TWI804885B - Gas turbine premixing tube structure - Google Patents

Gas turbine premixing tube structure Download PDF

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Publication number
TWI804885B
TWI804885B TW110120954A TW110120954A TWI804885B TW I804885 B TWI804885 B TW I804885B TW 110120954 A TW110120954 A TW 110120954A TW 110120954 A TW110120954 A TW 110120954A TW I804885 B TWI804885 B TW I804885B
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air holes
air
gas turbine
premixing tube
end side
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TW110120954A
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Chinese (zh)
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TW202206748A (en
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潞宇 王
俊介 西江
健斗 黛
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日商三井易艾斯機械有限公司
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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
    • 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
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

本發明提供一種在生成燃燒氣體與空氣之混合氣體時，生成均勻而充分被稀釋之混合氣體之燃氣渦輪之預混合管結構。 於預混合管1之圓筒狀之本體部1a形成空氣孔1a1、1a2、1a3、1a4。使形成於最上游側之空氣孔1a1之數量多於其他之空氣孔1a2、1a3、1a4之數量。空氣孔1a2、1a3、1a4形成於相互不同之錯開狀之位置。本體部1a之下游側，在連續於以逐漸成為小徑之方式收窄之圓錐形本體部1c之傾斜管部1e，指向燃燒器內筒103b之中央部而設置開口1d，使混合氣體向源自先導燃料之火焰噴射。The present invention provides a premixing tube structure of a gas turbine that generates a uniform and fully diluted mixed gas when the mixed gas of combustion gas and air is generated. Air holes 1a1 , 1a2 , 1a3 , and 1a4 are formed in the cylindrical body portion 1a of the premixing tube 1 . The number of air holes 1a1 formed on the most upstream side is larger than the number of other air holes 1a2, 1a3, and 1a4. The air holes 1a2, 1a3, and 1a4 are formed at positions different from each other in a staggered shape. On the downstream side of the main body part 1a, the inclined pipe part 1e, which is continuous with the conical main body part 1c which narrows gradually into a small diameter, is directed to the central part of the burner inner cylinder 103b and provided with an opening 1d, so that the mixed gas flows to the source. Flame injection from pilot fuel.

Description

燃氣渦輪之預混合管結構Gas turbine premixing tube structure

本發明係關於一種配置於燃氣渦輪之預混合式燃燒器之預混合管結構。 The present invention relates to a premix tube structure arranged in a premix combustor of a gas turbine.

於空氣氛圍中噴射燃燒氣體之擴散燃燒中，由於燃燒氣體與空氣未充分混合而以高濃度之狀態進行燃燒，故燃燒溫度增高，NOx(氮氧化物)之排出濃度增高。因此，藉由將水蒸氣或水噴射於燃燒區域而降低燃燒溫度來謀求NOx濃度之降低。 In the diffusion combustion of injecting combustion gas in the air atmosphere, since the combustion gas and air are not fully mixed and burn in a state of high concentration, the combustion temperature increases and the emission concentration of NOx (nitrogen oxides) increases. Therefore, the NOx concentration is reduced by injecting water vapor or water into the combustion area to lower the combustion temperature.

然而，相對燃料之供給量需要較多之水量，有使燃氣渦輪設備之效率降低之虞。 However, a large amount of water is required relative to the amount of fuel supplied, which may lower the efficiency of the gas turbine plant.

因此，採用不噴射水蒸氣或水而可排出低NOx之稀釋預混合燃燒。稀釋預混合燃燒係使燃燒氣體與空氣混合而將稀釋成低濃度之混合氣體供給至燃燒區域，進行燃燒。由於該預混合氣體之燃燒溫度降低，故NOx之生成被抑制從而排出濃度較低之NOx。 Therefore, a diluted premixed combustion that can emit low NOx without injecting water vapor or water is adopted. Diluted premixed combustion mixes the combustion gas with air and supplies the mixed gas diluted to a low concentration to the combustion area for combustion. Since the combustion temperature of the premixed gas is lowered, the generation of NOx is suppressed and a lower concentration of NOx is discharged.

為了提高此種稀釋預混合燃燒之混合效率，例如，專利文獻1中，作為可以稀薄之混合氣體進行穩定之燃燒，可減少氮氧化物之排出之燃氣渦 輪燃燒器，提案如下結構：自以特定量***於襯管而配置之預蒸發預混合管之前端在特定位置之周圍於周向形成有複數之燃燒氣體供給孔之開口。 In order to improve the mixing efficiency of this kind of diluted premixed combustion, for example, in Patent Document 1, as a gas vortex that can perform stable combustion with a lean mixture, it can reduce the emission of nitrogen oxides. A wheel combustor proposes a structure in which a plurality of openings of combustion gas supply holes are formed in the circumferential direction around a specific position from the front end of the pre-evaporation pre-mixing tube arranged by inserting a specific amount into the liner.

又，專利文獻2中提案如下結構：自預混合管之周壁面之孔流入至燃燒器內之空氣，在燃燒器內形成圍繞軸向流之旋流，火焰被保持於遠離燃燒器頂部之位置。 In addition, Patent Document 2 proposes a structure in which the air flowing into the burner from the hole in the peripheral wall of the premixing tube forms a swirling flow around the axial flow in the burner, and the flame is kept at a position away from the top of the burner. .

