JPH04131620A - Sub-combustion chamber type swirling combustion device - Google Patents
Sub-combustion chamber type swirling combustion deviceInfo
- Publication number
- JPH04131620A JPH04131620A JP25303390A JP25303390A JPH04131620A JP H04131620 A JPH04131620 A JP H04131620A JP 25303390 A JP25303390 A JP 25303390A JP 25303390 A JP25303390 A JP 25303390A JP H04131620 A JPH04131620 A JP H04131620A
- Authority
- JP
- Japan
- Prior art keywords
- combustion chamber
- fuel
- sub
- primary air
- combustion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 92
- 239000000446 fuel Substances 0.000 claims abstract description 68
- 238000002347 injection Methods 0.000 claims abstract description 27
- 239000007924 injection Substances 0.000 claims abstract description 27
- 238000001704 evaporation Methods 0.000 claims abstract description 17
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 13
- 239000000567 combustion gas Substances 0.000 claims abstract description 8
- 239000007921 spray Substances 0.000 claims description 18
- 230000008020 evaporation Effects 0.000 claims description 14
- 229910052799 carbon Inorganic materials 0.000 abstract description 14
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 12
- 239000007789 gas Substances 0.000 abstract description 8
- 239000002245 particle Substances 0.000 abstract description 5
- 239000000203 mixture Substances 0.000 abstract description 4
- 239000007788 liquid Substances 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000002309 gasification Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 abstract 1
- 230000005855 radiation Effects 0.000 abstract 1
- 230000000052 comparative effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 238000010790 dilution Methods 0.000 description 4
- 239000012895 dilution Substances 0.000 description 4
- 238000009423 ventilation Methods 0.000 description 4
- 230000008021 deposition Effects 0.000 description 3
- 239000011362 coarse particle Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000003111 delayed effect Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000000779 smoke Substances 0.000 description 2
- 238000009834 vaporization Methods 0.000 description 2
- 230000008016 vaporization Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Landscapes
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Spray-Type Burners (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、主としてガスタービンに用いられる燃焼器、
特に主燃焼室の上流側に副燃焼室を設けたガスタービン
用の渦巻燃焼器に関するものである。[Detailed Description of the Invention] [Industrial Application Field] The present invention mainly relates to a combustor used in a gas turbine,
In particular, the present invention relates to a swirl combustor for a gas turbine in which a sub-combustion chamber is provided upstream of a main combustion chamber.
第４図〜第６図に、主燃焼室の上流側に副燃焼室を設け
た従来のガスタービン用燃焼器（特公昭５４−８８９０
号公報参照）が例示されている。これらの図において、
１は燃焼器外筒、２は外筒１の中に広い通気間隙３をお
いて支持された燃焼器内筒で、内筒２は副燃焼室４、主
燃焼室５等をその内部に形成している。燃焼器内筒２の
第４図及び第６図における左端部は、外筒１の端部壁６
にボルト等によって取付けられるフランジ部７を介して
固定・支持されるが、そのフランク部７の中心を貫通し
て燃料噴射弁８が副燃゛焼室４の中に噴口１６を有して
おり、加圧された軽油のような燃料ｆを副燃焼室４の中
へ霧化して噴射するようになっている。なお９は副燃焼
室４内に臨んで設けられた点火プラグを示す。Figures 4 to 6 show a conventional gas turbine combustor (Japanese Patent Publication No. 54-8890) in which an auxiliary combustion chamber is provided upstream of the main combustion chamber.
For example, In these figures,
1 is a combustor outer cylinder, 2 is a combustor inner cylinder supported with a wide ventilation gap 3 in the outer cylinder 1, and the inner cylinder 2 has a sub-combustion chamber 4, a main combustion chamber 5, etc. formed therein. are doing. The left end of the combustor inner cylinder 2 in FIGS. 4 and 6 is the end wall 6 of the outer cylinder 1.
The fuel injection valve 8 is fixed and supported via a flange portion 7 attached by bolts or the like to the flange portion 7, and a fuel injection valve 8 has a nozzle port 16 in the auxiliary combustion chamber 4, passing through the center of the flank portion 7. , pressurized fuel f such as light oil is atomized and injected into the sub-combustion chamber 4. Note that 9 indicates a spark plug provided facing into the sub-combustion chamber 4.
