JPS6356444B2 - - Google Patents
Info
- Publication number
- JPS6356444B2 JPS6356444B2 JP980081A JP980081A JPS6356444B2 JP S6356444 B2 JPS6356444 B2 JP S6356444B2 JP 980081 A JP980081 A JP 980081A JP 980081 A JP980081 A JP 980081A JP S6356444 B2 JPS6356444 B2 JP S6356444B2
- Authority
- JP
- Japan
- Prior art keywords
- combustion chamber
- air
- main combustion
- liner
- main
- 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
Links
- 238000002485 combustion reaction Methods 0.000 claims description 71
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 14
- 239000000446 fuel Substances 0.000 claims description 13
- 238000002347 injection Methods 0.000 claims description 8
- 239000007924 injection Substances 0.000 claims description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 238000002156 mixing Methods 0.000 claims description 7
- 238000009841 combustion method Methods 0.000 claims description 5
- 238000010790 dilution Methods 0.000 claims description 3
- 239000012895 dilution Substances 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 9
- 239000000809 air pollutant Substances 0.000 description 6
- 231100001243 air pollutant Toxicity 0.000 description 6
- 239000000779 smoke Substances 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 5
- 239000000126 substance Substances 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 238000003915 air pollution Methods 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
-
- 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
-
- 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
- F23R3/34—Feeding into different combustion zones
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明はガスタービンから排出される大気汚染
物質を低減させる燃焼方法及び装置に関し、更に
詳しくは始動からアイドルに至る間に排出される
大気汚染物質を低減すると同時に定格運転時の大
気汚染物質を低減する燃焼方法及び装置に関す
る。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a combustion method and apparatus for reducing air pollutants emitted from a gas turbine, and more particularly relates to a combustion method and apparatus for reducing air pollutants emitted from a gas turbine, and more specifically, for reducing air pollution emitted during the period from startup to idling. The present invention relates to a combustion method and apparatus that reduce air pollutants during rated operation while reducing substances.
（従来の技術）
ガスタービンから排出される大気汚染物質の大
部分は燃焼室内部で生成される。(Prior Art) Most of the air pollutants emitted from gas turbines are generated inside the combustion chamber.
これらの大気汚染物質は、THC（全炭化水素）
CO、NOX及び黒煙によつて代表される。 These air pollutants are THC (total hydrocarbons)
Represented by CO, NOx and black smoke.
通常のガスタービンにおいては、上記各排出物
質の特性が第１図に示すようなものとなつてい
る。 In a typical gas turbine, the characteristics of each of the above-mentioned exhaust substances are as shown in FIG.
即ち、THC及びCOは低負荷域で急増し、NOX
及び黒煙は高負荷域で増大する。 That is, THC and CO increase rapidly in the low load range, and NO
and black smoke increases in high load ranges.
殊に、THC及びCOは低負荷域において増加割
合が急上昇し、アイドル時には非常に高い排出量
を呈している。 In particular, the rate of increase of THC and CO increases rapidly in the low load range, and emissions are extremely high during idling.
（発明が解決しようとする課題）
上記排出物質の低減策として種々の改善策が提
案されている。(Problems to be Solved by the Invention) Various improvement measures have been proposed as measures for reducing the above-mentioned discharged substances.
例えば、燃焼室へ入る空気量を低負荷域に少な
くし、高負荷域で空気量を多くするように、可動
吸入ノズルを設ける方式も提案されているが、こ
の方式では、高温、高圧状態での作動の信頼性に
難点があり、末だ実現していない。 For example, a method has been proposed in which a movable intake nozzle is installed to reduce the amount of air entering the combustion chamber in low load ranges and increase the amount of air in high load ranges. There are problems with the reliability of its operation, and it has not yet been realized.