又，專利文獻3中，揭示一種燃氣渦輪燃燒器，其於外筒體之內部具有燃燒筒與預混合管，該預混合管係由具備在預混合管之上部周壁內之貫通筒狀之內壁之間的間隙產生旋流之孔之上部周壁與下部周壁構成，於內壁之頂部中央配置第1壓力噴射噴嘴、於下部周壁以等角度間隔配置5個第2壓力噴射噴嘴。自各第2壓力噴射噴嘴向中心噴射之燃料，隨著自間隙流向燃燒筒之空氣之旋流，在燃燒器之上部區域於半徑方向擴展分散，由於長時間滯留而提前蒸發‧著火而完全燃燒。 Also, in Patent Document 3, a gas turbine combustor is disclosed, which has a combustion cylinder and a premixing tube inside the outer cylinder. The gap between the inner walls creates a swirling hole with an upper peripheral wall and a lower peripheral wall. The first pressure injection nozzle is arranged in the center of the top of the inner wall, and five second pressure injection nozzles are arranged at equal angular intervals on the lower peripheral wall. The fuel injected from each second pressure injection nozzle to the center expands and disperses in the radial direction in the upper area of the burner along with the swirling flow of air flowing from the gap to the combustion cylinder, and due to long-term residence, it evaporates in advance and ignites completely to burn completely.

[先前技術文獻] [Prior Art Literature] [專利文獻] [Patent Document]

[專利文獻1]日本特開平10-160163號公報 [Patent Document 1] Japanese Patent Application Laid-Open No. 10-160163

[專利文獻2]日本特開2009-198054號公報 [Patent Document 2] Japanese Patent Laid-Open No. 2009-198054

[專利文獻3]日本特開2012-247135號公報 [Patent Document 3] Japanese Unexamined Patent Publication No. 2012-247135

上述之專利文獻1~專利文獻3所揭示之燃氣渦輪燃燒器，係對空氣賦予旋流而促進與燃料之混合，且不產生逆火者。 The gas turbine combustors disclosed in the above-mentioned Patent Document 1 to Patent Document 3 impart swirl flow to the air to promote mixing with the fuel, and do not generate backfire.

然而，該等燃氣渦輪燃燒器主要係使產生旋流者，用以促進混合。但，混合濃度分佈之狀況不明，是否已實現燃燒氣體之濃度均勻化不明。因此，有在高濃度之狀態燃燒之虞，且有NOx之排出濃度部分增高之虞。 However, these gas turbine combustors are primarily those that create swirl to facilitate mixing. However, the status of the mixed concentration distribution is unclear, and it is unclear whether the concentration of the combustion gas has been uniformed. Therefore, there is a possibility of burning in a high-concentration state, and there is a possibility that the emission concentration of NOx will partially increase.

因此，本發明之目的在於提供一種實現促進燃燒氣體與空氣之混合、實現燃燒氣體之濃度均勻化、高效進行稀釋預混合燃燒之燃氣渦輪之預混合管結構。 Therefore, the object of the present invention is to provide a premixer tube structure of a gas turbine that promotes the mixing of combustion gas and air, realizes uniform concentration of combustion gas, and efficiently performs dilution premixed combustion.

為達成上述目的，本發明之燃氣渦輪之預混合管結構之特徵為，其係於燃燒器內筒之中央部配置先導燃料用噴嘴，於該先導燃料用噴嘴之周圍配置複數根主燃料用噴嘴，將該主燃料用噴嘴保持於基端部，將使自該主燃料用噴嘴噴射之主燃料與空氣混合之混合氣體自前端部向燃燒器內筒噴射之筒狀之預混合管，且於周壁周向排列有使內外連通而引入空氣之複數個空氣孔，且該空氣孔於軸向配置有複數行。 In order to achieve the above object, the gas turbine premixing tube structure of the present invention is characterized in that a pilot fuel nozzle is arranged in the center of the combustor inner cylinder, and a plurality of main fuel nozzles are arranged around the pilot fuel nozzle. The nozzle is a cylindrical premixing tube that holds the main fuel nozzle at the base end, and injects the mixed gas of the main fuel and air injected from the main fuel nozzle into the inner cylinder of the burner from the front end, and A plurality of air holes for connecting the inside and the outside and introducing air are arranged in the circumferential direction of the peripheral wall, and the air holes are arranged in a plurality of rows in the axial direction.

由於自周壁之周圍引入預混合用空氣，故自主燃料用噴嘴噴射之燃燒氣體與空氣混合，噴射至燃燒器內筒。 Since pre-mixing air is introduced from the periphery of the peripheral wall, the combustion gas injected from the main fuel nozzle is mixed with air and injected into the inner cylinder of the burner.

又，上述之燃氣渦輪之預混合管結構，較佳係上述空氣孔以錯開狀排列。 In addition, in the premixing tube structure of the above-mentioned gas turbine, it is preferable that the above-mentioned air holes are arranged in a staggered manner.