通気間隙３には図示されない空気圧縮機によって加圧さ
れた空気ａが供給されており、その一部は１次空気すと
して、第５図に示すような案内羽根１０を有する１次空
気通路１１の開口を通り、副燃焼室４内へ接線方向に流
入して、燃料噴射弁８の噴口１６から噴射される燃料噴
霧と共に副燃焼室４内において渦流を形成し、燃料と１
次空気が混合して、点火プラグ９により点火され、１次
燃焼を行なう。Air a pressurized by an air compressor (not shown) is supplied to the ventilation gap 3, and a part of the air a is supplied as a primary air passage 11 having a guide vane 10 as shown in FIG. The fuel flows into the auxiliary combustion chamber 4 through the opening in the tangential direction, forms a vortex in the auxiliary combustion chamber 4 together with the fuel spray injected from the nozzle 16 of the fuel injection valve 8, and the fuel and 1
The secondary air is mixed and ignited by the spark plug 9 to perform primary combustion.
１２は副燃焼室４と主燃焼室５の仕切壁に形成された絞
り開口で、１次燃焼をした未燃成分を含む燃焼ガスは、
旋回しながら絞り開口１２を通過して主燃焼室５へ流入
し、主燃焼室５の下流側部分の壁に設けられている多数
の小さな空気孔１３を通して、通気間隙３から２次空気
及び冷却空気Ｃとして加圧された空気の供給を受け、２
次燃焼を行なう。燃焼ガスは更に流出筒１４に設けられ
た希釈空気口１５を通して通気間隙３から流入する希釈
空気ｄによって増量されて大流量のタービン作動ガスｇ
となり、図示されないタービンロータを駆動して動力を
発生する。12 is a throttle opening formed in the partition wall between the auxiliary combustion chamber 4 and the main combustion chamber 5, through which the combustion gas containing unburned components that has undergone primary combustion is
The secondary air and cooling flow from the ventilation gap 3 into the main combustion chamber 5 through a swirling throttle opening 12 and through a number of small air holes 13 provided in the wall of the downstream part of the main combustion chamber 5. Receiving pressurized air as air C, 2
Perform the next combustion. The combustion gas is further increased in amount by dilution air d flowing in from the ventilation gap 3 through the dilution air port 15 provided in the outflow pipe 14, and becomes a large flow of turbine working gas g.
This generates power by driving a turbine rotor (not shown).
従来のガスタービンの燃焼器においては、１次空気通路
１１は副燃焼室４を形成する筒壁のうち、比較的上流側
の部分から開口するように設けられ、第４図及び第６図
に示したものでも、燃料噴射弁８の噴口１６から１次空
気通路１１の前方端までの距離Ｙは、副燃焼室４の直径
りのおよそ１０分の１程度にすぎない。In a conventional gas turbine combustor, the primary air passage 11 is provided so as to open from a relatively upstream portion of the cylindrical wall forming the auxiliary combustion chamber 4, as shown in FIGS. 4 and 6. Even in the case shown, the distance Y from the nozzle 16 of the fuel injection valve 8 to the front end of the primary air passage 11 is only about one-tenth of the diameter of the sub-combustion chamber 4.
そのたｔ１燃料は燃料噴射弁８から噴射されると同時に
１次空気が混合されることになり、燃料噴霧が蒸発して
気化する前の粗粒の状態で空気の中に浮遊するものと考
えられる。もちろん、その状態でも燃料は蒸発・気化す
るが、完全に蒸発が終らないうちに燃焼域に流入するの
で、比較的燃料粒子が大きいうちに燃焼が始まることに
なる。In addition, the t1 fuel is injected from the fuel injection valve 8 and mixed with primary air at the same time, and it is assumed that the fuel spray evaporates and floats in the air in the form of coarse particles before being vaporized. It will be done. Of course, even in this state, the fuel evaporates and vaporizes, but it flows into the combustion zone before evaporation is complete, so combustion begins while the fuel particles are relatively large.
したがって、着火性・始動性が必ずしも良くなく、着火
しても不完全燃焼になり易いから、燃焼安定性が高いと
は言えない。Therefore, the ignitability and startability are not necessarily good, and even if ignited, incomplete combustion tends to occur, so it cannot be said that the combustion stability is high.
