JPH0573971B2 - - Google Patents
Info
- Publication number
- JPH0573971B2 JPH0573971B2 JP29926786A JP29926786A JPH0573971B2 JP H0573971 B2 JPH0573971 B2 JP H0573971B2 JP 29926786 A JP29926786 A JP 29926786A JP 29926786 A JP29926786 A JP 29926786A JP H0573971 B2 JPH0573971 B2 JP H0573971B2
- Authority
- JP
- Japan
- Prior art keywords
- combustor
- water
- injection device
- combustion
- fuel
- 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.)
- Expired - Lifetime
Links
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 55
- 238000002347 injection Methods 0.000 claims description 37
- 239000007924 injection Substances 0.000 claims description 37
- 238000002485 combustion reaction Methods 0.000 claims description 36
- 239000000446 fuel Substances 0.000 claims description 35
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 13
- 239000007921 spray Substances 0.000 description 12
- 239000000567 combustion gas Substances 0.000 description 9
- 230000008020 evaporation Effects 0.000 description 4
- 238000001704 evaporation Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明はタービンエンジンの燃焼器に係り、特
に該燃焼器のNox低減化のための水噴射装置の
改善に関する。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a combustor for a turbine engine, and more particularly to an improvement in a water injection device for reducing Nox in the combustor.
（従来の技術）
一般に、タービンエンジンからの排気には窒素
酸化物、いわゆるNoxが多く含まれており、こ
のNoxの発生は燃焼器の燃焼温度が上昇すると
ともに増大する傾向がある。このために、Nox
の発生を低減するには燃焼最高温度を下げること
が効果があることが知られている。(Prior Art) Generally, exhaust gas from a turbine engine contains a large amount of nitrogen oxides, so-called Nox, and the generation of Nox tends to increase as the combustion temperature of the combustor increases. For this, Nox
It is known that lowering the maximum combustion temperature is effective in reducing the occurrence of
このため、従来のタービンエンジンの燃焼器の
燃料噴射装置７の内部または周囲に水噴射装置１
６から加圧した水を噴射し、その蒸発熱により一
次燃焼領域１３の燃焼室最高温度を下げNoxの
発生を低減しているものが知られている（特公昭
52−7083号公報参照）。 For this reason, the water injection device 1 is installed inside or around the fuel injection device 7 of the combustor of a conventional turbine engine.
It is known that pressurized water is injected from 6 and the heat of evaporation is used to lower the maximum temperature of the combustion chamber in the primary combustion area 13 and reduce the generation of Nox (Tokuko Sho).
(See Publication No. 52-7083).
（発明が解決しようとする問題点）
ところが、一般にタービンエンジンの燃焼器で
は、燃焼による高温度が発生する個所は次の２ケ
所とされている。(Problems to be Solved by the Invention) However, in general, in the combustor of a turbine engine, high temperatures due to combustion occur at the following two locations.
すなわちそのうちの１ケ所は、燃料噴射装置７
から噴射される燃料が、アシストスワラ１０から
の燃焼用補助空気により旋回されて約90°の広が
りとなつて燃焼する噴霧円錐１１の外端部Ａと、
他の１ケ所はメインスワラ１５からの燃焼用主空
気による旋回流により遠心力で燃焼器ライナ１２
の湾曲部で燃焼する肩部Ｂとである。 In other words, one of them is the fuel injection device 7.
an outer end A of the spray cone 11 where the fuel injected from the spray cone 11 is swirled by the combustion auxiliary air from the assist swirler 10 and burns with a spread of about 90°;
The other location is located on the combustor liner 12 due to the centrifugal force due to the swirling flow of the main air for combustion from the main swirler 15.
The shoulder part B burns at the curved part of the shoulder part B.
ところで前記した従来装置では、前者の噴霧円
錐１１の外端部Ａは水噴射装置１６から噴射する
水滴によつて燃焼最高温度を低下させてNoxの
発生を低減することができるが、前記水噴射装置
１６からの水滴は後者の燃焼器ライナ１２の肩部
Ｂまでは到達せず、この肩部Ｂでの燃焼最高温度
を低下させることができないので、この肩部Ｂで
のNoxの発生を低減させることができないもの
である。 By the way, in the conventional device described above, the outer end A of the former spray cone 11 can lower the maximum combustion temperature and reduce the generation of Nox by the water droplets injected from the water injection device 16. The water droplets from the device 16 do not reach the shoulder B of the latter combustor liner 12, and the maximum combustion temperature at this shoulder B cannot be lowered, so the generation of Nox at this shoulder B is reduced. It is something that cannot be done.