藉由以錯開狀配置，於軸向鄰接之空氣孔在周向之位置偏移。因 此，引入空氣之位置不同，在基端部側即上游側，有燃燒氣體通過不存在空氣孔之位置時，燃燒氣體不會與空氣充分混合。該混合不充分之燃燒氣體向軸向流動而通過下游側之空氣孔所面對之位置時，促進與空氣之混合。因此，通過上游側未被稀釋之燃燒氣體在下游側被稀釋，藉此根據向軸向流動而確實地被稀釋。 By being arranged in a staggered shape, the positions of the adjacent air holes in the axial direction are shifted in the circumferential direction. because Here, depending on the position where the air is introduced, on the base end side, that is, on the upstream side, when the combustion gas passes through a position where there are no air holes, the combustion gas will not be sufficiently mixed with the air. When the insufficiently mixed combustion gas flows in the axial direction and passes through the position facing the air holes on the downstream side, mixing with the air is promoted. Therefore, the combustion gas that has passed through the upstream side and is not diluted is diluted on the downstream side, thereby being surely diluted by flowing in the axial direction.

又，上述之燃氣渦輪之預混合管結構，較佳係上述空氣孔在基端部側於周向配置之數量多於在前端部側於周向配置之數量。 In addition, in the above gas turbine premixer tube structure, it is preferable that the number of the air holes arranged in the circumferential direction on the base end side is greater than the number arranged on the front end side in the circumferential direction.

使配置於周向之空氣孔之數量，在基端部側(上游側)多於在前端部側(下游側)。 The number of air holes arranged in the circumferential direction is made larger on the base end side (upstream side) than on the front end side (downstream side).

在基端部側為供給燃燒氣體而供給大量空氣使其混合較為理想，故可於基端部側形成多個空氣孔吸引空氣。 It is desirable to supply a large amount of air and mix it for supplying the combustion gas on the base end side, so a plurality of air holes can be formed on the base end side to suck air.

又，在前端部側對燃燒氣體經稀釋之混合氣體供給空氣，故不需要如基端部側般大量之空氣。因此，設前端部側之空氣孔少於基端部側。 In addition, air is supplied to the mixed gas in which the combustion gas has been diluted on the front end side, so a large amount of air is not required as on the base end side. Therefore, the number of air holes on the front end side is smaller than that on the base end side.

又，上述之燃氣渦輪之預混合管結構，較佳係上述空氣孔之開口面積在基端部側設為較大，在前端部側設為較小。 In addition, in the premixer tube structure of the above-mentioned gas turbine, it is preferable that the opening area of the air hole is set larger on the base end side and smaller on the front end side.

藉由使空氣孔之開口面積在基端部側較大，可吸引大量之空氣，促進燃燒氣體之稀釋。 By making the opening area of the air hole larger at the base end side, a large amount of air can be sucked in, and the dilution of the combustion gas can be promoted.

又，上述之燃氣渦輪之預混合管結構，較佳係與筒狀之軸正交之面 之開口面積，使前端部側之開口面積小於自基端部側至本體部之開口面積。 In addition, the premixing tube structure of the above-mentioned gas turbine is preferably a plane perpendicular to the axis of the cylinder. The opening area is such that the opening area on the front end side is smaller than the opening area from the base end side to the main body.

使對於筒狀之預混合管之橫剖面之開口面積於前端部側較小，並增大自前端部向燃燒器內筒噴射之混合氣體之流速。因此，可防止燃燒器內筒內之燃燒之逆火之產生。 The opening area of the cross section of the cylindrical premixing tube is made smaller on the front end side, and the flow velocity of the mixed gas injected from the front end to the inner cylinder of the burner is increased. Therefore, it is possible to prevent backfire of the combustion inside the burner inner cylinder.

根據本發明之燃氣渦輪之預混合管結構，可高效地降低混合氣體之濃度且可均勻化，進而可抑制燃燒導致之NOx之產生。又，由於通過預混合管之側壁供給空氣，故相較於自軸向之基端部側之開口引入空氣之結構，可減小預混合管與頂蓋之間隔，從而可實現燃氣渦輪之小型化。 According to the premixing tube structure of the gas turbine of the present invention, the concentration of the mixed gas can be effectively reduced and homogenized, thereby suppressing the generation of NOx caused by combustion. In addition, since the air is supplied through the side wall of the premixing tube, compared with the structure in which air is introduced from the opening on the base end side in the axial direction, the distance between the premixing tube and the top cover can be reduced, thereby realizing the gas turbine. miniaturization.