また、燃料が十分蒸発・気化していない粗粒のままで空
気と共に旋回するので、遠心力によって外方へ飛ばされ
た燃料粒が１次燃焼室４の筒壁などに付着しやすく、そ
れが輻射熱等により分解して煤状のカーボン（遊離炭素
）を生じ、壁面に堆積して流体の通路や燃焼室容積を狭
めるばかりでなく、時には大きな塊になって剥れ落ちて
、下流にあるタービン翼等を損傷させることもある。本
発明は、従来の副燃焼室式渦巻燃焼器のこのような問題
を解決し、着火性を改善し、完全燃焼が行なわれるよう
にして、燃焼安定性とタービンの熱効率を高めると共に
、カーボンの発生を抑制することを発明の目的としてい
る。In addition, since the fuel swirls with the air as coarse particles that have not been sufficiently evaporated or vaporized, the fuel particles blown outward by centrifugal force tend to adhere to the cylindrical wall of the primary combustion chamber 4. It decomposes due to radiant heat, etc., producing soot-like carbon (free carbon), which not only accumulates on walls and narrows the fluid passage and combustion chamber volume, but also sometimes flakes off in large chunks, damaging downstream turbines. It may also damage the wings. The present invention solves these problems of the conventional auxiliary combustion chamber type swirl combustor, improves ignitability, enables complete combustion, increases combustion stability and turbine thermal efficiency, and reduces carbon emissions. The purpose of the invention is to suppress the occurrence.
本発明者等は、従来の副燃焼室式渦巻燃焼器における前
述のような問題点は、燃料噴射弁の噴口と１次空気通路
の開口との距離Ｙが小さかったために生じたものである
との原因解明のもとに、距離Ｙを大きくとり、燃料噴射
弁から噴出した燃料噴霧が、１次空気通路から接線方向
に流入する空気と出会う前に噴霧の蒸発空間を通過する
ようにし、ここで燃料粒が輻射熱を受け、また減圧され
ることによって蒸発・気化するように構成することを考
えついた。The present inventors believe that the above-mentioned problems in the conventional auxiliary combustion chamber type swirl combustor are caused by the short distance Y between the nozzle of the fuel injector and the opening of the primary air passage. Based on elucidation of the cause of They came up with a structure in which the fuel particles receive radiant heat and are evaporated by being depressurized.
そこで、色々な形状の燃焼器を試作して実験を繰返した
ところ、前証のように距離Ｙを大きくとって、そこに燃
料噴霧の蒸発空間を形成すると、たしかに好ましい結果
が得られることが確認されたが、距離Ｙをあまりに大き
くすると、１次空気の混合が遅れるために、逆に空気不
足となって、やはりカーボンの発生をみることも判明し
た。この事実から、適正な距離Ｙの値には下限と共に上
限のあることを知り、その限界を追究した結果として本
発明の解決手段に到達したも、のである。Therefore, after repeatedly experimenting with combustor prototypes of various shapes, it was confirmed that by increasing the distance Y and forming an evaporation space for the fuel spray there as shown in the previous proof, favorable results could indeed be obtained. However, it has also been found that if the distance Y is made too large, the mixing of the primary air is delayed, resulting in a lack of air and the formation of carbon. From this fact, we learned that there is both a lower limit and an upper limit to the appropriate value of distance Y, and as a result of pursuing these limits, we arrived at the solution of the present invention.
したがって、本発明は、前記の課題の解決手段として、
上流側に設けられた燃料噴射弁と１次空気を接線方向に
流入させる１次空気通路とを備え内部に燃焼ガスの渦流
を発生させる副燃焼室と、前８己副燃焼室の下流側に接
続する主燃焼室からなリ、前記１次空気通路の前記副燃
焼室の壁面における開口の上流端は、前記燃料噴射弁の
噴口との間に所定の距離Ｙを有し、前記距離Ｙの値は前
記副燃焼室の直径をＤとして、
Ｄ／４≦Ｙ≦Ｄ
の範囲から選定されており、それによって前記副燃焼室
の上流側に所定の大きさの燃料の噴霧蒸発空間が形成さ
れていることを特徴とする副燃焼室式渦巻燃焼器を提供
する。Therefore, the present invention, as a means for solving the above problems,
A sub-combustion chamber is provided with a fuel injection valve provided on the upstream side and a primary air passage through which primary air flows in in a tangential direction, and generates a vortex flow of combustion gas inside; The upstream end of the opening in the wall surface of the auxiliary combustion chamber of the primary air passage has a predetermined distance Y between it and the nozzle of the fuel injection valve, and The value is selected from the range of D/4≦Y≦D, where D is the diameter of the auxiliary combustion chamber, thereby forming a fuel spray evaporation space of a predetermined size on the upstream side of the auxiliary combustion chamber. A sub-combustion chamber type swirl combustor is provided.
