WO2021261431A1 - 燃料噴射器及びこの燃料噴射器を備える燃焼器並びにこの燃焼器を備えるガスタービン - Google Patents
燃料噴射器及びこの燃料噴射器を備える燃焼器並びにこの燃焼器を備えるガスタービン Download PDFInfo
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- WO2021261431A1 WO2021261431A1 PCT/JP2021/023368 JP2021023368W WO2021261431A1 WO 2021261431 A1 WO2021261431 A1 WO 2021261431A1 JP 2021023368 W JP2021023368 W JP 2021023368W WO 2021261431 A1 WO2021261431 A1 WO 2021261431A1
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- opening
- flow path
- divided
- fuel injector
- internal flow
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
Definitions
- the present disclosure relates to a fuel injector, a combustor including the fuel injector, and a gas turbine including the combustor.
- the gas turbine described in Patent Document 1 is provided with a fuel injector (peg) having a double pipe structure having an inner pipe through which fuel flows and an outer pipe through which air flows. Since this fuel injector extends in a direction intersecting the direction of air flow, stagnation may be formed in a region on the downstream side of the fuel injector in the direction of air flow. If the air containing the fuel injected from the fuel injector stays in such a stagnation, the reliability of the combustor is lowered.
- peg fuel injector having a double pipe structure having an inner pipe through which fuel flows and an outer pipe through which air flows. Since this fuel injector extends in a direction intersecting the direction of air flow, stagnation may be formed in a region on the downstream side of the fuel injector in the direction of air flow. If the air containing the fuel injected from the fuel injector stays in such a stagnation, the reliability of the combustor is lowered.
- At least one embodiment of the present disclosure provides a fuel injector capable of improving the reliability of the combustor, a combustor including the fuel injector, and a gas turbine including the combustor.
- the purpose is to do.
- the fuel injector according to the present disclosure is a fuel injector having a main body portion extending in the axial direction, and the main body portion is an axial flow path formed so as to extend in the axial direction.
- the first opening portion and the second opening portion When the main body portion is viewed so as to face the portion, the first opening portion and the second opening portion have the radial flow path outside the main body portion in the circumferential direction about the axis of the main body portion. It is located on the opposite side of the third opening that opens to the surface.
- the possibility of forming stagnation of air and fuel flow in the region on the downstream side of the fuel injector can be reduced, so that the reliability of the combustor can be improved.
- FIG. 3 is a cross-sectional view taken along the line IV-IV of FIG. It is sectional drawing along the VV line of FIG.
- FIG. 3 is a view seen from the direction of arrow VI in FIG.
- FIG. 3 is a view seen from the direction of arrow VII in FIG.
- the gas turbine 1 includes a compressor 2 and a plurality of combustors 3 (only one combustor 3 is shown in FIG. 1). It is equipped with a turbine 4.
- the compressor 2 is configured to suck in and compress the atmosphere, which is the outside air, and supply the compressed air to the combustor 3.
- the combustor 3 is configured to generate combustion gas by burning fuel supplied from the outside using air compressed by the compressor 2.
- the turbine 4 is configured to generate a rotational driving force by receiving the supply of the combustion gas generated by the combustor 3 and output the generated rotational driving force to the compressor 2 and an external device such as a generator 6. ing.
- the combustor 3 includes an outer cylinder 11, and an inner cylinder 12 is provided inside the outer cylinder 11 at predetermined intervals in the radial direction about the axis of the outer cylinder 11. There is.
- the tail cylinder 13 is connected to the tip of the inner cylinder 12.
- a ring-shaped flow path 21 through which air compressed by the compressor 2 (see FIG. 1) flows is formed between the outer cylinder 11 and the inner cylinder 12.
- a pilot combustion burner 14 and a plurality of main combustion burners 15 provided so as to surround the pilot combustion burner 14 are arranged inside the inner cylinder 12, a pilot combustion burner 14 and a plurality of main combustion burners 15 provided so as to surround the pilot combustion burner 14 are arranged.
- the pilot combustion burner 14 includes a pilot nozzle 23, and each main combustion burner 15 includes a main nozzle 26.
- a plurality of pegs 28 that are fuel injectors are arranged in the circumferential direction around the axis of the outer cylinder 11 (that is, the inner cylinder 12). It is provided so as to have a predetermined interval (in the circumferential direction about the axis of the).
- Each peg 28 is provided so that the base end portion is fixed to the outer cylinder 11 and the tip end portion extends toward the inner cylinder 12.
- the peg 28 has a main body portion 30 extending from the base end portion 30a to the tip end portion 30b.
- the main body portion 30 has a double pipe structure composed of an inner pipe 31 and an outer pipe 32, and the main body portion 30 has an axial flow path formed so as to extend in the axial direction. 33 is included, and the first opening 36 and the second opening 37 that open to the outer surface 30c of the main body 30 are included, and the inside of the main body 30 is formed so as to extend from the first opening 36 to the second opening 37.
- An internal flow path 35 is formed.
- the internal flow path 35 is configured to extend inside the circumferential direction (hereinafter, simply referred to as “circumferential direction”) about the axis L of the main body portion 30 so as to surround the axial flow path 33, and is a first opening. It includes two branch flow path portions 35a and 35b extending in opposite directions in the circumferential direction from 36 toward the second opening 37. The axial flow path 33 and the internal flow path 35 do not communicate with each other.
- the main body 30 is further provided with a radial flow path 34 formed so that one end communicates with the axial flow path 33 and the other end opens to the outer surface 30c of the main body 30. It is formed.
- the radial flow path 34 does not communicate with the internal flow path 35 (see FIG. 4).
- a third opening 38 is formed on the outer surface 30c as an opening of the radial flow path 34.
- the radial flow path 34 includes six radial flow paths 34a, 34b, 34c, 34d, 34e, and 34f, but the number is not limited to six and may be any number. good. Further, the position of each radial flow path 34 is not limited. In FIG.
- two radial flow paths 34 are formed at the same position in the axial direction, but only one radial flow path 34 is formed at an arbitrary position in the axial direction. May be formed.
- two radial flow paths 34a and 34b are provided near the tip portion 30b and at the same position in the axial direction, and the other four radial channels are provided.
- the flow paths 34c to 34f may be arranged at different positions in the axial direction on the proximal end portion 30a side of the radial flow paths 34a and 34b, respectively.