1:預混合管 1: premix tube

1a:本體部 1a: Body part

1a1:空氣孔 1a1: air holes

1a2:空氣孔 1a2: air holes

1a3:空氣孔 1a3: air holes

1a4:空氣孔 1a4: air hole

1b:底板 1b: Bottom plate

1c:圓錐形本體部 1c: Conical body part

1d:開口 1d: opening

1e:傾斜管部 1e: Inclined tube

2:預混合管 2: pre-mixing tube

2a:本體部 2a: Body part

2a1:空氣孔 2a1: air holes

2a2:空氣孔 2a2: air holes

2a3:空氣孔 2a3: air holes

2a4:空氣孔 2a4: air holes

2b:蓋體 2b: Cover

2c:連續本體部 2c: continuous body

2d:開口 2d: opening

2e:傾斜管部 2e: Inclined tube

4:預混合管 4: Premixing tube

4a:上部開口 4a: Upper opening

11:噴嘴支持管 11: Nozzle support pipe

11a:密封件 11a: Seal

100:燃氣渦輪 100: gas turbine

101:空氣吸入口 101: Air suction port

101a:進氣導流板 101a: Air intake deflector

102:壓縮機 102: Compressor

103:燃燒器 103: Burner

103a:燃燒器外筒 103a: Burner outer cylinder

103b:燃燒器內筒 103b: Burner inner cylinder

104:渦輪 104: turbo

105:主軸 105:Spindle

106:排氣管道 106: exhaust pipe

110:主燃料用噴嘴 110: Nozzle for main fuel

111:先導燃料用噴嘴 111: Nozzle for pilot fuel

112:頂蓋 112: top cover

C:軸 C: axis

T1:基端部 T1: base end

T2:前端部 T2: front end

圖1係顯示具備本發明之第一實施形態之結構之燃氣渦輪之預混合管之概略之立體圖。 Fig. 1 is a schematic perspective view showing a premixer tube of a gas turbine having a structure according to a first embodiment of the present invention.

圖2係圖1所示之燃氣渦輪之預混合管之前視圖。 Fig. 2 is a front view of the premixing tube of the gas turbine shown in Fig. 1 .

圖3係沿圖2之3-3線切斷而顯示之剖視圖。 Fig. 3 is a cross-sectional view taken along line 3-3 in Fig. 2 .

圖4係圖1所示之燃氣渦輪之預混合管之俯視圖。 Fig. 4 is a top view of the premixing tube of the gas turbine shown in Fig. 1 .

圖5係將圖1所示之燃氣渦輪之預混合管於與軸正交之面切斷而顯示之剖視圖，(A)係圖2之5A-5A線剖視圖，(B)係5B-5B線剖視圖，(C)係5C-5C線剖視圖，(D)係5D-5D線剖視圖。 Fig. 5 is a cross-sectional view showing the premixing tube of the gas turbine shown in Fig. 1 cut on a plane perpendicular to the axis, (A) is a cross-sectional view of line 5A-5A in Fig. 2 , and (B) is a cross-sectional view of line 5B-5B Line sectional view, (C) is a 5C-5C line sectional view, (D) is a 5D-5D line sectional view.

圖6係圖1所示之燃氣渦輪之預混合管之本體部之展開圖。 Fig. 6 is an expanded view of the main body of the premixing tube of the gas turbine shown in Fig. 1 .

圖7係具備本發明之第二實施形態之結構之燃氣渦輪之預混合管之立體圖。 Fig. 7 is a perspective view of a premixing tube of a gas turbine having a structure according to a second embodiment of the present invention.

圖8係圖7所示之燃氣渦輪之預混合管之前視圖。 Fig. 8 is a front view of the premixing tube of the gas turbine shown in Fig. 7 .

圖9係沿圖7之9-9線而顯示之剖視圖。 Fig. 9 is a cross-sectional view along line 9-9 of Fig. 7 .

圖10係說明具備本發明之結構之燃氣渦輪之預混合管之空氣之引入狀態的圖，且於沿軸之面切斷而顯示之剖視圖。 Fig. 10 is a diagram illustrating a state of introducing air into a premixing tube of a gas turbine having the structure of the present invention, and is a cross-sectional view cut along a plane along the axis.

圖11係說明安裝具備本發明之結構之預混合管之燃氣渦輪之概略剖視圖。 Fig. 11 is a schematic cross-sectional view illustrating a gas turbine equipped with a premixer having the structure of the present invention.

圖12係顯示於軸向引入空氣之結構之預混合管之圖，且係相當於圖10之剖視圖。 Fig. 12 is a diagram showing a premixing tube of a structure in which air is introduced in the axial direction, and is a sectional view corresponding to Fig. 10 .

基於所圖示之較佳之實施形態具體說明本發明之燃氣渦輪之預混合管結構。 The structure of the premixer tube of the gas turbine of the present invention will be specifically described based on the illustrated preferred embodiment.

首先，參照圖11說明安裝具備本發明之結構之預混合管之燃氣渦輪之一實施例之概略。 First, an outline of an embodiment of a gas turbine equipped with a premixer tube having the structure of the present invention will be described with reference to FIG. 11 .

燃氣渦輪100中，自空氣吸入口101吸引之空氣通過進氣導流板101a被供給至壓縮機102並被壓縮，該壓縮空氣被引導至燃燒器103。該燃燒器103為燃燒器外筒103a與燃燒器內筒103b之雙重結構，壓縮空氣被引導至燃燒器內筒103b之外側。 In the gas turbine 100 , the air sucked from the air inlet 101 is supplied to the compressor 102 through the intake deflector 101 a and compressed, and the compressed air is guided to the combustor 103 . The burner 103 has a double structure of a burner outer cylinder 103a and a burner inner cylinder 103b, and the compressed air is guided to the outside of the burner inner cylinder 103b.

於燃燒器103之燃燒器內筒103b之上部，安裝有配置於以燃燒器內筒 103b之軸為中心之圓周上之適當個數之預混合管1。預混合管1之下部與燃燒器內筒103b之內部連通，於上部配置有供給主燃料之主燃料用噴嘴110，對燃燒器內筒103b之內部噴射主燃料。 On the top of the burner inner cylinder 103b of the burner 103, a The axis of 103b is the appropriate number of premixing tubes 1 on the circumference of the center. The lower part of the premixer tube 1 communicates with the interior of the burner inner cylinder 103b, and the upper part is provided with a main fuel nozzle 110 for supplying main fuel, and injects the main fuel into the interior of the burner inner cylinder 103b.