（問題点を解説するための手段）
そこで本発明は、前記従来装置の問題点を解決
するための手段として、第１図ないし第３図に例
示する如く、燃焼器１の軸中央に燃料噴射装置７
と水噴射装置１６とを同心的に設け、更に燃料噴
射装置７および水噴射装置１６の外周に燃焼器１
に燃焼用主空気を導入し旋回させるメインスワラ
１５を同心的に設けたタービンエンジンの燃焼器
において、前記水噴射装置１６の水路１８先端の
ノズル１９の上流側に前記メインスワラ１５に面
して開口する多数の水噴射孔２０を穿設したもの
である。(Means for explaining the problems) Therefore, as a means for solving the problems of the conventional device, the present invention provides fuel injection at the center of the axis of the combustor 1, as illustrated in FIGS. 1 to 3. Device 7
and a water injection device 16 are provided concentrically, and a combustor 1 is further provided on the outer periphery of the fuel injection device 7 and the water injection device 16.
In a turbine engine combustor in which a main swirler 15 for introducing and swirling main air for combustion is provided concentrically, an opening facing the main swirler 15 is provided on the upstream side of a nozzle 19 at the tip of a waterway 18 of the water injection device 16. A large number of water injection holes 20 are provided.
（作用）
本発明は前記手段により、メインスワラ１５に
面して開口する水噴出孔２０から噴出する水滴が
メインスワラ１５の旋回空気流に乗つて燃焼器ラ
イナ１２の肩部Ｂまで到達し、この水滴の蒸発熱
を燃焼ガスにより奪つて、燃焼最高温度を下げ、
同時に水噴射装置１６よりの噴射水滴により噴霧
円錐１１の外端部Ａでの燃焼最高温度を下げるこ
とと相俟つて、高温の発生する前記外端部Ａおよ
び肩部ＢでのNoxの発生を低減させるものであ
る。(Function) By the above-mentioned means, the present invention allows water droplets ejected from the water ejection holes 20 opened facing the main swirler 15 to ride on the swirling airflow of the main swirler 15 and reach the shoulder portion B of the combustor liner 12. The heat of evaporation is taken away by the combustion gas, lowering the maximum combustion temperature,
At the same time, the water droplets injected from the water injection device 16 lower the maximum combustion temperature at the outer end A of the spray cone 11, and at the same time, reduce the generation of Nox at the outer end A and shoulder B, where high temperatures occur. It is intended to reduce
（実施例）
以下に図面を参照して本発明の好適な実施例を
詳細に説明する。(Embodiments) Preferred embodiments of the present invention will be described in detail below with reference to the drawings.
第１図ないし第３図は本発明の第１実施例であ
り、符号１は図示しない圧縮機から加圧した空気
の供給を受けて都市ガス等のガス燃料を燃焼さ
せ、燃焼ガスを図示しないガスタービンに供給し
て回転させる釣錐状の燃焼器であり、２は燃焼器
１を覆う燃焼器外筒である。３は燃焼器外筒２の
先端の軸中央に穿設された穴に外側より嵌入する
アウタボデイで、燃焼用補助用空気を燃焼室４に
導入する送気口５を有する。６はアウタボデイ３
を軸方向に貫通する穴にＯリング６ｂによりシー
ルしつつネジ６ａを介して螺合するインナボデイ
である。７は燃焼器１の軸中央に設けられる燃料
噴射装置であり、該燃料噴射装置７はインナボデ
イ６の軸中心を軸方向に貫通し燃料を燃焼室４に
圧送する送油孔８と、燃焼室４に対面した先端に
燃料を低圧で燃焼室４に噴射する燃料弁チツプ９
とからなつている。１０はアシストスワラであ
り、燃料弁チツプ９とアシストスワラー１０はイ
ンナボデイ６とアウタボデイ３の軸方向の間に挟
着されており、該アシストスワラ１０は燃料弁チ
ツプ９の周りに送気口５からの断熱圧縮した300
℃、７気圧の補助空気を燃焼室４に0.4気圧の気
圧差で圧送させて旋回させ、燃料弁チツプ９から
噴射する燃料を第１図点線で図示する如き約90°
の広がりを有する円錐状に噴霧し噴霧円錐１１を
形成する。 Figures 1 to 3 show a first embodiment of the present invention, and reference numeral 1 indicates pressurized air supplied from a compressor (not shown) to combust gas fuel such as city gas, and combustion gas (not shown) It is a cone-shaped combustor that is supplied to a gas turbine and rotated, and 2 is a combustor outer cylinder that covers the combustor 1. Reference numeral 3 denotes an outer body which is fitted from the outside into a hole bored in the center of the shaft at the tip of the combustor outer cylinder 2, and has an air supply port 5 for introducing auxiliary air for combustion into the combustion chamber 4. 6 is outer body 3