- the positions of the radial flow paths 34a, 34b, 34c, 34d, 34e, and 34f are such that the third openings 38a, 38b, 38c, 38d, 38e, and 38f each have the second opening 37 in the axial direction (FIG. 4). It is preferable to determine that it is located within the range in which (see) exists.
- the first opening 36 The second opening 37 is located on the opposite side of the third opening 38c in the circumferential direction. That is, the third opening 38c is located between the first opening 36 and the second opening 37 in the circumferential direction.
- the center positions of the first opening 36, the second opening 37, and the third opening 38c in the circumferential direction are A, B, and C, and the axis center of the main body 30 on the axis L is O.
- angle AOC (hereinafter referred to as angle ⁇ 1) and the angle BOC (hereinafter referred to as angle ⁇ 2) are 45 ° or more and 135 ° or less, preferably 60 ° or more and 120 ° or less, and more preferably 80 ° or more and 100 ° or less, respectively. , Most preferably 90 °.
- the opening surfaces 32a of the outer pipe 32 defining the first opening 36 are the opening surfaces 32a1 and 32a2, respectively, and the extension surfaces S1 and S2 of the opening surfaces 32a1 and the opening surfaces 32a2 are respectively.
- the angle formed is ⁇ 3
- a part of the air compressed by the compressor 2 flows into the internal flow path 35 through the first opening 36, but when ⁇ 3 is set to less than 45 °, as much as possible
- the opening width in the circumferential direction must be widened, which is limited based on the thickness of the main body 30.
- the internal flow path 35 includes three divided internal flow paths 35c, 35d, 35e that do not communicate with each other in the axial direction.
- the divided internal flow paths 35c, 35d, 35e include the first divided openings 36a, 36b, 36c constituting the first opening 36, respectively.
- the divided internal flow paths 35c, 35d, 35e include the second divided openings 37a, 37b, 37c constituting the second opening 37, respectively.
- the number of internal flow paths 35 to be divided is not limited to 3, and the internal flow path 35 may be divided into two or any number of four or more. In that case, the number of divisions of each of the first opening 36 and the second opening 37 is the same as the number of divisions of the internal flow path 35.
- each of the third openings 38a to 38f is located within the range in which the second opening 37 (see FIG. 4) exists in the axial direction.
- the third opening 38f is the second divided opening 37a in the axial direction as shown in FIG.
- the third opening 38d is located within the range in which the second split opening 37b exists in the axial direction
- the third opening 38b has the second split opening 37c in the axial direction.
- the configuration is located within the range.
- the third openings 38a, 38c, 38e are also configured to be located within the range in which the second divided openings 37c, 37b, 37a exist in the axial direction, respectively. preferable.
- each of the internal flow paths 35 that is, the divided internal flow paths 35c, 35d, and 35e, is directed from the first opening 36 toward the second opening 37, or the first opening 36 and the second opening 37. It can be configured so that the flow path area decreases from the position between the and toward the second opening 37.
- the opening width in the axial direction and the opening width in the circumferential direction of the first opening 36 are set to w 1a and w 1p , respectively. 2 Assuming that the opening width in the axial direction and the opening width in the circumferential direction of the opening 37 are w 2a and w 2p , respectively, it is preferable that (w 1a / w 2a )> (w 1p / w 2p).
- FIG. 8 shows an example of a configuration for realizing a configuration in which the flow path area of the internal flow path 35 decreases from the position between the first opening 36 and the second opening 37 toward the second opening 37.
- FIG. 8 shows a cut surface CS along the axis L of an arbitrary flow path surface FS of one branch flow path portion 35b of the internal flow path 35 with respect to the cross-sectional view shown in FIG. 4 (the left view of FIG. 8).
- the axis L of the main body 30 developed on a virtual plane (the figure on the right side of FIG. 8; hereinafter, this figure is referred to as a “developed view”, and the shape represented by this developed view is “developed”. "Shape").
- the branch flow path portion 35b is divided into a first flow path portion 35b1 which is a portion upstream from the first opening 36 toward the second opening 37 and a second flow path portion 35b2 which is a portion on the downstream side.
- the flow path surface FS the flow path surface corresponding to the first flow path portion 35b1 is referred to as FS1
- the flow path surface corresponding to the second flow path portion 35b2 is referred to as FS2.
- the angle formed by the direction R1 in which the flow path surface FS1 of the first flow path portion 35b1 extends with respect to the axis L is ⁇ a
- the direction R2 in which the flow path surface FS2 of the second flow path portion 35b2 extends with respect to the axis L is ⁇ a
- FIG. 8 shows an example of a configuration in which ⁇ b ⁇ a, instead of such a simple configuration. That is, the second flow path portion 35b2 is bent toward the tip portion 30b (see FIG. 3) with respect to the first flow path portion 35b1 (in FIG. 8, in the depth direction perpendicular to the paper surface). There is.
- the flow path area of the internal flow path 35 is reduced, that is, the flow path area of the second flow path portion 35b2 is reduced.
- the second opening portion 37 is axially aligned with the third opening portion 38 into which fuel is injected. It can be in the same position.
- the opening areas of the first divided openings 36a to 36c are drawn to be the same, but the present invention is not limited to such a form. At least two of the respective opening areas of the first divided openings 36a to 36c may be different from each other. For example, if there is no radial flow path 34c and 34e for the configuration shown in FIG. 5, and therefore there is also no third opening 38c and 38e, the position of the first opening 36 closest to the tip 30b.
- the opening area of the first divided opening 36c of the divided internal flow path 35e in the above is larger than the opening area of each of the first divided openings 36a and 36b of the other divided internal flow paths 35c and 35d. May be good. In this case, the third openings 38f and 38d (see FIG.
- the fuel is injected from each of the third openings 38 after flowing through the axial flow path 33 (see FIGS. 4 and 5), and the air compressed by the compressor 2 (see FIG. 1).
- the range in which the second split opening 37c is present in the axial direction is injected as compared with the range in which the second split openings 37a and 37b are present in the axial direction. It is thought that the amount of fuel will increase.
- the amount of air flowing into the divided internal flow path 35e corresponding to the latter range is the other divided internal flow path 35c. , 35d or more.