又，於燃燒器內筒103b之中央上部配置有先導燃料用噴嘴111，將先導燃料噴射至燃燒器內筒103b內。所噴射之先導燃料藉由未圖示之點燃裝置點燃。 Moreover, the nozzle 111 for pilot fuel is arrange|positioned at the center upper part of the combustor inner cylinder 103b, and the pilot fuel is injected into the combustor inner cylinder 103b. The injected pilot fuel is ignited by an ignition device not shown.

經引導至燃燒器內筒103b之外側之壓縮空氣被引導至預混合管1，與主燃料之燃燒氣體混合而生成混合氣體，該混合氣體自預混合管1之下部向燃燒器內筒103b之內部噴射而促進燃燒，產生高溫‧高壓之作動氣體。 The compressed air guided to the outside of the inner cylinder 103b of the burner is guided to the premixing pipe 1, and mixed with the combustion gas of the main fuel to generate a mixed gas, which flows from the lower part of the premixing pipe 1 to the inner cylinder 103b of the burner. Internal injection promotes combustion and generates high temperature and high pressure operating gas.

在燃燒器103產生之作動氣體被引導至渦輪104，使渦輪翼旋轉而使主軸105旋轉。藉由主軸105之旋轉，使壓縮機102旋轉，且獲得所期望之輸出旋轉。供於渦輪104之旋轉之作動氣體成為排氣氣體而自排氣管道106排出。 The working gas generated in the combustor 103 is guided to the turbine 104 to rotate the turbine blades and rotate the main shaft 105 . By the rotation of the main shaft 105, the compressor 102 is rotated, and a desired output rotation is obtained. The operating gas supplied to the rotation of the turbine 104 becomes exhaust gas and is discharged from the exhaust duct 106 .

圖1~圖6顯示具備本發明之第一實施形態之結構之預混合管1。該預混合管1係圓筒形之本體部1a之上部除中央部以外被底板1b封閉，且該底板1b之中央部介隔密封件11a安裝有保持主燃料用噴嘴110之噴嘴支持管11。另，預混合管1之噴嘴支持管11之側(基端部T1之一例)為主燃料流動之上游側。 1 to 6 show a premixer tube 1 having the structure of the first embodiment of the present invention. The premixing tube 1 is closed by a bottom plate 1b except for the central portion on the upper part of the cylindrical body portion 1a, and the central portion of the bottom plate 1b is provided with a nozzle support pipe 11 holding a main fuel nozzle 110 through a sealing member 11a. In addition, the side of the nozzle support pipe 11 of the premixer pipe 1 (an example of the base end portion T1) is the upstream side where the main fuel flows.

又，本體部1a之下部(前端部T2之一例)，即主燃料流動之下游側，連續有逐漸被縮徑而下部側成為小徑之筒狀之圓錐形本體部1c。又，以使開口1d指向自該圓錐形本體部1c相對本體部1a之軸C方向偏倚之方向的方式，連續有傾斜管部1e。又，該開口1d如圖2所示為圓形。 Further, the lower part of the main body 1a (an example of the front end T2), that is, the downstream side of the flow of the main fuel, continues with a cylindrical conical main body 1c whose diameter is gradually reduced and the lower side becomes a small diameter. In addition, the inclined pipe portion 1e continues so that the opening 1d is directed in a direction deviated from the conical body portion 1c relative to the axis C direction of the body portion 1a. In addition, this opening 1d is circular as shown in FIG. 2 .

於預混合管1之本體部1a形成有適當數量之空氣孔1a1、1a2、1a3、1a4。該空氣孔1a1、1a2、1a3、1a4如圖6之展開圖所示，在預混合管1之上游側形成於周向之空氣孔1a1之數量，多於其下游側形成於周向之空氣孔1a2~1a4之數量。該實施形態中，顯示有於軸C方向並列設置有4行之空氣孔1a1、1a2、1a3、1a4者，然而該等最上游側之空氣孔1a1為16個，配置於其他位置之空氣孔1a2、1a3、1a4為8個。 An appropriate number of air holes 1a1, 1a2, 1a3, 1a4 are formed in the main body 1a of the premixing tube 1. The air holes 1a1, 1a2, 1a3, and 1a4 are shown in the expanded view of FIG. 6, the number of the air holes 1a1 formed in the circumferential direction on the upstream side of the premixing tube 1 is more than the number of the air holes 1a2-1a4 formed in the circumferential direction on the downstream side. quantity. In this embodiment, four rows of air holes 1a1, 1a2, 1a3, and 1a4 are shown arranged in parallel in the axis C direction, but the number of air holes 1a1 on the most upstream side is 16, and the air holes 1a2 arranged in other positions , 1a3, 1a4 are 8.