This is an inner body that is screwed into a hole passing through the body in the axial direction through a screw 6a while being sealed with an O-ring 6b. Reference numeral 7 denotes a fuel injection device provided at the axial center of the combustor 1, and the fuel injection device 7 has an oil feed hole 8 that passes through the axial center of the inner body 6 in the axial direction and pumps fuel into the combustion chamber 4, and a fuel valve chip 9 whose tip facing 4 injects fuel into the combustion chamber 4 at low pressure;
It is made up of. Reference numeral 10 denotes an assist swirler, and the fuel valve tip 9 and the assist swirler 10 are sandwiched between the inner body 6 and the outer body 3 in the axial direction. Adiabatic compression of 300
℃, 7 atmospheres of auxiliary air is forced into the combustion chamber 4 with a pressure difference of 0.4 atmospheres, and the fuel is injected from the fuel valve tip 9 at an angle of about 90 degrees as shown by the dotted line in Figure 1.
A spray cone 11 is formed by spraying in a conical shape having a spread of .
１２は燃焼器外筒２内で、かつ燃料噴射装置７
を有するインナボデイ６およびインナボデイ６の
外周にネジ部６ａより螺合するアウタボデイ３の
外側に位置する燃焼器ライナであり、該燃焼器ラ
イナ１２の内側を前記燃焼室４の一次燃焼領域１
３に、燃焼器ライナ１２の外側で燃焼器外筒２と
の間を圧縮機から圧送される燃焼用主空気の送気
通路１４にそれぞれ形成し、燃焼気ライナ１２の
基部に送基通路１４に連通し燃焼用主空気を0.4
気圧の圧力差で圧送して旋回させて燃焼させるメ
インスワラ１５を燃料噴射装置７および後述の水
噴射装置１６と同心的に形成する。 12 is inside the combustor outer cylinder 2 and the fuel injection device 7
It is a combustor liner located outside the outer body 3 which is screwed into the outer periphery of the inner body 6 and the inner body 6 through the threaded portion 6a, and the inside of the combustor liner 12 is connected to the primary combustion area 1 of the combustion chamber 4.
3, an air supply passage 14 is formed between the combustor outer cylinder 2 and the combustor outer cylinder 2 on the outside of the combustor liner 12, and an air supply passage 14 is formed at the base of the combustion air liner 12. The main air for combustion is communicated to 0.4
A main swirler 15 is formed concentrically with the fuel injection device 7 and the water injection device 16, which will be described later, to be fed under pressure using a pressure difference, swirled, and combusted.
しかして、１６は本発明の特徴をなす水噴射装
置１６であり、該水噴射装置１６は前記燃料噴射
装置７と同心的に設け、アウタボデイ３内を軸方
向に燃焼室４に向けて水路１８を形成し、次いで
その先はアウタボデイ３の外周と燃焼室ライナ１
２の内周との間の〓間を水路１８とし、水路１８
の先端をノズル１９として、該ノズル１９より水
滴を噴霧円錐１１内の燃焼ガスに噴霧し、噴霧円
錐１１の外端部Ａの燃焼ガスの最高温度を低下さ
せる。 Reference numeral 16 denotes a water injection device 16 which is a feature of the present invention, and the water injection device 16 is provided concentrically with the fuel injection device 7, and is directed toward the combustion chamber 4 in the axial direction within the outer body 3. , and then the outer periphery of the outer body 3 and the combustion chamber liner 1
The space between the inner periphery of 2 and the inner circumference of
The tip of the nozzle 19 is used to spray water droplets onto the combustion gas within the spray cone 11, thereby lowering the maximum temperature of the combustion gas at the outer end A of the spray cone 11.