- the opening area of the second divided opening 37c that defines the range of the third opening 38 having the largest opening area, that is, the range where the third openings 38a and 38b are located is defined as S 2L, and this second The opening area of the first divided opening 36c corresponding to the divided opening 37c is S 1L, and the opening area of each of the second divided openings 37a and 37b defining each range in which the other third openings 38f and 38d are located.
- the opening areas of the second divided openings 37a, 37b, and 37c are all configured to be the same.
- a part of the air compressed by the compressor 2 flows into the internal flow path 35 through the first opening 36, and then flows into the internal flow path through the second opening 37.
- the amount of air flowing out from each of the second divided openings 37a, 37b, 37c is the amount of air flowing out of each of the first divided openings 36a, 36b, 36c corresponding to the second divided openings 37a, 37b, 37c. Since it can be adjusted by the opening area, the design work of the peg 28 can be simplified.
- the opening areas of the second divided openings 37a, 37b, and 37c are all the same, it does not require that the opening areas are completely the same, and even if there are some differences, they are approximately the same. It may be the same opening area.
- the ratio of the opening area of each of the second divided openings 37a, 37b, 37c to the average value of the opening areas of the second divided openings 37a, 37b, 37c is 0.8 to 1.2. Just do it.
- the air introduced into the combustor 3 flows into the inner cylinder 12 through the flow path 21, and is mixed and mixed with the fuel supplied from the pilot nozzle 23 and the main nozzle 26. It becomes anxious, and the air-fuel mixture burns to generate combustion gas.
- the air passes through the flow path 21, it passes through the peg 28, and fuel is supplied from the peg 28 at this time as well, and the air and the fuel are mixed.
- the fuel supplied to the peg 28 from a supply source flows through the axial flow path 33 from the base end portion 30a side toward the tip end portion 30b side, and from the radial flow path 34a to It is distributed to each of the 34f and is injected from each of the third openings 38a to 38f into the flow path 21.
- the air flowing through the flow path 21 branches to both sides of the peg 28 and passes through the peg 28.
- the fuel injected from each of the third openings 38a and 38b is mixed with each of the air that branches to both sides of the peg 28 and passes through the peg 28, and is mixed with each of the air passing through the peg 28 on the downstream side of the peg 28 in the direction of air flow.
- Meet. The region between the position where the air and fuel branching to both sides of the peg 28 and passing through the peg 28 meet on the downstream side of the peg 28 and the peg 28, that is, the region K behind the peg 28 when viewed in the direction of air flow.
- air and fuel may be stagnant, that is, stagnation of air and fuel flow may be formed. If air and fuel stay in the region K, it causes a decrease in the reliability of the combustor 3 (see FIG. 2).
- the peg 28 when the peg 28 is used, if the peg 28 is arranged so that the first opening 36 faces the direction in which the air flows, when the air passes through the peg 28, a part of the air reaches the first opening 36. It flows through the internal flow path 35 and flows out from the internal flow path 35 through the second opening 37. According to the positional relationship between the first opening 36 and the peg 28 of the second opening 37, the second opening 37 faces the region K, so that the second opening 37 faces the region K from the internal flow path 35 via the second opening 37. The outflowing air will flow out toward the region K.
- the air flowing out from the internal flow path 35 toward the region K causes the air and the fuel to stay in the region K toward the downstream side. Since it is flushed out, the possibility of forming stagnation of air and fuel flow in the region K can be reduced.
- the opening area of the second opening 37 is smaller than the opening area of the first opening 36, so that the flow velocity of the air flowing into the first opening 36 is larger than the flow velocity of the air flowing into the first opening 36.
- the flow velocity of the air flowing out from the second opening 37 increases.
- the ability to flush out the air and fuel staying in the region K is increased, so that the air and fuel The possibility of flow stagnation can be further reduced. Further, as shown in FIG.
- the flow velocity of the air flowing through the second flow path portion 35b2 is increased by configuring the flow path area of the inner second flow path portion 35b2 to decrease toward the second opening 37. Since it gradually increases, it is possible to prevent the flow of air flowing out from the second opening 37 from being unnecessarily disturbed.
- the opening area of the first divided opening 36c of the divided internal flow path 35e located at the position closest to the tip portion 30b is the first divided opening 36a, 36b of the other divided internal flow paths 35c, 35d, respectively.
- the third opening 38f is located within the range in which the second split opening 37a exists in the axial direction, and the third opening 38d has the second split opening 37b in the axial direction. If the third openings 38a and 38b are located within the range and the second split openings 37c are located within the range in the axial direction, the amount of air flowing into the split internal flow paths 35c and 35d is increased. In comparison, the amount of air flowing into the split internal flow path 35e increases. As shown in FIG.
- the air flowing out from the second opening 37 that suppresses the mixture of the fuel and the air flowing out from the third opening 38 from staying in the region K. It is the air flowing out from the second opening 37 that suppresses the mixture of the fuel flowing out from the third opening 38 and the air from staying in the region K, and the fuel flowing out from the third opening 38. It is the air flowing out from the second opening 37 that suppresses the air-fuel mixture with the air from staying in the region K.
- the third opening 38 includes the four third openings 38a, 38b, 38d, 38f
- the total amount of fuel flowing out from the third openings 38a and b is the third opening 38c and the third opening 38c.
- the amount of fuel flowing out from each of d is larger than the amount of fuel flowing out from each of d, when fuel and air stay in the region K, the fuel concentration in the stagnant air-fuel mixture becomes high, which gives the reliability of the combustor 3 (see FIG. 2).
- the negative effects will be greater.
- the amount of air flowing into the split internal flow path 35e is larger than the amount of air flowing into each of the other split internal flow paths 35c and 35d, the ability to push out the air and fuel staying in the region K is also large. As a result, the possibility that the air and fuel staying in the region K are swept away and the stagnation of the air and fuel flow is formed can be reduced.
- the third opening 38 is located within the range where the second opening 37 exists in the axial direction of the main body portion 30. According to this configuration, the air flowing out from the internal flow path 35 (see FIG. 4) through the second opening 37 passes through the region K at the position where the third opening 38 exists in the axial direction, and thus the region. It is possible to flush the air and fuel retained in K to reduce the possibility of forming a stagnation in the air and fuel flow.