該等空氣孔1a1、1a2、1a3、1a4之位置關係顯示於圖5與圖6。圖5(A)係沿圖2之5A-5A線在與軸C正交之面切斷之剖面圖，於該部分配置有16個空氣孔1a1。又，圖5(B)係配置於距空氣孔1a1最近之下游側之空氣孔1a2之部分切斷之沿圖2之5B-5B線切斷之剖面圖，於該部分配置有8個空氣孔1a2。該8個空氣孔1a2配置於相對於16個空氣孔1a1每隔一個於軸C方向重疊之位置。又，配置於距空氣孔1a2最近之下游側之空氣孔1a3為8個，如圖5(B)與圖5(C)所示，配置於與空氣孔1a2之位置於周向以22.5°之角度偏移之位置。且，配置於最下游之空氣孔1a4於周向配置有8個，如圖5(B)與圖5(D)所示，該等空氣孔1a4配置於與空氣孔1a2於軸C方向相等之位置。 The positional relationship of these air holes 1a1, 1a2, 1a3, 1a4 is shown in Fig. 5 and Fig. 6 . FIG. 5(A) is a cross-sectional view taken along the line 5A-5A of FIG. 2 along the plane perpendicular to the axis C, and 16 air holes 1a1 are arranged in this part. Also, Fig. 5(B) is a cross-sectional view cut along the line 5B-5B in Fig. 2 of the part of the air hole 1a2 arranged on the downstream side closest to the air hole 1a1, and eight air holes are arranged in this part 1a2. The eight air holes 1a2 are arranged at positions overlapping each other in the axis C direction with respect to the 16 air holes 1a1. Also, there are eight air holes 1a3 arranged on the downstream side closest to the air hole 1a2, as shown in Figure 5(B) and Figure 5(C), and are arranged at a distance of 22.5° in the circumferential direction from the position of the air hole 1a2. The position of the angular offset. In addition, there are eight air holes 1a4 arranged in the most downstream direction in the circumferential direction, as shown in FIG. 5(B) and FIG. 5(D). Location.

另，關於空氣孔1a2、1a3、1a4，亦可藉由配置於分別以15°之角度偏移之位置，將該等空氣孔1a2、1a3、1a4全體配置於在沿軸C之方向偏移之位置。 In addition, regarding the air holes 1a2, 1a3, and 1a4, it is also possible to dispose all of the air holes 1a2, 1a3, and 1a4 at positions offset in the direction along the axis C by arranging them at positions offset by an angle of 15°, respectively. Location.

再者，可使空氣孔1a1、1a2、1a3、1a4各者之直徑不同。該情形下，較佳為，增大配置於上游側之空氣孔1a1之直徑。又，亦可向下游側逐漸縮小直徑，還可使空氣孔1a2、1a3、1a4之直徑相等。 Furthermore, the diameters of the air holes 1a1, 1a2, 1a3, and 1a4 may be different. In this case, it is preferable to increase the diameter of the air hole 1a1 arranged on the upstream side. Also, the diameter can be gradually reduced toward the downstream side, and the diameters of the air holes 1a2, 1a3, and 1a4 can also be made equal.

且，該預混合管1如圖11所示，指向燃燒器內筒103b之中央部而配置開口1d。因此，向於先導燃料點燃之火焰噴射混合氣體。 In addition, as shown in FIG. 11 , the premixing tube 1 is provided with an opening 1d directed toward the center of the burner inner tube 103b. Therefore, the mixed gas is injected toward the flame ignited by the pilot fuel.

其次，以下說明具備該第一實施形態之結構之預混合管1之作用。 Next, the action of the premixer tube 1 having the structure of the first embodiment will be described below.

該第一實施形態之預混合管1，對於從主燃料用噴嘴110噴射之主燃料之燃料氣體，自形成於本體部1a之空氣孔1a1、1a2、1a3、1a4導入壓縮空氣而稀釋燃燒氣體，在預混合管1之內部混合而生成混合氣體。燃燒氣體在由主燃料用噴嘴110剛噴射後處於最高濃度。該預混合管1，由於位於最上游側之空氣孔1a1之數量多於下游側之空氣孔1a2、1a3、1a4之數量，故自最上游側之空氣孔1a1導入大量之空氣。因此，促進濃度較高之燃燒氣體之稀釋。 The premixer tube 1 of the first embodiment introduces compressed air from the air holes 1a1, 1a2, 1a3, and 1a4 formed in the main body 1a to the fuel gas of the main fuel injected from the main fuel nozzle 110 to dilute the combustion gas, Mixed inside the premixer 1 to generate mixed gas. The combustion gas is at the highest concentration immediately after being injected from the main fuel nozzle 110 . In the premixing tube 1, since the number of air holes 1a1 on the most upstream side is greater than the number of air holes 1a2, 1a3, and 1a4 on the downstream side, a large amount of air is introduced from the air holes 1a1 on the most upstream side. Thus, the dilution of the higher concentrations of combustion gases is facilitated.