副燃焼室の上流側に設けられた燃料噴射弁の噴口から燃
料が噴射されると、燃料噴霧は円錐形に十分に拡開して
減圧されると共に、噴射された副燃焼室の上流側の部分
は、噴霧蒸発空間となっていて、そこに１次空気が直接
流入することがないので、空気が混入する前の燃料噴霧
は壁面や燃焼ガスからの輻射熱を受けて加熱され、液状
の燃料粒は蒸発して気化し、すみやかに気体状の燃料と
なる。When fuel is injected from the nozzle of the fuel injection valve installed on the upstream side of the auxiliary combustion chamber, the fuel spray expands into a conical shape and is depressurized. This part is a spray evaporation space, and primary air does not directly flow into it, so the fuel spray before air is mixed in is heated by radiant heat from the wall and combustion gas, and becomes liquid fuel. The grains evaporate and become vaporized, quickly turning into gaseous fuel.
気化した燃料は副燃焼室の下流側の壁面に開口している
１次空気通路から渦巻状に噴火する１次空気と混合する
と共に着火して燃焼するが、燃料の気化が進んでいるの
で着火しやすく、また燃焼効率も高く、カーボンを発生
することがない。The vaporized fuel mixes with the primary air that erupts in a spiral form from the primary air passage that opens on the downstream wall of the sub-combustion chamber, ignites and burns, but as the fuel vaporization progresses, ignition does not occur. It is easy to burn, has high combustion efficiency, and does not generate carbon.
１次空気が流入する位置が適正であるから、燃料蒸発の
気化が十分に進んだ後であり、しかも１次空気の混入が
遅すぎて逆に燃料と空気の混合状態が悪化し、空気不足
の部分を生じて燃焼効率が低下するという問題も生じな
い。Because the position where the primary air flows in is appropriate, it occurs after the fuel evaporation has sufficiently progressed, and the mixing of the primary air is too slow, resulting in a worsening of the mixture of fuel and air, resulting in air shortage. There is also no problem that the combustion efficiency decreases due to the occurrence of the part shown in FIG.
第１図〜第３図に本発明の第１実施例を示す。 A first embodiment of the present invention is shown in FIGS. 1-3.
第２図は第１図の一部の横断面を拡大して示す側面図で
あり、第３図は第１図の要部を拡大して示すものである
。これらの図において、既に説明した第４図〜第６図に
示す従来のガスタービンの燃焼器と実質的に同じ構造部
分については、同じ参照符号を付けることによって重複
する説明は省略することとする。2 is an enlarged side view of a cross section of a part of FIG. 1, and FIG. 3 is an enlarged view of the main part of FIG. 1. In these figures, structural parts that are substantially the same as those of the conventional gas turbine combustor shown in FIGS. 4 to 6, which have already been explained, are designated by the same reference numerals and redundant explanation will be omitted. .
この実施例の特徴は、副燃焼室４′を形成する筒壁にお
いて、１次空気通路１１′の開口と、それに伴なう案内
羽根１０′をできるだけ主燃焼室５に接近させて設け、
それによって１次空気通路１１′の開口前端と燃料噴射
弁８の噴口１６との間に、副燃焼室４′の直径りの２分
の１程度の距離Ｙを取り、副燃焼室４′の前方部分に空
気の吹き込まない噴霧蒸発空間１７を形成したことであ
る。第１実施例の場合、副燃焼室４′の前方部分はフラ
ンジ部７の外周に溶接された室壁が、燃料噴霧角θ（約
４５°）と略同程度の開き角θ′によりラッパ状に拡開
する部分１８によって形成され、その拡開部分１８の周
辺が滑らかなＲ面によって副燃焼室４′の円筒部分１９
に接続している。The feature of this embodiment is that the opening of the primary air passage 11' and the accompanying guide vane 10' are provided as close to the main combustion chamber 5 as possible in the cylindrical wall forming the sub-combustion chamber 4'.
As a result, a distance Y of approximately 1/2 of the diameter of the auxiliary combustion chamber 4' is provided between the opening front end of the primary air passage 11' and the nozzle 16 of the fuel injection valve 8. This is because a spray evaporation space 17 into which no air is blown is formed in the front part. In the case of the first embodiment, the front part of the auxiliary combustion chamber 4' has a chamber wall welded to the outer periphery of the flange portion 7, which has a trumpet-like opening angle θ' that is approximately the same as the fuel spray angle θ (approximately 45°). The cylindrical portion 19 of the sub-combustion chamber 4' is formed by a portion 18 which expands into
is connected to.