- the internal flow path 35 has two branch flow path portions 35a and 35b, but it may be configured to have only one of the branch flow path portions 35a and 35b.
- the inner wall surfaces 35c1 and 35c2 defining the divided internal flow path 35c, the inner wall surfaces 35d1 and 35d2 defining the divided internal flow path 35d, and the inner wall surfaces 35e1 and 35e2 defining the divided internal flow path 35e are respectively. Although it is drawn as a flat surface, it is not limited to a flat surface, and may be a smooth curved surface, or a surface provided with steps, irregularities, or the like.
- the protrusion 60 includes a surface portion 61 whose bending direction is reversed on the way of the outer surface 31a1 defining the branch flow path portion 35a of the outer surface 31a toward the protrusion 60, and a branch flow path portion 35b of the outer surface 31a. It is preferable that the outer surface 31a2 defining the above surface has a cross-sectional shape sharp toward the second opening 37 due to the surface portion 62 whose bending direction is reversed on the way to the protrusion 60.
- the air flowing in the vicinity of the outer surfaces 31a1 and 31a2 is directed toward the second opening 37 along each of the surface portions 61 and 62, so that the branch flow path portions 35a and 35b, respectively. Since it is possible to suppress the turbulence of the flow that may occur due to collision when the air flowing through the merging, it is possible to suppress the turbulence of the flow that may be contained in the air flowing out from the second opening 37.
- the third opening 38 may protrude from the outer surface 30c of the main body portion 30.
- the third opening 38c is drawn so as to protrude from the outer surface 30c, but the other third openings 38a, 38b, 38d, 38e, 38f may have the same configuration. good. Further, some of the plurality of third openings 38 may have such a configuration.
- the fuel injector of the present disclosure is not limited to the configuration of the peg 28. Any configuration can be used as long as the air flowing out from the internal flow path in the peg can flush the air and fuel staying in the region K, and the configuration of the combustion injector according to the other embodiment may be used. Illustrated in FIG.
- the axial flow path 53 formed in the main body 50 is partially divided into two axial flows in the axial direction of the main body 50 (the direction perpendicular to the paper surface in FIG. 12). It has a structure divided into roads 53a and 53b.
- the axial flow path 53 may have two or more structures divided into two divided axial flow paths 53a and 53b at different positions in the axial direction of the main body portion 50.
- the main body 50 is formed with radial flow paths 54a and 54b having one end communicating with each of the divided axial flow paths 53a and 53b and the other end opening to the outer surface 50c of the main body 50.
- only one of the radial flow paths 54a and 54b may be formed.
- the main body 50 is formed with an internal flow path 55 formed so as to pass between the divided axial flow paths 53a and 53b.
- the openings opened at both ends of the internal flow path 55 on the outer surface 50c of the main body 50 are the first opening 56 and the second opening 57, and the radial flow path 54a, on the outer surface 50c of the main body 50.
- the openings opened by each of the 54b are the third openings 58a and 58b.
- the main body 50 has different positions in the axial direction.
- Two or more internal flow paths 55 can be formed in.
- the peg 48 a part of the air flowing toward the peg 48 flows into the internal flow path 55 through the first opening 56, and the remaining air branches to both sides of the peg 48 and passes through the peg 48.
- the fuel injected from each of the third openings 58a and 58b branches to both sides of the peg 48 and is mixed with each of the air passing through the peg 48, and merges on the downstream side of the peg 48 in the direction of air flow. do.
- the air flowing out from the internal flow path 55 through the second opening 57 flows out toward the region on the back side of the peg 48 when viewed in the direction of air flow, so that the air flows out to the region on the back side of the peg 48. And even if the fuel tries to stay, it is swept away by the air flowing out from the second opening 57.
- the opening width of the second opening 57 in the circumferential direction about the axis L'of the main body 50 is smaller than the opening width of the first opening 56.
- the opening area of the second opening 57 is made smaller than the opening area of the first opening 56.
- the outer cross-sectional shape of the main bodies 30 and 50 is circular, but the cross-sectional shape is not limited to this shape, and any cross-sectional shape such as an ellipse, a polygon, or a wing shape may be used. ..
- the lines extending in the axial directions of the main bodies 30 and 50 through the center of gravity of any cross-sectional shape can be the axis lines L and L'of the main bodies 30 and 50, respectively.
- the fuel injector is A fuel injector (pegs 28, 48) having a main body (30, 50) extending in the axial direction.
- the main body (30, 50) is Axial flow paths (33, 53) formed so as to extend in the axial direction, and A radial flow path (34, 50c) formed so that one end communicates with the axial flow path (33, 53) and the other end opens to the outer surface (30c, 50c) of the main body (30, 50).
- the first opening (36,56) and the second opening (37,57) that open to the outer surface (30c, 50c) are included, and the first opening (36,56) to the second opening ( 37, 57) includes an internal flow path (35, 55) formed so as to extend inside the main body (30, 50).
- the first opening (36,56) and the second opening (37,57) are radial flow paths in the circumferential direction about the axis (L) of the main body (30, 50). (34, 54a, 54b) is located on the opposite side of the third opening (38, 58a, 58b) that opens to the outer surface (30c, 50c).
- the possibility of forming stagnation of air and fuel flow in the region on the downstream side of the fuel injector can be reduced, so that the reliability of the combustor can be improved.
- the fuel injector according to another aspect is the fuel injector of [1].
- the opening area of the second opening (37,57) is smaller than the opening area of the first opening (36,56).
- the fuel injector according to still another aspect is the fuel injector of [1] or [2].
- the axial opening width of the second opening (37,57) is smaller than the axial opening width of the first opening (36,56).
- the opening width in the circumferential direction of the second opening not to be smaller than the opening width in the circumferential direction of the first opening. Since the risk of stagnation of air and fuel flows can be reduced, the reliability of the combustor can be improved.
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [3].
- the main body portion (30) includes a tip end portion (30b) and a base end portion (30a).
- the internal flow path (35) includes a plurality of divided internal flow paths (35c, 35d, 35e) that do not communicate with each other in the axial direction.
- Each of the plurality of divided internal flow paths (35c, 35d, 35e) includes a first divided opening (36a, 36b, 36c) constituting the first opening (36).
- the opening area of the first divided opening (36c) of the divided internal flow path (35e) located closest to the tip (30b) is the other. It is larger than the opening area of the first divided opening (36a, 36b) of the divided internal flow path (35c, 35d).