又，由於空氣孔1a2、1a3、1a4係於周向之位置偏移而配置，故難以對通過空氣孔1a2未面對之位置，即在周向鄰接之空氣孔1a2彼此之中間之位置所面對之位置的燃燒氣體導入空氣。然而，由於配置於該空氣孔1a2之下游之空氣孔1a3，係配置於相對空氣孔1a2偏移之位置，故對於通過未形成空氣孔1a2之部分之燃燒氣體，藉由自空氣孔1a3導入之空氣而稀釋。因此，供給之燃燒氣體全體與空氣均等地混合，稀釋至所期望之狀態而供給於燃燒，生成高溫‧高壓之作動氣體。 Also, since the air holes 1a2, 1a3, and 1a4 are arranged at offset positions in the circumferential direction, it is difficult to align the position where the passing air hole 1a2 does not face, that is, the position between the circumferentially adjacent air holes 1a2 facing each other. The combustion gas at the position is introduced into the air. However, since the air hole 1a3 arranged downstream of the air hole 1a2 is arranged at a position offset from the air hole 1a2, the combustion gas passing through the part where the air hole 1a2 is not formed is introduced by the air hole 1a3. diluted with air. Therefore, the supplied combustion gas is uniformly mixed with the air, diluted to the desired state, and supplied for combustion to generate high-temperature and high-pressure operating gas.

另，預混合管1之下游部形成有較本體部1a更小徑之開口1d，故自開口1d噴射之混合氣體之流速增大。因此，由於對於先導燃料之火焰高速噴射，故不會有著火之燃燒氣體之火焰逆火。 In addition, the downstream portion of the premixing tube 1 is formed with an opening 1d having a smaller diameter than the main body portion 1a, so that the flow velocity of the mixed gas injected from the opening 1d increases. Therefore, since the flame of the pilot fuel is sprayed at a high speed, there is no flame backfiring of the ignited combustion gas.

且，驅動渦輪104後之作動氣體自排氣管道106排出。該排出之排出氣體，因在預混合管1混合而稀釋之混合氣體之燃燒氣體濃度低，故NOx之排出量較小。 Moreover, the operating gas after driving the turbine 104 is discharged from the exhaust pipe 106 . The discharged exhaust gas has a low concentration of combustion gas in the mixed gas mixed and diluted in the premixer 1, so the amount of NOx discharged is small.

圖7~圖9顯示具備第二實施形態之結構之燃氣渦輪之預混合管2。針對該實施形態之預混合管2之部位，即與圖1~圖6所示之第一實施形態之預混合管1相同之部位，附加相同之符號。 7 to 9 show the premixing tube 2 of the gas turbine having the structure of the second embodiment. The parts of the premixing pipe 2 of this embodiment, that is, the same parts as the premixing pipe 1 of the first embodiment shown in FIGS. 1 to 6 are assigned the same symbols.

於該預混合管2之本體部2a之上部，設有蓋體2b，其與本體部2a分開而於中央部介隔密封件11a安裝有噴嘴支持管11。 On the upper part of the main body part 2a of the premixing pipe 2, a cover body 2b is provided, which is separated from the main body part 2a, and a nozzle support pipe 11 is attached to the central part through a sealing member 11a.

於本體部2a之下部連續有連續本體部2c，其上游側之上端部以連續於本體部2a之圓形向下游側逐漸縮徑，且下游側之下端部形成為方形。 There is a continuous body portion 2c at the lower part of the body portion 2a, the upper end of the upstream side gradually decreases in diameter from a circle continuous to the body portion 2a toward the downstream side, and the lower end of the downstream side is formed into a square shape.

且，於該連接本體部2c之下端部，連接有與連續本體部2c連續之方形之傾斜管部2e之上端部，且開口2d指向於使該傾斜管部2e之下端部相對軸C方向偏倚之方向。即，開口2d如圖8所示，為方形。 And, at the lower end of the connecting body part 2c, the upper end of the square inclined pipe part 2e continuous with the continuous body part 2c is connected, and the opening 2d is directed so that the lower end of the inclined pipe part 2e is biased relative to the direction of the axis C. direction. That is, the opening 2d has a square shape as shown in FIG. 8 .

預混合管2之本體部2a，與第一實施形態之預混合管1之本體部1a相同，設有適當數量之空氣孔2a1、2a2、2a3、2a4。該等空氣孔2a1、2a2、2a3、2a4以與形成於預混合管1之本體部1a之空氣孔1a1、1a2、1a3、1a4相同之數量配置於相同位置。因此，關於形成於本體部2a之空氣孔2a1、2a2、2a3、2a4，為與顯示第一實施形態之預混合管1之本體部1a之剖面之圖5(A)~(D)相同之剖面形狀。 The main body portion 2a of the premixing tube 2 is the same as the main body portion 1a of the premixing tube 1 of the first embodiment, and is provided with an appropriate number of air holes 2a1, 2a2, 2a3, 2a4. These air holes 2a1, 2a2, 2a3, 2a4 are arranged at the same positions in the same number as the air holes 1a1, 1a2, 1a3, 1a4 formed in the main body portion 1a of the premixing tube 1. Therefore, the air holes 2a1, 2a2, 2a3, and 2a4 formed in the main body 2a are the same cross-sections as those shown in FIGS. shape.

關於該預混合管2，亦與預混合管1之情形相同，如圖11所示，使開 口2d指向燃燒器內筒103b之中央部配置，向於先導燃料點燃之火焰噴射混合氣體。且，由於開口2d之開口面積小於本體部2a之剖面積，故混合氣體之流速增大而可防止逆火。 Regarding this premixing tube 2, it is the same as the situation of the premixing tube 1, as shown in FIG. The port 2d is arranged to point to the center of the burner inner tube 103b, and injects the mixed gas to the flame ignited by the pilot fuel. Furthermore, since the opening area of the opening 2d is smaller than the cross-sectional area of the body portion 2a, the flow velocity of the mixed gas is increased to prevent backfire.