加圧された燃料が燃料噴射弁８の噴口１６から噴射され
ると、噴霧蒸発空間１７の中へ噴射角θを有する円錐状
に拡散し、減圧されると共に燃焼ガスや燃焼室壁からの
輻射熱を受けて液体の粒である燃料粒が蒸発し、すみや
かに気体状の燃料になる。When the pressurized fuel is injected from the nozzle 16 of the fuel injection valve 8, it diffuses into the spray evaporation space 17 in a conical shape with an injection angle θ, and is depressurized and radiated heat from the combustion gas and the combustion chamber wall. As a result, the liquid fuel particles evaporate and quickly become gaseous fuel.
そして気化が進んだ状態で円筒部分１９に入り、１次空
気通路１１′から接線方向に流入する１次空気と出会い
、渦流を形成しながら燃料分子と空気がよく混合して着
火・燃焼する。The vaporized state then enters the cylindrical portion 19, where it encounters the primary air flowing tangentially from the primary air passage 11', where the fuel molecules and air mix well while forming a vortex, resulting in ignition and combustion.
したがって燃焼効率が高く、燃焼が安定し、可燃限界が
高くて着火性・始動性も良くなる。拡開部分１８の開き
角θ′は燃料の噴霧角θと略同じ大きさにとっであるか
ら、噴霧蒸発空間１７は最小の容積で燃料に対し十分な
蒸発・気化作用をもたらし、デッドスペースがないから
２次的な渦流の停滞によるカーボンの堆積も起こらない
。Therefore, combustion efficiency is high, combustion is stable, flammability limit is high, and ignitability and startability are improved. Since the opening angle θ' of the expanding portion 18 is set to approximately the same size as the fuel spray angle θ, the spray evaporation space 17 provides sufficient evaporation and vaporization action for the fuel with the minimum volume, and no dead space is created. Since there is no such thing, carbon deposition due to secondary vortex stagnation does not occur.
燃焼効率の点では第１図〜第３図に示した第１実施例に
対して若干劣るが、同様に可燃限界が高く、燃焼安定性
に優れている第２実施例を第７図に示す。参照符号は既
に述べたものと共通であるが、この実施例は、第１実施
例にぐらべて副燃焼室４″の形が相違する。燃料噴射弁
８の先端と１次空気通路１１′の前端との距離Ｙは、や
はり副燃焼室４′の直径りの１７２程度と大きくとり、
燃料のための十分な大きさの噴霧蒸発空間１７′を形成
しているが、その形状はラッパ形でなく略円筒形である
。The second embodiment is shown in FIG. 7, which is slightly inferior to the first embodiment shown in FIGS. 1 to 3 in terms of combustion efficiency, but has a similarly high flammability limit and excellent combustion stability. . Although the reference numerals are the same as those already described, this embodiment differs from the first embodiment in the shape of the auxiliary combustion chamber 4''.The tip of the fuel injection valve 8 and the primary air passage 11' The distance Y from the front end of the auxiliary combustion chamber 4' is set as large as 172 mm, which is the diameter of the auxiliary combustion chamber 4'.
A sufficiently large spray evaporation space 17' for fuel is formed, but its shape is not a trumpet shape but a substantially cylindrical shape.
これらの例について空気流量（Ｇａ）と燃料流量（Ｇｆ
）の比を変化させた場合の可燃限界を調べて線図として
示したものが第８図である。燃料が希薄となる領域では
、空燃比がそれ以上大きくなると安定燃焼を続けること
ができなくなる可燃限界が存在するが、可燃限界は前記
の距離Ｙの大きさによって著しく変化することが判明し
た。試作実験に使用した第１実施例（第１図〜第３図に
示したもの。第８図における曲線Ａ）、第２実施例（第
７図に示したもの。第８図の曲線Ｂ）のほかに、比較例
として第９図に示したもの（曲線Ｃ）、及び第１０図に
示したもの（曲線Ｄ）の特性も調べて同じ第８図に表示
した。For these examples, the air flow rate (Ga) and fuel flow rate (Gf
Fig. 8 is a diagram showing the flammability limit when the ratio of ) is changed. In a region where the fuel is lean, there is a flammability limit beyond which stable combustion cannot continue if the air-fuel ratio increases, but it has been found that the flammability limit changes significantly depending on the size of the distance Y mentioned above. The first example (shown in Figures 1 to 3; curve A in Figure 8) and the second example (shown in Figure 7; curve B in Figure 8) used in the prototype experiment. In addition, the characteristics of the comparative examples shown in FIG. 9 (curve C) and those shown in FIG. 10 (curve D) were also investigated and are shown in FIG.