なお、１７は前記水路１８に水を供給するアウ
タボデイ３に穿設した送水口である。 Incidentally, reference numeral 17 denotes a water supply port drilled in the outer body 3 for supplying water to the water channel 18.
そして、前記ノズル１９の上流側のメインスワ
ラ１５に面する燃焼器ライナ１２の半径方向に多
数の水噴出孔２０を、その流路断面積の和が前記
ノズル１９の流路断面積に対して約２：１となる
如くして、水噴出孔２０からメインスワラ１５の
方向に水滴を噴出させ、メインスワラ１５によつ
て旋回させられた燃焼用主空気と混合して燃焼器
ライナ１２の湾曲部である肩部Ｂ付近の燃焼ガス
の最高温度を低下させるものである。 A large number of water jet holes 20 are provided in the radial direction of the combustor liner 12 facing the main swirler 15 on the upstream side of the nozzle 19, so that the sum of the flow passage cross-sectional areas thereof is approximately equal to the flow passage cross-sectional area of the nozzles 19. Water droplets are ejected from the water ejection holes 20 in the direction of the main swirler 15 at a ratio of 2:1, and are mixed with the main combustion air swirled by the main swirler 15 to form a curved portion of the combustor liner 12. This lowers the maximum temperature of combustion gas near shoulder B.
叙上の如く構成したガスタービンエンジンの燃
焼器の作動について説明する。 The operation of the combustor of the gas turbine engine configured as described above will be explained.
燃料はインナボデイ６内の燃焼噴射装置７の送
油孔８からインナボデイ６の先端に螺合した燃焼
弁チツプ９に導かれ低圧で燃焼室４の一次燃焼領
域１３に噴射される。一方、燃焼を補助する補助
空気は図示しない圧縮機により断熱圧縮した300
℃、７気圧の空気を0.4気圧の気圧差でアウタボ
デイ３の送気口５よりインナボデイ６との間の〓
間を経てインナボデイ６に隣接する燃料弁チツプ
９とアウダボデイ３の間に挟着されたアシストス
ワラ１０に圧送し、アシストスワラ１０の内部に
おいて径方向に対し傾斜する向きに延在せしめた
空気噴出器１０ａにより旋回流とし、前記燃料弁
チツプ９から噴射される燃料と混合し、第１図点
線で図示する如き90°の広がりを有する円錐状に
噴霧化して噴霧円錐１１を形成し、図示しない点
火栓によつて点火し燃焼する。また、送気通路１
４により導入される燃焼用主空気がメインスワラ
１５により旋回流として燃焼を助ける。 Fuel is guided from an oil feed hole 8 of a combustion injection device 7 in the inner body 6 to a combustion valve chip 9 screwed to the tip of the inner body 6, and is injected at low pressure into the primary combustion region 13 of the combustion chamber 4. On the other hand, auxiliary air to assist combustion is adiabatically compressed by a compressor (not shown).
℃, 7 atm air is connected between the air outlet 5 of the outer body 3 and the inner body 6 with a pressure difference of 0.4 atm.
An air injector is configured to force-feed the air to the assist swirler 10 sandwiched between the fuel valve chip 9 adjacent to the inner body 6 and the outer body 3 through the space between the fuel valve chips 9 and the outer body 3, and extend inside the assist swirler 10 in a direction inclined with respect to the radial direction. 10a, the mixture is mixed with the fuel injected from the fuel valve tip 9, and atomized into a conical shape having a 90° spread as shown by the dotted line in FIG. 1 to form a spray cone 11. It is ignited by a stopper and burns. In addition, air supply passage 1
The main air for combustion introduced by the main swirler 15 is turned into a swirling flow to assist combustion.