更に、排出物質中のNOX成分を低減させるた
め、２段以上の燃焼を行なわせる方式も公知であ
る。（特開昭53−123712号公報参照）
この方式は高負荷域で多段燃焼を行なわせるよ
うにしているため、低負荷域や始動時及びアイド
ル時のTHC、COの低減が不十分なものとなつて
いる。 Furthermore, in order to reduce NOx components in exhaust materials, a method of performing combustion in two or more stages is also known. (Refer to Japanese Patent Application Laid-Open No. 53-123712) Since this method performs multistage combustion in the high load range, the reduction of THC and CO in the low load range, at startup, and during idling is insufficient. It's summery.
そこで、本発明の目的は燃焼室へ入る空気を予
熱することによつて低負荷域のTHC、COを低減
すると共に、定格運転時に水を導入させるように
して排気中のNOX成分及び黒煙を低減したガス
タービンの燃焼方法及び装置を提供するにある。 Therefore, the purpose of the present invention is to reduce THC and CO in the low load range by preheating the air entering the combustion chamber, and to reduce NOx components in the exhaust and black smoke by introducing water during rated operation. An object of the present invention is to provide a combustion method and apparatus for a gas turbine in which combustion is reduced.
（課題を解決するための手段）
本発明の特徴とする構成は、主燃焼室の上流に
空気予熱燃焼室を設け、始動時からアイドル時に
は該空気予熱燃焼室で主燃焼室へ流入する前の空
気を予熱すると同時に、該予熱空気によつて主燃
焼室を構成するライナを加熱するようにし、更に
定格運転時には前記空気予熱燃焼室で水を気化さ
せて主燃焼室へ該気化した水を導入させた点にあ
る。(Means for Solving the Problems) The characteristic configuration of the present invention is that an air preheating combustion chamber is provided upstream of the main combustion chamber, and from the time of startup to idling, the air preheating combustion chamber is used to prevent air from flowing into the main combustion chamber. At the same time as the air is preheated, the liner constituting the main combustion chamber is heated by the preheated air, and furthermore, during rated operation, water is vaporized in the air preheating combustion chamber and the vaporized water is introduced into the main combustion chamber. The point is that I let it happen.
（実施例）
以下、図によつて本発明の一実施例を詳しく説
明する。(Example) Hereinafter, an example of the present invention will be described in detail with reference to the drawings.
第２図を参照して、燃焼器ケーシング１内には
主燃焼室２を形成するライナ３が設けられ、該ラ
イナ３には１次空気孔４及び冷却空気孔５が形成
されている。主燃焼室２の上流中心には主燃焼噴
射弁６が設けられ、その外周に１次空気導入用ス
ワーラ７が設けられている。 Referring to FIG. 2, a liner 3 forming a main combustion chamber 2 is provided within the combustor casing 1, and the liner 3 has primary air holes 4 and cooling air holes 5 formed therein. A main combustion injection valve 6 is provided at the center upstream of the main combustion chamber 2, and a primary air introduction swirler 7 is provided around its outer periphery.
点火プラグ８はライナ３の壁面付近に突設さ
れ、主燃焼噴射弁６からの噴霧に点火する。 The spark plug 8 is provided protruding near the wall surface of the liner 3 and ignites the spray from the main combustion injection valve 6.
主燃焼室２の上流には空気予熱燃焼室９が設け
られる。空気予熱燃焼室９は細筒状のパイロツト
バーナ部１０と、円錐状に拡開する混合部１１及
び太筒状の覆体１２とからなつている。パイロツ
トバーナ部１０には多数の小空気孔１３が設けら
れ、この小空気孔１３から空気が入り込む。混合
部１１にも複数の空気孔１４から導入される空気
がパイロツトバーナ部１０で燃焼されたガスと混
合する。 An air preheating combustion chamber 9 is provided upstream of the main combustion chamber 2 . The air preheating combustion chamber 9 consists of a narrow cylindrical pilot burner section 10, a conically expanding mixing section 11, and a thick cylindrical cover 12. A large number of small air holes 13 are provided in the pilot burner section 10, and air enters through these small air holes 13. Air introduced into the mixing section 11 through the plurality of air holes 14 is mixed with the gas combusted in the pilot burner section 10.
