 Oil supply line 31 Fuel injection path 31a Outer fuel Injection path 31b Inner fuel ejection path 33 Separation ring body 34 Piping unit 35 Nozzle 36 Pipe insertion hole 37 Ring manifold 38 Fuel supply pipe 39 Oil fuel injection hole 40 Storage space 41 Opening portion 42 Rib 43 Cavity 44 Cavity wall 46 Annular space 47 Groove Article 48 Sealing plate DESCRIPTION OF SYMBOLS 50 Space 51 Spacer 52 Guide part 53 1st guide surface 54 Ridge line 56 2nd guide surface 58 Both end surfaces 59 Radial direction guide surface 60 Arc-shaped end surface 62 Nozzle cavity 63 Radial direction opposing surface A Compressed air

Claims (12)

  1. A plurality of fuel supply passages extending along the axis at intervals in the circumferential direction of the axis;
    A cavity connected to the plurality of fuel supply passages, into which fuel flowing through the fuel supply passages is introduced and extending in the circumferential direction;
    A plurality of nozzles provided at intervals in the circumferential direction and connected to one side in the axial direction of the cavity, and a fuel ejection path for ejecting the fuel to the outside of the cavity, and
    A combustor, wherein a guide portion for guiding the fuel introduced from the fuel supply passage to the fuel ejection passage is formed in the cavity.
  2. The fuel ejection path is provided with at least a pair with respect to the fuel supply path,
    The one and the other of the pair of fuel ejection paths are arranged so as to form equal intervals in the opposite direction of the circumferential direction from each of the fuel supply paths as viewed from the direction along the axis. The combustor according to 1.
  3.   The combustor according to claim 2, wherein the cavity is formed independently for each of the at least one pair of fuel ejection paths.
  4.   4. The combustor according to claim 2, wherein the guide portion guides the fuel introduced from the fuel supply path to one and the other of the at least one pair of fuel ejection paths. 5.
  5.   5. The combustion according to claim 4, wherein the guide portion is a pair of guide surfaces that are provided between the pair of fuel ejection paths and branch the fuel into one circumferential direction and the other circumferential direction. vessel.
  6.   The guide portions are a pair of guide surfaces formed at both ends in the circumferential direction of the cavity and formed so as to gradually increase the circumferential width of the cavity toward one side in the axial direction. The combustor according to claim 4 or 5.
  7.   The combustion according to any one of claims 3 to 5, wherein the fuel ejection path is connected to both end faces in the circumferential direction of the cavity, and the guide portion is the both end faces. vessel.
  8. A pair of inner fuel ejection paths for injecting the fuel radially inward;
    A pair of outer fuel ejection paths for injecting the fuel radially outward,
    The combustor according to claim 7, wherein a pair of radial guide surfaces for branching the fuel radially inward and radially outward are formed on the both end surfaces.
  9.   5. The combustor according to claim 3, wherein both end faces of the cavity in the circumferential direction have an arc shape when viewed from a direction along the axis.
  10. A pair of inner fuel ejection paths for injecting the fuel radially inward;
    A pair of outer fuel ejection paths for injecting the fuel radially outward,
    The cavity has a pair of radially opposed surfaces that gradually decrease in distance in the radial direction toward one side in the axial direction.
    The guide portions are the pair of radially opposed surfaces, and the two pairs of fuel ejection paths are connected to respective one axial end portions of the pair of radially opposed surfaces. The combustor according to claim 3 or 4.
  11. The combustor includes a cylindrical separation ring body;
    A pipe-shaped fuel supply pipe penetrating the inside of the separation ring body along the axis, the inside being the fuel supply path;
    A ring manifold disposed at one end in the axial direction of the separation ring body and forming the cavity therein;
    11. The space according to claim 1, wherein a space is provided between at least one of the fuel supply pipe and the separation ring body and between the ring manifold and the separation ring body. The combustor according to one item.
  12.   A rotating machine comprising the combustor according to any one of claims 1 to 11.
JP2013222243A 2013-10-25 2013-10-25 Combustor and rotating machine Active JP6116464B2 (en)

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Citations (8)

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JP2002031343A (en) * 2000-07-13 2002-01-31 Mitsubishi Heavy Ind Ltd Fuel injection member, burner, premixing nozzle of combustor, combustor, gas turbine and jet engine
JP2003148710A (en) * 2001-11-14 2003-05-21 Mitsubishi Heavy Ind Ltd Combustor
JP2003279043A (en) * 2002-03-22 2003-10-02 Ishikawajima Harima Heavy Ind Co Ltd LOW NOx COMBUSTOR FOR GAS TURBINE
JP2009074792A (en) * 2007-09-21 2009-04-09 General Electric Co <Ge> Toroidal ring manifold for secondary fuel nozzle of dln gas turbine
JP2009074706A (en) * 2007-09-19 2009-04-09 Hitachi Ltd Gas turbine combustor
JP2011099654A (en) * 2009-11-09 2011-05-19 Mitsubishi Heavy Ind Ltd Combustion burner for gas turbine
JP2011122814A (en) * 2009-12-08 2011-06-23 General Electric Co <Ge> Fuel injection in secondary fuel nozzle
JP2011149676A (en) * 2009-12-22 2011-08-04 Mitsubishi Heavy Ind Ltd Combustion burner and boiler with the combustion burner

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002031343A (en) * 2000-07-13 2002-01-31 Mitsubishi Heavy Ind Ltd Fuel injection member, burner, premixing nozzle of combustor, combustor, gas turbine and jet engine
JP2003148710A (en) * 2001-11-14 2003-05-21 Mitsubishi Heavy Ind Ltd Combustor
JP2003279043A (en) * 2002-03-22 2003-10-02 Ishikawajima Harima Heavy Ind Co Ltd LOW NOx COMBUSTOR FOR GAS TURBINE
JP2009074706A (en) * 2007-09-19 2009-04-09 Hitachi Ltd Gas turbine combustor
JP2009074792A (en) * 2007-09-21 2009-04-09 General Electric Co <Ge> Toroidal ring manifold for secondary fuel nozzle of dln gas turbine
JP2011099654A (en) * 2009-11-09 2011-05-19 Mitsubishi Heavy Ind Ltd Combustion burner for gas turbine
JP2011122814A (en) * 2009-12-08 2011-06-23 General Electric Co <Ge> Fuel injection in secondary fuel nozzle
JP2011149676A (en) * 2009-12-22 2011-08-04 Mitsubishi Heavy Ind Ltd Combustion burner and boiler with the combustion burner

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