このとき、アウタボデイ３と燃焼器ライナ１２
との間の水路１８に連通するノズル１９から水滴
噴霧円錐１１に向けて噴出するので、この噴霧水
滴の蒸発熱により噴霧円錐１１の外端部Ａの燃焼
最高温度を低下させるとともに、メインスワラ１
５に面して開口する水噴出孔２０から噴出する水
滴がメインスワラ１５の旋回空気流に乗つて微細
化され燃焼器ライナ１２の肩部Ｂに保持された燃
焼ガスの高温度に導かれ、同じくこの水滴の蒸発
熱を燃焼ガスより奪つて燃焼最高温度を低下さ
せ、Noxの発生を低減するものである。 At this time, the outer body 3 and the combustor liner 12
The water droplets are ejected toward the spray cone 11 from the nozzle 19 communicating with the waterway 18 between the main swirler 1 and the main swirler 1.
Water droplets ejected from the water jet holes 20 that open facing the combustor liner 15 are atomized by the swirling air flow of the main swirler 15, and are guided to the high temperature of the combustion gas held on the shoulder B of the combustor liner 12. The heat of evaporation of these water droplets is taken away from the combustion gas, lowering the maximum combustion temperature and reducing the generation of Nox.
なお、前記実施例では水噴出孔２０の流路断面
積の和をノズル１９の流路断面積に対して２：１
としたが、この値は適宜決定して良いものであ
る。 In the above embodiment, the sum of the cross-sectional areas of the water jet holes 20 is 2:1 with respect to the cross-sectional area of the nozzles 19.
However, this value may be determined as appropriate.
また、前記実施例では水噴出孔２０は水路１８
のノズル１９の上流側にメインスワラ１５に面す
る燃焼器ライナ１２の半径方向に形成したが、該
水噴出孔２０は第２図に図示する如くメインスワ
ラ１５に対面する如く燃焼器ライナ１２に斜めに
穿設しても良く、また、図示しないが、メインス
ワラ１５近くに水を導入するパイプを設けて、該
パイプに多数の水噴出孔をメインスワラ方向に向
けて穿設しても良いものである。 Further, in the embodiment, the water jet hole 20 is
The water jet holes 20 are formed on the upstream side of the nozzle 19 in the radial direction of the combustor liner 12 facing the main swirler 15, but the water jet holes 20 are formed diagonally in the combustor liner 12 so as to face the main swirler 15 as shown in FIG. Alternatively, although not shown, a pipe for introducing water may be provided near the main swirler 15, and a large number of water jet holes may be bored in the pipe toward the main swirler.
叙上の如き水噴射装置を設けたガスタービンの
燃焼器でのガスタービン出力に対するNox排出
量を水噴射量０／hr、30／hr、60／hrで比
較したものを第３図に図示するが、例えば出力
200KWのとき水噴射量０／hrのときNox濃度
は約80P.P.Mであるが、水噴射量を30／hr、60
／hrとしたときのNox濃度はそれぞれ約35P.P.
M、25P.P.Mとなり、特に水噴射量30／hr（水
の燃料に対する噴射割合約25％）としたときに
Nox濃度を約50％以上低減できる顕著な効果が
あることが第３図により明白である。 Figure 3 shows a comparison of the NOx emissions relative to the gas turbine output in the combustor of a gas turbine equipped with a water injection device as described above, with water injection amounts of 0/hr, 30/hr, and 60/hr. but for example the output
At 200KW, the Nox concentration is approximately 80P.PM when the water injection amount is 0/hr, but when the water injection amount is 30/hr and 60
/hr, the Nox concentration is approximately 35P.P.
M, 25P.PM, especially when the water injection amount is 30/hr (injection ratio of water to fuel is about 25%).
It is clear from FIG. 3 that there is a remarkable effect of reducing the Nox concentration by about 50% or more.
次に、燃料を常時は都市ガス、非常時（例えば
地震の時）には液体燃料に自動的に切換える第２
実施例としての２燃料方式のタービンエンジンの
燃焼器について第４図および第５図を参照して説
明する。 Next, there is a second system that automatically switches the fuel to city gas at all times and to liquid fuel in emergencies (for example, during an earthquake).
A combustor for a two-fuel type turbine engine as an example will be described with reference to FIGS. 4 and 5. FIG.
本実施例の構造は前記第１実施例とほぼ同一で
あるので詳細は省略するが、第４図図示の如く、
燃焼器２の燃料噴射装置７の送油孔８にガス燃料
を供給する配管中に遮断弁Ｘを、また液体燃料を
供給する配管中に遮断弁Ｙを、また水噴射装置１
６の送水口１７に水を供給する配管中に遮断弁Ｚ
をそれぞれ設け、各遮断弁Ｘ、Ｙ、Ｚを第５図図
示の如く開閉する。 The structure of this embodiment is almost the same as that of the first embodiment, so the details will be omitted, but as shown in FIG.