パイロツトバーナ部１０の上流端中心にはパイ
ロツト燃料及び水を噴射する弁１５が設けられ、
又、パイロツトバーナ部１０の壁面付近には点火
プラグ１６が設けられている。 A valve 15 for injecting pilot fuel and water is provided at the center of the upstream end of the pilot burner section 10.
Further, a spark plug 16 is provided near the wall surface of the pilot burner section 10.
覆体１２は主燃焼室２の１次空気孔４を覆うと
ころまで延びており、予熱された空気を主燃焼室
２内へ導入して燃焼させるようにしている。 The cover 12 extends to cover the primary air hole 4 of the main combustion chamber 2, and allows preheated air to be introduced into the main combustion chamber 2 and combusted.
上記のように構成された本発明の作用につい
て、以下説明する。 The operation of the present invention configured as described above will be explained below.
まず、ガスタービンがアイドル時には、パイロ
ツト燃料Ｐが弁１５を介してパイロツトバーナ部
１０へ噴射される。すると、小空気孔１３から空
気が導入され、点火プラグ１３により点火され
る。よつてパイロツトバーナ部１０内で燃焼が生
起し、混合部１１へ高温燃焼ガスタービンが送ら
れる。混合部１１内へは空気孔１４から空気が導
入され、この空気と燃焼ガスタービンとが混合し
て主燃焼室２内へ導入される空気の予熱が行なわ
れる。予熱温度は必要に応じて適当に設定される
ものではあるが、300℃ないし400℃程度が望まし
い。 First, when the gas turbine is idling, pilot fuel P is injected into the pilot burner section 10 via the valve 15. Then, air is introduced from the small air hole 13 and ignited by the spark plug 13. Combustion thus occurs in the pilot burner section 10 and a high temperature combustion gas turbine is sent to the mixing section 11. Air is introduced into the mixing section 11 through the air hole 14, and the air is mixed with the combustion gas turbine to preheat the air introduced into the main combustion chamber 2. Although the preheating temperature can be appropriately set as necessary, it is preferably about 300°C to 400°C.
燃焼器ケーシング１に導入された空気のうち、
空気予熱燃焼室９へ導入されない分は、覆体１２
の外側と燃焼器ケーシング１との間を通つて主燃
焼室２の下流側から希釈空気として流入する。 Of the air introduced into the combustor casing 1,
The air that is not introduced into the preheating combustion chamber 9 is covered by the cover 12.
Dilution air flows in from the downstream side of the main combustion chamber 2 through between the outside of the main combustion chamber 2 and the combustor casing 1 .
さて、300℃ないし400℃に予熱された空気はス
ワーラ７及び１次空気孔４を介して主燃焼室２内
へ導入される。そして、主燃焼噴射弁６から燃焼
が噴射され、該予熱空気と燃料とが混合して点火
プラグ１６によつて点火される。このため、ここ
で主たる燃焼が行なわれる。この場合、予熱空気
が主燃焼室２を形成するライナ３の上流部分を加
熱するので、ライナ３の温度が高くなつており、
ライナ３の内面に衝突する燃料の蒸発が促進され
で燃焼が良好となる。殊に、ライナ３の温度が
300℃ないし400℃程度になると、噴射された燃料
がライナに衝突して飛びはねる性質を持つように
なる。（これをライデンフロスト現象という）こ
のため、ライナ３の内面への燃料付着に基づく
THCやCOの排出が低減される。 Now, air preheated to 300°C to 400°C is introduced into the main combustion chamber 2 via the swirler 7 and the primary air hole 4. Then, combustion is injected from the main combustion injection valve 6, and the preheated air and fuel are mixed and ignited by the ignition plug 16. Therefore, the main combustion takes place here. In this case, the preheated air heats the upstream portion of the liner 3 forming the main combustion chamber 2, so the temperature of the liner 3 becomes high.
The evaporation of the fuel colliding with the inner surface of the liner 3 is promoted, resulting in better combustion. In particular, if the temperature of liner 3 is
When the temperature reaches around 300℃ or 400℃, the injected fuel collides with the liner and starts to fly away. (This is called the Leidenfrost phenomenon.) Therefore, due to fuel adhesion to the inner surface of liner 3,
Emissions of THC and CO are reduced.