以上說明之預混合管1、2，如圖10所示，自本體部1a、2a之側方供給經稀釋之空氣。 The premixing tubes 1 and 2 described above are supplied with diluted air from the sides of the main body parts 1a and 2a as shown in FIG. 10 .

另一方面，圖12顯示自預混合管4之上部開口4a引入空氣之結構。該預混合管4為自上方引入空氣之結構，故必須增大燃氣渦輪100之頂蓋112與預混合管4之上部開口4a之間之距離。 On the other hand, FIG. 12 shows a structure in which air is introduced from the upper opening 4a of the premixing tube 4. As shown in FIG. The premixing tube 4 is a structure in which air is introduced from above, so the distance between the top cover 112 of the gas turbine 100 and the upper opening 4a of the premixing tube 4 must be increased.

與此相對，具備本發明之結構之預混合管1、2係自側方引入空氣，故如圖10所示，可縮小預混合管1、2之上部與頂蓋112之間之距離。 In contrast, the premixing tubes 1 and 2 with the structure of the present invention introduce air from the side, so as shown in FIG. 10 , the distance between the top of the premixing tubes 1 and 2 and the top cover 112 can be reduced.

因此，可減小燃氣渦輪100之高度，實現燃氣渦輪100之小型化。 Therefore, the height of the gas turbine 100 can be reduced, and the size of the gas turbine 100 can be realized.

根據本發明之燃氣渦輪之預混合管結構，可將燃燒氣體容易而均等地稀釋成所期望之濃度，故有助於降低排氣中之NOx濃度。 According to the premixing tube structure of the gas turbine of the present invention, the combustion gas can be easily and evenly diluted to the desired concentration, thus helping to reduce the NOx concentration in the exhaust gas.

1:預混合管 1: premix tube

1a:本體部 1a: Body part

1a1:空氣孔 1a1: air holes

1a2:空氣孔 1a2: air holes

1a3:空氣孔 1a3: air holes

1a4:空氣孔 1a4: air holes

1c:圓錐形本體部 1c: Conical body part

1d:開口 1d: opening

1e:傾斜管部 1e: Inclined tube

Claims (7)

一種燃氣渦輪之預混合管結構，其特徵為：其係於燃燒器內筒之中央部配置先導燃料用噴嘴，於該先導燃料用噴嘴之周圍配置複數根主燃料用噴嘴，將該主燃料用噴嘴保持於基端部，將使自該主燃料用噴嘴噴射之主燃料與空氣混合之混合氣體自前端部向燃燒器內筒噴射之筒狀之預混合管，且，於周壁周向排列有使內外連通而引入空氣之複數個空氣孔，且該空氣孔於軸向配置有複數行。 A premixing tube structure for a gas turbine, characterized in that: a pilot fuel nozzle is arranged in the center of the combustor inner cylinder, a plurality of main fuel nozzles are arranged around the pilot fuel nozzle, and the main fuel The nozzle is held at the base end, and the mixed gas of the main fuel and air injected from the main fuel nozzle is injected into the inner cylinder of the burner from the front end, and the cylindrical premixing tube is arranged in the circumferential direction of the surrounding wall There are a plurality of air holes for connecting the inside and the outside to introduce air, and the air holes are arranged in a plurality of rows in the axial direction. 如請求項1之燃氣渦輪之預混合管結構，其中上述空氣孔以錯開狀排列。 The gas turbine premixing tube structure according to claim 1, wherein the air holes are arranged in a staggered manner. 如請求項1之燃氣渦輪之預混合管結構，其中上述空氣孔在基端部側於周向配置之數量，多於在前端部側於周向配置之數量。 The premixing tube structure of a gas turbine according to claim 1, wherein the number of said air holes arranged in the circumferential direction on the base end side is greater than the number arranged on the front end side in the circumferential direction. 如請求項2之燃氣渦輪之預混合管結構，其中上述空氣孔在基端部側於周向配置之數量，多於在前端部側於周向配置之數量。 The gas turbine premixing tube structure according to claim 2, wherein the number of said air holes arranged in the circumferential direction on the base end side is greater than the number arranged on the front end side in the circumferential direction. 如請求項1至4中任一項之燃氣渦輪之預混合管結構，其中上述空氣孔之開口面積在基端部側設為較大，在前端部側設為較小。 The gas turbine premixer tube structure according to any one of claims 1 to 4, wherein the opening area of the air holes is set larger on the base end side and smaller on the front end side. 如請求項1至4中任一項之燃氣渦輪之預混合管結構，其中與筒狀之軸正交之面之開口面積，係前端部側之開口面積小於自基端部側至本體部之開口面積。 The gas turbine premixing tube structure according to any one of claims 1 to 4, wherein the opening area of the plane perpendicular to the cylindrical axis is smaller than the opening area on the front end side to the main body from the base end side The opening area. 如請求項5之燃氣渦輪之預混合管結構，其中與筒狀之軸正交之面之開口面積，係前端部側之開口面積小於自基端部側至本體部之開口面積。 The gas turbine premixing tube structure according to claim 5, wherein the opening area of the plane perpendicular to the cylindrical axis is smaller than the opening area from the base end side to the main body.
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