- the main body portion in which a plurality of third openings are opened at different positions in the axial direction if the number of third openings in the vicinity of the tip portion is larger than the number of third openings in other positions, the vicinity of the tip portion The fuel injection amount in is larger than the fuel injection amount in other positions.
- the amount of air flowing into the divided internal flow path located at the position closest to the tip of the plurality of divided internal flow paths flows into the other divided internal flow paths.
- the fuel injector Since the amount of air that exceeds the amount of air and flows out from the split internal flow path closest to the tip is greater than the amount of air that flows out from the other split internal channels, the fuel injector near the tip The possibility of air and fuel flow stagnation is reduced by flushing the air and fuel that resides in the downstream region of the.
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [4].
- the main body portion (30) includes a tip end portion (30b) and a base end portion (30a).
- the internal flow path (35) includes a plurality of divided internal flow paths (35c, 35d, 35e) that do not communicate with each other in the axial direction.
- the plurality of divided internal channels (35c, 35d, 35e) each include a second divided opening (37a, 37b, 37c) constituting the second opening (37).
- the ratio of the opening area of each of the plurality of second divided openings (37a, 37b, 37c) to the average value of the opening areas of the plurality of second divided openings (37a, 37b, 37c) is 0.85 to 1. .2.
- the opening area of each second divided opening is almost the same. Then, the amount of air flowing out from each second division opening can be adjusted by the opening area of each first division opening corresponding to each second division opening, so that the design work of the fuel injector can be simplified. can.
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [5].
- the third opening (38) is located within the range in which the second opening (37) exists in the axial direction.
- the air flowing out from the internal flow path through the second opening is the region on the downstream side of the fuel injector at the position where the third opening exists in the axial direction. It is possible to reduce the possibility of forming stagnation of the air and fuel flow by flushing the air and fuel staying in the area on the downstream side of the fuel injector.
- the fuel injector according to still another aspect is the fuel injector of [6].
- the internal flow path (35) includes a plurality of divided internal flow paths (35c, 35d, 35e) that do not communicate with each other in the axial direction, and the plurality of divided internal flow paths (35c, 35d, 35e), respectively.
- the first divided opening (36a, 36b, 36c) constituting the first opening (36) and the second divided opening (37a, 37b, 37c) constituting the second opening (37) are included.
- the third openings (38a, 38b, 38c, 38d) in the range in which each of the plurality of second divided openings (37a, 37b, 37c) exists in the axial direction the opening area is the largest.
- the opening area of the second divided opening (37c) that defines the range in which the third opening (38a, 38b) is located is S 2L
- the opening area of the portion (36c) is S 1L
- the opening area of the second divided opening (37a, 37b) defining the range in which the other third opening (38c, 38d) is located is S 2S .
- the opening area of the first divided opening (36a, 36b) corresponding to the second divided opening (37a, 37b) is S 1S , (S 1L / S 2L )> (S 1S / S 2S ). ..
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [7].
- the axial opening width and the circumferential opening width of the first opening (36) are w 1a and w 1p , respectively, and the axial opening width and the circumferential direction of the second opening (37). If the opening widths of are w 2a and w 2p , respectively, then (w 1a / w 2a )> (w 1p / w 2p ).
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [8].
- the internal flow path (35) extends so as to surround the axial flow path (33) in the radial direction of the main body portion (30).
- the opening width in the circumferential direction of the second opening can be made as long as possible. If the opening width in the circumferential direction of the second opening is short, stagnation points are formed on both sides of the second opening in the circumferential direction. On the other hand, according to the configuration of the above [9], the possibility that a stagnation point is formed in the region on the downstream side of the fuel injector can be further reduced.
- the fuel injector according to still another aspect is the fuel injector of [9].
- the internal flow path (35) is A first flow path portion (35b1) extending in the circumferential direction from the first opening (36) toward the second opening (37), and A second flow path portion (35b2) extending in the circumferential direction from the end portion of the first flow path portion (35b1) opposite to the first opening portion (36) to the second opening portion (37).
- the angle ( ⁇ b) formed by the extending direction (R2) of the second flow path portion (35b2) with respect to the axis (L) is The extending direction (R1) of the first flow path portion (35b1) is smaller than the angle ( ⁇ a) formed with respect to the axis (L).
- the fuel injector can be formed so that the opening area of the second opening is smaller than the opening area of the first opening. Further, according to this configuration, the second opening can be positioned at the same position in the axial direction as the third opening in which the fuel is injected.
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [10].
- the internal flow path (35) is configured such that the flow path area decreases from the first opening (36) toward the second opening (37).
- the flow velocity of the air flowing through the second flow path portion increases toward the second opening portion, so that the ability to push out the air and fuel staying in the region on the downstream side of the fuel injector is increased. , The possibility of forming stagnation of air and fuel flow can be further reduced.
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [11].
- the internal flow path is configured such that the opening width of the flow path cross section in the axial direction decreases from the first opening to the second opening.
- the fuel injector according to still another aspect is the fuel injector according to any one of [1] to [12].
- the internal flow path (35) includes two branch flow paths (35a, 35b) extending in opposite directions in the circumferential direction from the first opening (36) toward the second opening (37). ..
- the opening width in the circumferential direction of the second opening can be made as long as possible. If the opening width in the circumferential direction of the second opening is short, stagnation of air and fuel flows is formed on both sides of the second opening in the circumferential direction. On the other hand, according to the configuration of the above [13], the possibility of stagnation being formed in the region on the downstream side of the fuel injector can be further reduced.
- the combustor according to one aspect is The fuel injector (28, 48) according to any one of [1] to [13] is provided.
- the fuel injector of the present disclosure by using any of the fuel injectors [1] to [13], the possibility of forming stagnation of air and fuel flow can be reduced. It is possible to prevent the configuration of the combustor from becoming complicated.
- the gas turbine according to one aspect is Compressor (2) and With the combustor (3) of [14], It is equipped with a turbine (4).
- the possibility of forming stagnation of air and fuel flow can be reduced, so that the configuration of the gas turbine becomes complicated. Can be prevented.