第９図及び第１０図に示した比較例は、いずれも噴口１
６の位置と１次空気通路１１″及び１１ ’の開口の前
方端位置とが一致していて、前述の距離Ｙが零の場合で
あり、燃料は燃料噴射弁８から噴射されると同時に１次
空気すの旋回流に巻き込まれ、直ちに着火される。した
がって燃料の液粒は蒸発・気化のいとまを与えられるこ
となく燃焼域に送り込まれるため燃焼が完全に行なわれ
ない。また、遠心力により副燃焼室４″及び４″′の室
壁に振りとばされて付着する燃料の量も多く、それが熱
分解してカーボンの堆積を生じやすい。さらに第９図の
ように、１次空気通路１１″の後端と絞り開口１２との
間に大きな距離ｌがあると、絞り開口１２が１次空気す
の一部によって被覆されるとか冷却されるということが
ないから、絞り開口１２が燃焼ガスの接触によって溶損
しやすいという別の問題もある。In both the comparative examples shown in FIGS. 9 and 10, the nozzle 1
6 and the front end positions of the openings of the primary air passages 11'' and 11' coincide, the aforementioned distance Y is zero, and fuel is injected from the fuel injection valve 8 at the same time as 1. The fuel droplets are then caught up in the swirling flow of air and immediately ignited.Therefore, the fuel droplets are sent into the combustion zone without being given time to evaporate or vaporize, so combustion does not occur completely.Also, centrifugal force As a result, a large amount of fuel is blown off and adhered to the walls of the auxiliary combustion chambers 4'' and 4'', which tends to thermally decompose and cause carbon deposits.Furthermore, as shown in Figure 9, If there is a large distance l between the rear end of the air passage 11'' and the diaphragm opening 12, the diaphragm opening 12 will not be covered or cooled by a part of the primary air chamber. Another problem is that it is susceptible to erosion due to contact with combustion gases.
本発明の２つの実施例（第１図Ａ１第７面Ｂ）と２つの
比較例（第９図Ｃ・第１０図Ｄ）の可燃限界を比較して
示す第８図から判るように、各曲線の右下の領域である
燃焼安定範囲の広さは、Ａ＞Ｂ＞Ｃ＞Ｄ
のように副燃焼室の構造によって著しい違いを示した。As can be seen from FIG. 8, which shows a comparison of the flammability limits of two embodiments of the present invention (FIG. 1 A1, seventh surface B) and two comparative examples (FIGS. 9 C and 10 D), each The breadth of the stable combustion range, which is the area on the lower right of the curve, showed significant differences depending on the structure of the sub-combustion chamber, such as A>B>C>D.
本発明の２つの実施例は副燃焼室の上流側に噴霧蒸発空
間１７．１７’を備えているために共に高い可燃限界を
有し、非常に希薄な燃料空気の混合物でも着火し、安定
に燃焼するから、燃焼効率もアイドル時でＡが９８％、
Ｂが９５％と高い。これに反して、２つの比較例の場合
はＹの距離が零であって、燃料が噴射されると直ちに１
次空気すの旋回流に巻き込まれるから吹き消えも多（、
燃料が十分に濃くないと着火することができない。また
、燃焼効率も低く、カーボンの発生・堆積も多くなる。Both embodiments of the present invention have a high flammability limit because they are equipped with a spray evaporation space 17,17' upstream of the sub-combustion chamber, and even a very lean fuel-air mixture can be ignited stably. Since it burns, the combustion efficiency is 98% for A at idle.
B is high at 95%. On the other hand, in the two comparative examples, the distance Y is zero, and the distance Y is 1 immediately after the fuel is injected.
It often gets blown out because it gets caught up in the swirling flow of air.
If the fuel is not rich enough, it will not be possible to ignite. Furthermore, combustion efficiency is low, and carbon generation and deposition increases.