A shut-off valve
A shutoff valve Z is installed in the piping that supplies water to the water supply port 17 of 6.
are provided respectively, and the respective shutoff valves X, Y, and Z are opened and closed as shown in FIG.
すなわち、常時は遮断弁Ｙを閉じるとともに遮
断弁Ｘを開として、都市ガスを燃料として燃焼を
行ない、遮断弁Ｚも開として水を噴霧して燃焼ガ
スの最高温度を低く保つてNoxの低減を計つて
いる。地震などの非常時には感知器によつて遮断
弁Ｙを開いて燃料を液体に切換え、遮断弁ＸはtG
の短時間のタイミングをおいて閉とし、また遮断
弁Ｚは遮断弁Ｙの開と同時に閉とし、遮断弁Ｘの
閉と同時または暫時の猶予をおいて開とする如く
制御する。すなわち、
tW≧tG
とするものである。 In other words, normally shutoff valve Y is closed and shutoff valve X is opened to perform combustion using city gas as fuel, and shutoff valve Z is also open and water is sprayed to keep the maximum temperature of the combustion gas low to reduce NOx. I'm planning. In the event of an emergency such as an earthquake, a sensor opens the shutoff valve Y to switch the fuel to liquid, and the shutoff valve
The shut-off valve Z is closed at the same time as the shut-off valve Y is opened, and the shut-off valve Z is controlled to be closed at the same time as the shut-off valve X is closed or after a short delay. In other words, t W ≧t G.
かくの如く時差をもつて制御するのは、燃料を
都市ガスより液体に切換える時に水の噴射を燃料
の切換より遅らせて保炎を維持し、それによつて
燃料切換時のエンストを防止するためである。 The reason for controlling with such a time difference is to maintain flame stability by delaying water injection when switching fuel from city gas to liquid, thereby preventing engine stalling when switching fuel. be.
（発明の効果）
本発明は叙上の如く構成するものであるので、
メインスワラ１５に面して開口する水噴出孔２０
から噴出する水滴がメインスワラ１５の旋回空気
流に乗つて燃焼器ライナ１２の肩部Ｂまで到達
し、この水滴の蒸発熱を燃焼ガスにより奪つて、
肩部Ｂでの燃焼最高温度を下げ、同時に水噴射装
置１６よりの噴射水滴により噴霧円錐１１の外端
部Ａでの燃焼最高温度を下げることと相俟つて、
高温の発生する前記外端部Ａおよび肩部Ｂでの
Noxの発生を低減させるものである。(Effect of the invention) Since the present invention is constructed as described above,
Water spout hole 20 opening facing main swirler 15
The water droplets ejected from the main swirler 15 reach the shoulder B of the combustor liner 12 on the swirling airflow of the main swirler 15, and the heat of evaporation of these water droplets is taken away by the combustion gas.
In conjunction with lowering the maximum combustion temperature at the shoulder B and at the same time lowering the maximum combustion temperature at the outer end A of the spray cone 11 by means of water droplets injected from the water injection device 16,
At the outer end A and shoulder B where high temperatures occur
This reduces the generation of Nox.
第１図は本発明の好適な第１実施例としてのガ
スタービンエンジンの燃焼器の断面図、第２図は
第１図要部の変形例、第３図は第１実施例の効果
を示すガスタービン出力とNox濃度および水噴
射割合とのグラフ、第４図は燃料をガスと液体と
に切換える２燃料方式のタービンエンジンの燃焼
器の配管系統図、第５図は第４図装置の各遮断弁
の開閉のタイムチヤートである。
１……燃焼器、７……燃料噴射装置、１１……
噴霧円錐、１２……燃焼器ライナ、１５……メイ
ンスワラ、１６……水噴射装置、１８……水路、
１９……ノズル、２０……水噴出孔、Ａ……外端
部、Ｂ……肩部。
FIG. 1 is a sectional view of a combustor of a gas turbine engine as a first preferred embodiment of the present invention, FIG. 2 is a modification of the main part of FIG. 1, and FIG. 3 shows the effect of the first embodiment. A graph of gas turbine output, Nox concentration, and water injection ratio. Figure 4 is a piping system diagram of the combustor of a dual-fuel turbine engine that switches fuel between gas and liquid. Figure 5 is a diagram of each of the devices in Figure 4. This is a time chart of opening and closing of the shutoff valve. 1... Combustor, 7... Fuel injection device, 11...