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Abstract
Description
本願は、2020年6月26日に日本国特許庁に出願された特願2020-110413号に基づき優先権を主張し、その内容をここに援用する。
図1に示されるように、本開示の一実施形態に係るガスタービン1は、圧縮機2と、複数の燃焼器3(図1には1つの燃焼器3のみが図示されている)と、タービン4とを備えている。圧縮機2は、外部の空気である大気を吸入して圧縮し、圧縮された空気を燃焼器3に供給するように構成されている。燃焼器3は、圧縮機2により圧縮された空気を用いて、外部から供給された燃料を燃焼させることにより、燃焼ガスを生成するように構成されている。タービン4は、燃焼器3により生成された燃焼ガスの供給を受けて回転駆動力を発生させ、発生した回転駆動力を圧縮機2及び例えば発電機6等の外部機器に出力するように構成されている。
図3に示されるように、ペグ28は、基端部30aから先端部30bまで延びる本体部30を有している。図4に示されるように、本体部30は、内管31と外管32とからなる二重管構造を有し、本体部30には、軸方向に延びるように形成された軸方向流路33と、本体部30の外表面30cに開口する第1開口部36及び第2開口部37を含むとともに第1開口部36から第2開口部37まで本体部30の内部を延びるように形成された内部流路35とが形成されている。内部流路35は、本体部30の軸線Lを中心とする周方向(以下、単に「周方向」という)の内側に軸方向流路33を囲むように延びるように構成され、第1開口部36から第2開口部37に向かって周方向において反対方向に延びる2つの分岐流路部35a,35bを含んでいる。尚、軸方向流路33と内部流路35とは連通していない。
図1に示されるように、ガスタービン1の運転中は、圧縮機2によって圧縮された空気が生成され、この空気が燃焼器3内に導入される。燃焼器3内では、圧縮された空気に燃料が混合された後、混合気を燃焼させ、高温高圧の燃焼ガスを生成する。燃焼ガスはタービン4に導入されてタービン4を駆動し、タービン4で発生した回転駆動力を圧縮機2及び外部機器(例えば発電機6等)に出力する。
図9では、分割内部流路35cを画定する内壁面35c1及び35c2と、分割内部流路35dを画定する内壁面35d1及び35d2と、分割内部流路35eを画定する内壁面35e1及び35e2とはそれぞれ、平らな面として描かれているが、平らな面に限定するものではなく、滑らかな湾曲面であってもよいし、段差や凹凸等が設けられた面であってもよい。
軸方向に延びる本体部(30,50)を有する燃料噴射器(ペグ28,48)であって、
前記本体部(30,50)は、
前記軸方向に延びるように形成された軸方向流路(33,53)と、
一端が前記軸方向流路(33,53)に連通するとともに他端が前記本体部(30,50)の外表面(30c,50c)に開口するように形成された径方向流路(34,54a,54b)と、
前記外表面(30c,50c)に開口する第1開口部(36,56)及び第2開口部(37,57)を含むとともに前記第1開口部(36,56)から前記第2開口部(37,57)まで前記本体部(30,50)の内部を延びるように形成された内部流路(35,55)と
を含み、
前記第1開口部(36,56)と前記第2開口部(37,57)とは、前記本体部(30,50)の軸線(L)を中心とする周方向において、前記径方向流路(34,54a,54b)が前記外表面(30c,50c)に開口する第3開口部(38,58a,58b)に対して反対側に位置する。
前記第2開口部(37,57)の開口面積は前記第1開口部(36,56)の開口面積よりも小さい。
前記第2開口部(37,57)の前記軸方向における開口幅は前記第1開口部(36,56)の前記軸方向における開口幅よりも小さい。
前記本体部(30)は先端部(30b)及び基端部(30a)を含み、
前記内部流路(35)は、前記軸方向において互いに連通しない複数の分割内部流路(35c,35d,35e)を含み、
前記複数の分割内部流路(35c,35d,35e)はそれぞれ、前記第1開口部(36)を構成する第1分割開口部(36a,36b,36c)を含み、
前記複数の分割内部流路(35c,35d,35e)のうち最も前記先端部(30b)に近い位置にある分割内部流路(35e)の前記第1分割開口部(36c)の開口面積が他の分割内部流路(35c,35d)の前記第1分割開口部(36a,36b)の開口面積よりも大きい。
前記本体部(30)は先端部(30b)及び基端部(30a)を含み、
前記内部流路(35)は、前記軸方向において互いに連通しない複数の分割内部流路(35c,35d,35e)を含み、
前記複数の分割内部流路(35c,35d,35e)はそれぞれ、前記第2開口部(37)を構成する第2分割開口部(37a,37b,37c)を含み、
複数の前記第2分割開口部(37a,37b,37c)の開口面積の平均値に対する前記複数の第2分割開口部(37a,37b,37c)のそれぞれの開口面積の比が0.85~1.2である。
前記第3開口部(38)は、前記軸方向において前記第2開口部(37)が存在する範囲内に位置する。
前記内部流路(35)は、前記軸方向において互いに連通しない複数の分割内部流路(35c,35d,35e)を含み、前記複数の分割内部流路(35c,35d,35e)はそれぞれ、前記第1開口部(36)を構成する第1分割開口部(36a,36b,36c)と、前記第2開口部(37)を構成する第2分割開口部(37a,37b,37c)とを含み、
前記軸方向において複数の前記第2分割開口部(37a,37b,37c)のそれぞれが存在する前記範囲内の前記第3開口部(38a,38b,38c,38d)のうち、最も開口面積の大きい第3開口部(38a,38b)が位置する前記範囲を画定する前記第2分割開口部(37c)の開口面積をS2Lとし、この第2分割開口部(37c)に対応する第1分割開口部(36c)の開口面積をS1Lとし、その他の第3開口部(38c,38d)が位置する前記範囲を画定する前記第2分割開口部(37a,37b)の開口面積をS2Sとし、この第2分割開口部(37a,37b)に対応する第1分割開口部(36a,36b)の開口面積をS1Sとすると、(S1L/S2L)>(S1S/S2S)である。
前記第1開口部(36)の前記軸方向の開口幅及び前記周方向の開口幅をそれぞれw1a及びw1pとし、前記第2開口部(37)の前記軸方向の開口幅及び前記周方向の開口幅をそれぞれw2a及びw2pとすると、(w1a/w2a)>(w1p/w2p)である。
前記内部流路(35)は、前記軸方向流路(33)を前記本体部(30)の径方向の内側に囲むように延びる。
前記内部流路(35)は、
前記第1開口部(36)から前記第2開口部(37)へ向かって前記周方向に延びる第1流路部(35b1)と、
前記第1開口部(36)とは反対側の前記第1流路部(35b1)の端部から前記第2開口部(37)まで前記周方向に延びる第2流路部(35b2)と
を含み、
前記第1開口部(36)から前記第2開口部(37)まで前記第1流路部(35b1)及び前記第2流路部(35b2)の前記軸線(L)に沿った切断面(CS)と、前記軸線(L)とを仮想平面上に展開した展開形状において、前記第2流路部(35b2)の延びる方向(R2)が前記軸線(L)に対してなす角度(θb)は、前記第1流路部(35b1)の延びる方向(R1)が前記軸線(L)に対してなす角度(θa)よりも小さい。