第８図に記入した直線はＹの値が副燃焼室４の直径りの
１／４とした場合であって、Ｙの値がこれより小さくな
ると比較例Ｃ，Ｄのように可燃限界が低下し、燃焼効率
が悪化する。しかしながら、Ｙの値があまりに大きい場
合も、前述のように１次空気の混合が遅れて不完全燃焼
となり、カーボンを発生するが、実験の結果、良好な燃
焼状態をもたらすＹの値の最大値は、副燃焼室の直径り
と同程度の値であることが確認されている。なお、第８
図における点ａはアイドル時を示すものである。The straight line drawn in Figure 8 is when the value of Y is set to 1/4 of the diameter of the auxiliary combustion chamber 4, and when the value of Y is smaller than this, the flammability limit decreases as in Comparative Examples C and D. However, combustion efficiency deteriorates. However, if the value of Y is too large, as mentioned above, the mixing of the primary air will be delayed resulting in incomplete combustion and carbon will be generated.However, as a result of experiments, the maximum value of Y that produces good combustion conditions It has been confirmed that the value is approximately the same as the diameter of the auxiliary combustion chamber. In addition, the 8th
Point a in the figure indicates the idle time.
本発明により可燃限界が高くなり、燃焼効率が向上して
安定燃焼の範囲が著しく広くなるので、低負荷時にも燃
焼が停止するようなおそれがなく、またカーボンの発生
・堆積も少なくなるので、堆積したカーボンによるトラ
ブルも避けることができる。また、燃焼状態が良好とな
るために、ＨＣや白煙、または黒煙の発生も少なくなる
。The present invention increases the flammability limit, improves combustion efficiency, and significantly widens the range of stable combustion, so there is no risk of combustion stopping even at low loads, and the generation and deposition of carbon is reduced. Trouble caused by deposited carbon can also be avoided. Furthermore, since the combustion condition is improved, the generation of HC, white smoke, or black smoke is also reduced.
第１図は本発明の第１実施例の全体構成を示す縦断面図
、第２図は第１図の■−■断面図、第３図は第１図の要
部を拡大して示す縦断面図、第４図は従来例の全体構成
を示す縦断面図、第５図は第４図の■−■断面図、第６
図は第４図の要部を拡大して示す縦断面図、第７図は本
発明の第２実施例の全体構成を示す縦断面図、第８図は
可燃限界の特性を比較して示す線図、第９図及び第１０
図はそれぞれ比較例の全体構成を示す縦断面図である。
１・・・燃焼器外筒、 ２・・・燃焼器内筒、３・・
・通気間隙、
４′ ・４” 、４”’・・・副燃焼室、５・・・主燃
焼室、 ６・・・端部壁、７・・・フランジ部、
訃・・燃料噴射弁、９・・・点火プラグ、 １０．
１０’・・・案内羽根、１１・１１’ 、 １１”
、 １１”’・・・１次空気通路、１２・・・絞り開口
、 １３．１３’・・・空気孔、１４・・・流出筒
、 １５・・・希釈空気口、１６・・・噴口、
１７．１７’・・・噴霧蒸発空間、１８・・・
拡開部分、 １９・・・円筒部分、ａ・・・加圧空
気、 ｂ・・・１次空気、Ｃ，Ｃ’・・・２次空気
及び冷却空気、ｄ・・・希釈空気、 ｆ・・・軽油
、ｇ・・・タービン作動ガス、
ｌ・・・距離、
Ｙ・・・噴口と１次空気通路との距離、θ・・・噴霧角
、 θ′・・・開き角。
第３図
第１
４′・・・副燃焼室
訃・・燃料噴射弁
１１’・・・１次空気通路
図
】７・・・噴霧蒸発空間
ｂ・・・１次空気
Ｙ・・・距 離
第
国
第
４・・・副燃焼室
５・・・主燃焼室
１１・・・１次空気通路
図
１６・・・噴 口
ｂ・・・１次空気
第
図
第
図
燃料流量ＧｆFIG. 1 is a vertical sectional view showing the overall configuration of the first embodiment of the present invention, FIG. 2 is a sectional view taken along the line ■-■ in FIG. 1, and FIG. 4 is a vertical cross-sectional view showing the overall configuration of the conventional example, FIG. 5 is a sectional view taken along ■--■ of FIG.
The figure is a longitudinal sectional view showing an enlarged view of the main part of Fig. 4, Fig. 7 is a longitudinal sectional view showing the overall configuration of the second embodiment of the present invention, and Fig. 8 shows a comparison of the characteristics of the flammability limit. Diagrams, Figures 9 and 10
Each figure is a longitudinal sectional view showing the overall structure of a comparative example. 1... Combustor outer cylinder, 2... Combustor inner cylinder, 3...