Spray cone, 12... Combustor liner, 15... Main swirler, 16... Water injection device, 18... Water channel,
19... Nozzle, 20... Water spout hole, A... Outer end, B... Shoulder.
Claims (1)
装置１６とを同心的に設け、更に燃料噴射装置７
および水噴射装置１６の外周に燃焼器１に燃焼用
主空気を導入し旋回させるメインスワラ１５を同
心的に設けたタービンエンジンの燃焼器におい
て、前記水噴射装置１６の水路１８先端のノズル
１９の上流側に前記メインスワラ１５に面して開
口する多数の水噴出孔２０を穿設したことを特徴
とするタービンエンジンの燃焼器。1 A fuel injection device 7 and a water injection device 16 are provided concentrically at the center of the axis of the combustor 1, and the fuel injection device 7
In a turbine engine combustor, a main swirler 15 for introducing and swirling main air for combustion into the combustor 1 is provided concentrically around the outer periphery of the water injection device 16, upstream of the nozzle 19 at the tip of the water channel 18 of the water injection device 16. A combustor for a turbine engine, characterized in that a large number of water jet holes 20 are formed on the side facing the main swirler 15.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP29926786A JPS63150516A (en) | 1986-12-15 | 1986-12-15 | Combustor of turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP29926786A JPS63150516A (en) | 1986-12-15 | 1986-12-15 | Combustor of turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS63150516A JPS63150516A (en) | 1988-06-23 |
| JPH0573971B2 true JPH0573971B2 (en) | 1993-10-15 |
Family
ID=17870328
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP29926786A Granted JPS63150516A (en) | 1986-12-15 | 1986-12-15 | Combustor of turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63150516A (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6367239B1 (en) * | 1998-12-09 | 2002-04-09 | General Electric Company | Fuel delivery systems and method |
| US11140946B2 (en) | 2019-06-06 | 2021-10-12 | Wonderland Switzerland Ag | Magnetic buckle assembly |
-
1986
- 1986-12-15 JP JP29926786A patent/JPS63150516A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS63150516A (en) | 1988-06-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4600151A (en) | Fuel injector assembly with water or auxiliary fuel capability | |
| US5317861A (en) | Method of operating a combustion section supply system having fuel and water injection for a rotary machine | |
| US5593095A (en) | Nozzles for fuel injections | |
| US5201181A (en) | Combustor and method of operating same | |
| US4215549A (en) | Turbocharger combustor system | |
| CA1099528A (en) | Gaseous fuel delivery system | |
| US5862668A (en) | Gas turbine engine combustion equipment | |
| US5685492A (en) | Fuel injector nozzles | |
| KR950001074A (en) | Gas turbine burner | |
| JP2007155170A (en) | Fuel nozzle, gas turbine combustor, fuel nozzle of gas turbine combustor, and remodeling method of gas turbine combustor | |
| US5090625A (en) | Nozzles for in-cylinder fuel injection systems | |
| JPH04227410A (en) | Rear-section charging type fuel nozzle | |
| JPH05149149A (en) | Gas turbine combustor | |
| JPS6233490B2 (en) | ||
| JP3673009B2 (en) | Gas turbine combustor | |
| US4004414A (en) | Combustion chamber for supercharged internal combustion engine | |
| US4835962A (en) | Fuel atomization apparatus for gas turbine engine | |
| US4517802A (en) | Turbocharger combustor method | |
| US4464901A (en) | Turbocharger combustor system | |
| JP2008031847A (en) | Gas turbine combustor, its operating method, and modification method of gas turbine combustor | |
| JP3864238B2 (en) | Fuel injection device | |
| JPH0573971B2 (en) | ||
| US5497743A (en) | Injector for separate control of flow and momentum | |
| US5009589A (en) | Stored energy combustor fuel injection system | |
| JPH08145363A (en) | Gas turbine combustor for liquid fuel |