前記内部流路(35)は、前記第1開口部(36)から前記第2開口部(37)に向かって流路面積が減少するように構成されている。
前記第内部流路は、前記第1開口部から前記第2開口部に向かって流路断面の前記軸方向における開口幅が減少するように構成されている。
前記内部流路(35)は、前記第1開口部(36)から前記第2開口部(37)に向かって前記周方向において反対方向に延びる2つの分岐流路部(35a,35b)を含む。
[1]~[13]のいずれかの燃料噴射器(28,48)を備える。
圧縮機(2)と、
[14]の燃焼器(3)と、
タービン(4)と
を備える。
2 圧縮機
3 燃焼器
4 タービン
28 ペグ(燃料噴射器)
30 本体部
30a (本体部の)基端部
30b (本体部の)先端部
30c (本体部の)外表面
33 軸方向流路
34 径方向流路
34a 径方向流路
34b 径方向流路
34c 径方向流路
34d 径方向流路
35 内部流路
35a 分岐流路部
35b 分岐流路部
35b1 第1流路部
35b2 第2流路部
35c 分割内部流路
35d 分割内部流路
35e 分割内部流路
36 第1開口部
36a 第1分割開口部
36b 第1分割開口部
36c 第1分割開口部
37 第2開口部
37a 第2分割開口部
37b 第2分割開口部
37c 第2分割開口部
38 第3開口部
38a 第3開口部
38b 第3開口部
38c 第3開口部
38d 第3開口部
48 ペグ(燃料噴射器)
50 本体部
50c (本体部の)外表面
53 軸方向流路
54 径方向流路
54a 径方向流路
54b 径方向流路
55 内部流路
56 第1開口部
57 第2開口部
58a 第3開口部
58b 第3開口部
CS 切断面
L (本体部の)軸線
L’ (本体部の)軸線
Claims (15)
- 軸方向に延びる本体部を有する燃料噴射器であって、
前記本体部は、
前記軸方向に延びるように形成された軸方向流路と、
一端が前記軸方向流路に連通するとともに他端が前記本体部の外表面に開口するように形成された径方向流路と、
前記外表面に開口する第1開口部及び第2開口部を含むとともに前記第1開口部から前記第2開口部まで前記本体部の内部を延びるように形成された内部流路と
を含み、
前記第1開口部と前記第2開口部とは、前記本体部の軸線を中心とする周方向において、前記径方向流路が前記外表面に開口する第3開口部に対して反対側に位置する燃料噴射器。 - 前記第2開口部の開口面積は前記第1開口部の開口面積よりも小さい、請求項1に記載の燃料噴射器。
- 前記第2開口部の前記軸方向における開口幅は前記第1開口部の前記軸方向における開口幅よりも小さい、請求項1または2に記載の燃料噴射器。
- 前記本体部は先端部及び基端部を含み、
前記内部流路は、前記軸方向において互いに連通しない複数の分割内部流路を含み、
前記複数の分割内部流路はそれぞれ、前記第1開口部を構成する第1分割開口部を含み、
前記複数の分割内部流路のうち最も前記先端部に近い位置にある分割内部流路の前記第1分割開口部の開口面積が他の分割内部流路の前記第1分割開口部の開口面積よりも大きい、請求項1~3のいずれか一項に記載の燃料噴射器。 - 前記本体部は先端部及び基端部を含み、
前記内部流路は、前記軸方向において互いに連通しない複数の分割内部流路を含み、
前記複数の分割内部流路はそれぞれ、前記第2開口部を構成する第2分割開口部を含み、
複数の前記第2分割開口部の開口面積の平均値に対する前記複数の第2分割開口部のそれぞれの開口面積の比が0.8~1.2である、請求項1~4のいずれか一項に記載の燃料噴射器。 - 前記第3開口部は、前記軸方向において前記第2開口部が存在する範囲内に位置する、請求項1~5のいずれか一項に記載の燃料噴射器。
- 前記内部流路は、前記軸方向において互いに連通しない複数の分割内部流路を含み、前記複数の分割内部流路はそれぞれ、前記第1開口部を構成する第1分割開口部と、前記第2開口部を構成する第2分割開口部とを含み、
前記軸方向において複数の前記第2分割開口部のそれぞれが存在する前記範囲内の前記第3開口部のうち、最も開口面積の大きい第3開口部が位置する前記範囲を画定する前記第2分割開口部の開口面積をS2Lとし、この第2分割開口部に対応する第1分割開口部の開口面積をS1Lとし、その他の第3開口部が位置する前記範囲を画定する前記第2分割開口部の開口面積をS2Sとし、この第2分割開口部に対応する第1分割開口部の開口面積をS1Sとすると、(S1L/S2L)>(S1S/S2S)である、請求項6に記載の燃料噴射器。 - 前記第1開口部の前記軸方向の開口幅及び前記周方向の開口幅をそれぞれw1a及びw1pとし、前記第2開口部の前記軸方向の開口幅及び前記周方向の開口幅をそれぞれw2a及びw2pとすると、(w1a/w2a)>(w1p/w2p)である、請求項1~7のいずれか一項に記載の燃料噴射器。
- 前記内部流路は、前記軸方向流路を前記本体部の径方向の内側に囲むように延びる、請求項1~8のいずれか一項に記載の燃料噴射器。
- 前記内部流路は、
前記第1開口部から前記第2開口部へ向かって前記周方向に延びる第1流路部と、
前記第1開口部とは反対側の前記第1流路部の端部から前記第2開口部まで前記周方向に延びる第2流路部と
を含み、
前記第1開口部から前記第2開口部まで前記第1流路部及び前記第2流路部の前記軸線に沿った切断面と、前記軸線とを仮想平面上に展開した展開形状において、前記第2流路部の延びる方向が前記軸線に対してなす角度は、前記第1流路部の延びる方向が前記軸線に対してなす角度よりも小さい、請求項9に記載の燃料噴射器。 - 前記内部流路は、前記第1開口部から前記第2開口部に向かって流路面積が減少するように構成されている、請求項1~10のいずれか一項に記載の燃料噴射器。
- 前記内部路部は、前記第1開口部から前記第2開口部に向かって流路断面の前記軸方向における開口幅が減少するように構成されている、請求項1~11のいずれか一項に記載の燃料噴射器。
- 前記内部流路は、前記第1開口部から前記第2開口部に向かって前記周方向において反対方向に延びる2つの分岐流路部を含む、請求項1~12のいずれか一項に記載の燃料噴射器。
- 請求項1~13のいずれか一項に記載の燃料噴射器を備える燃焼器。
- 圧縮機と、
請求項14に記載の燃焼器と、
タービンと
を備えるガスタービン。
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KR1020227043997A KR20230008224A (ko) | 2020-06-26 | 2021-06-21 | 연료 분사기 및 이 연료 분사기를 구비하는 연소기 및 이 연소기를 구비하는 가스 터빈 |
CN202180043832.XA CN115803566A (zh) | 2020-06-26 | 2021-06-21 | 燃料喷射器、具备该燃料喷射器的燃烧器及具备该燃烧器的燃气轮机 |
DE112021002636.4T DE112021002636T5 (de) | 2020-06-26 | 2021-06-21 | Brennstoffeinspritzdüse, brennkammer mit der brennstoffeinspritzdüse, und gasturbine mit der brennkammer |