・Vent gap, 4'・4",4"'... Sub-combustion chamber, 5... Main combustion chamber, 6... End wall, 7... Flange part,
Death...Fuel injection valve, 9...Spark plug, 10.
10'...Guide vane, 11.11', 11"
, 11'''...Primary air passage, 12...Aperture opening, 13.13'...Air hole, 14...Outflow tube, 15...Dilution air port, 16...Nozzle port,
17.17'...Spray evaporation space, 18...
Expanding part, 19... Cylindrical part, a... Pressurized air, b... Primary air, C, C'... Secondary air and cooling air, d... Dilution air, f. ...Light oil, g...Turbine working gas, l...Distance, Y...Distance between nozzle and primary air passage, θ...Spray angle, θ'...Opening angle. Fig. 3 1 4'...Sub-combustion chamber...Fuel injection valve 11'...Primary air passage diagram]7...Spray evaporation space b...Primary air Y...Distance Country No. 4...Sub-combustion chamber 5...Main combustion chamber 11...Primary air passage diagram 16...Nozzle b...Primary air diagram Diagram Fuel flow rate Gf
Claims (1)
に流入させる１次空気通路とを備え内部に燃焼ガスの渦
流を発生させる副燃焼室と、前記副燃焼室の下流側に接
続する主燃焼室からなり、前記１次空気通路の前記副燃
焼室の壁面における開口の上流端は、前記燃料噴射弁の
噴口との間に所定の距離Ｙを有し、前記距離Ｙの値は前
記副燃焼室の直径をＤとして、 Ｄ／４≦Ｙ≦Ｄ の範囲から選定されており、それによって前記副燃焼室
の上流側に所定の大きさの燃料の噴霧蒸発空間が形成さ
れていることを特徴とする副燃焼室式渦巻燃焼器。[Scope of Claims] A sub-combustion chamber that includes a fuel injection valve provided on the upstream side and a primary air passage through which primary air flows tangentially, and generates a vortex flow of combustion gas therein; and the sub-combustion chamber. The upstream end of the opening in the wall surface of the auxiliary combustion chamber of the primary air passage has a predetermined distance Y from the nozzle of the fuel injection valve, and The value of the distance Y is selected from the range of D/4≦Y≦D, where D is the diameter of the sub-combustion chamber, thereby creating a fuel spray evaporation space of a predetermined size on the upstream side of the sub-combustion chamber. A sub-combustion chamber type swirl combustor characterized by the following:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP25303390A JPH04131620A (en) | 1990-09-22 | 1990-09-22 | Sub-combustion chamber type swirling combustion device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP25303390A JPH04131620A (en) | 1990-09-22 | 1990-09-22 | Sub-combustion chamber type swirling combustion device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04131620A true JPH04131620A (en) | 1992-05-06 |
Family
ID=17245548
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP25303390A Pending JPH04131620A (en) | 1990-09-22 | 1990-09-22 | Sub-combustion chamber type swirling combustion device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04131620A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008047825A1 (en) * | 2006-10-20 | 2008-04-24 | Ihi Corporation | Gas turbine combustor |
| JP2009287888A (en) * | 2008-05-30 | 2009-12-10 | Ihi Corp | Burner |
| JP2011007430A (en) * | 2009-06-26 | 2011-01-13 | Ihi Corp | Combustor for micro gas turbine |
| CN106594801A (en) * | 2015-10-16 | 2017-04-26 | 中航商用航空发动机有限责任公司 | Low-pollution combustion chamber adopting forced diversion at main-combustion-stage outlet |
-
1990
- 1990-09-22 JP JP25303390A patent/JPH04131620A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008047825A1 (en) * | 2006-10-20 | 2008-04-24 | Ihi Corporation | Gas turbine combustor |
| JPWO2008047825A1 (en) * | 2006-10-20 | 2010-02-25 | 株式会社Ihi | Gas turbine combustor |
| US9038392B2 (en) | 2006-10-20 | 2015-05-26 | Ihi Corporation | Gas turbine combustor |
| JP2009287888A (en) * | 2008-05-30 | 2009-12-10 | Ihi Corp | Burner |
| JP2011007430A (en) * | 2009-06-26 | 2011-01-13 | Ihi Corp | Combustor for micro gas turbine |
| CN106594801A (en) * | 2015-10-16 | 2017-04-26 | 中航商用航空发动机有限责任公司 | Low-pollution combustion chamber adopting forced diversion at main-combustion-stage outlet |
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