US17/928,771 US20230228421A1 (en) | 2020-06-26 | 2021-06-21 | Fuel injector, combustor including the fuel injector, and gas turbine including the combustor |
JP2022531966A JP7438354B2 (ja) | 2020-06-26 | 2021-06-21 | 燃料噴射器及びこの燃料噴射器を備える燃焼器並びにこの燃焼器を備えるガスタービン |
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Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008089298A (ja) * | 2006-10-03 | 2008-04-17 | General Electric Co <Ge> | 天然ガススワール安定化ノズル及び方法に対する液体燃料による機能強化 |
JP2009270816A (ja) * | 2008-05-09 | 2009-11-19 | General Electric Co <Ge> | ガスタービンエンジン用の燃料ノズル及びそれを製作する方法 |
JP2012132673A (ja) * | 2010-12-17 | 2012-07-12 | General Electric Co <Ge> | ペグなし二次燃料ノズル |
JP2017180267A (ja) * | 2016-03-30 | 2017-10-05 | 三菱日立パワーシステムズ株式会社 | ガスタービン |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4198815A (en) * | 1975-12-24 | 1980-04-22 | General Electric Company | Central injection fuel carburetor |
JP2001280641A (ja) | 2000-03-31 | 2001-10-10 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器、および、ガスタービン燃焼器における燃料と空気の混合方法 |
JP2002031343A (ja) | 2000-07-13 | 2002-01-31 | Mitsubishi Heavy Ind Ltd | 燃料噴出部材、バーナ、燃焼器の予混合ノズル、燃焼器、ガスタービン及びジェットエンジン |
US6837052B2 (en) | 2003-03-14 | 2005-01-04 | Power Systems Mfg, Llc | Advanced fuel nozzle design with improved premixing |
FR2873408B1 (fr) * | 2004-07-23 | 2008-10-17 | Snecma Moteurs Sa | Turboreacteur avec un ecran de protection de la rampe de carburant d'un anneau bruleur, l'anneau bruleur et l'ecran de protection |
DE102004041272B4 (de) * | 2004-08-23 | 2017-07-13 | General Electric Technology Gmbh | Hybridbrennerlanze |
JP2006144759A (ja) | 2004-11-25 | 2006-06-08 | Toyota Central Res & Dev Lab Inc | ガスタービン用予混合燃焼器およびその燃料供給制御方法 |
US20060191268A1 (en) | 2005-02-25 | 2006-08-31 | General Electric Company | Method and apparatus for cooling gas turbine fuel nozzles |
US7654091B2 (en) * | 2006-08-30 | 2010-02-02 | General Electric Company | Method and apparatus for cooling gas turbine engine combustors |
US20100192582A1 (en) | 2009-02-04 | 2010-08-05 | Robert Bland | Combustor nozzle |
US8528338B2 (en) * | 2010-12-06 | 2013-09-10 | General Electric Company | Method for operating an air-staged diffusion nozzle |
EP3076081A1 (en) * | 2015-04-01 | 2016-10-05 | Siemens Aktiengesellschaft | Swirler, burner and combustor for a gas turbine engine |
CN106402934A (zh) * | 2016-11-21 | 2017-02-15 | 深圳智慧能源技术有限公司 | 燃气轮机燃烧室及其喷嘴 |
JP2020110413A (ja) | 2019-01-15 | 2020-07-27 | 株式会社ソフイア | 遊技機 |
-
2021
- 2021-06-21 WO PCT/JP2021/023368 patent/WO2021261431A1/ja active Application Filing
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- 2021-06-21 JP JP2022531966A patent/JP7438354B2/ja active Active
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Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008089298A (ja) * | 2006-10-03 | 2008-04-17 | General Electric Co <Ge> | 天然ガススワール安定化ノズル及び方法に対する液体燃料による機能強化 |
JP2009270816A (ja) * | 2008-05-09 | 2009-11-19 | General Electric Co <Ge> | ガスタービンエンジン用の燃料ノズル及びそれを製作する方法 |
JP2012132673A (ja) * | 2010-12-17 | 2012-07-12 | General Electric Co <Ge> | ペグなし二次燃料ノズル |
JP2017180267A (ja) * | 2016-03-30 | 2017-10-05 | 三菱日立パワーシステムズ株式会社 | ガスタービン |
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KR20230008224A (ko) | 2023-01-13 |
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