主燃焼室２内の燃焼温度は非常に高温となるの
で、そのままタービンブレードへ導入すると熱的
に問題が生ずる。そこで、前述の空気予熱燃焼室
９の外側をバイパスした非予熱空気を冷却空気孔
５から導入し、燃焼ガスの温度を下げてタービン
ブレードへ導く。 Since the combustion temperature within the main combustion chamber 2 is extremely high, thermal problems will occur if the combustion temperature is directly introduced into the turbine blades. Therefore, the non-preheated air that has bypassed the outside of the air preheating combustion chamber 9 is introduced through the cooling air hole 5 to lower the temperature of the combustion gas and guide it to the turbine blades.
次に、定格運転時には、水Ｗを弁１５を介して
パイロツトバーナ部へ噴射する。この場合には、
空気予熱燃焼室９での燃焼は停止している。噴射
された水は混合部１１内で完全に気化し、主燃焼
室２内へ導入される。気化しない水の一部はライ
ナ３に衝突し、ライナ壁の冷却を行なつて気化す
る。この水噴射によつて主燃焼室２内での燃焼ガ
ス温度が低下し、NOXの生成が抑制されると同
時に、燃焼ガス中の水素分が増加して黒煙の生成
が抑制される。 Next, during rated operation, water W is injected into the pilot burner section through the valve 15. In this case,
Combustion in the air preheating combustion chamber 9 has stopped. The injected water is completely vaporized within the mixing section 11 and introduced into the main combustion chamber 2. A portion of the water that does not vaporize hits the liner 3, cools the liner wall, and vaporizes. This water injection lowers the temperature of the combustion gas in the main combustion chamber 2, suppressing the generation of NOx , and at the same time increases the hydrogen content in the combustion gas, suppressing the generation of black smoke.
（発明の効果）
以上に説明した本発明の構成及び作用から生ず
る本発明の効果は以下のとおりである。(Effects of the Invention) The effects of the present invention resulting from the configuration and operation of the present invention explained above are as follows.
主燃焼室へ導入される空気が予熱され、かつ主
燃焼室を構成するライナ壁の温度が上昇するの
で、始動からアイドルに至る間の主燃焼室での燃
焼性能が向上する。 Since the air introduced into the main combustion chamber is preheated and the temperature of the liner wall constituting the main combustion chamber increases, the combustion performance in the main combustion chamber from startup to idle is improved.
又、火炎の吹き消えが防止されるので、信頼性
が向上する。 Furthermore, since the flame is prevented from blowing out, reliability is improved.
更に又、空気予熱を行なうことにより火炎の吹
き消えのない範囲で燃料−空気当量比の限界を下
げることができるようになり、低NOX化のため
の希薄燃焼を行なうことができるものとなる。 Furthermore, by preheating the air, it becomes possible to lower the limit of the fuel-air equivalence ratio within a range that does not blow out the flame, making it possible to perform lean combustion for low NOx . .
空気予熱によつて始動からアイドルの間の
THC及びCO排出量、その他の大気汚染物質の排
出量が低減する。 From start to idle by air preheating
THC and CO emissions, as well as other air pollutant emissions, will be reduced.
更に、ライナ壁温が高くなるので、ライナ壁面
に対する燃料の付着がなくなり、THC及びCOの
生成が低減される。 Additionally, the increased liner wall temperature eliminates fuel adhesion to the liner wall, reducing the production of THC and CO.
又、燃料の微粒化性能に若干の問題があつたと
しても、空気予熱をしているために燃焼性能が低
下しない。 Furthermore, even if there is a slight problem in the atomization performance of the fuel, the combustion performance will not deteriorate because the air is preheated.
又、良好な燃焼を行なう燃料−空気当量比の範
囲をを大きくとれるので、作動の自由度、設計の
自由度が大きくなる。 Furthermore, since the range of fuel-air equivalence ratios for achieving good combustion can be widened, the degree of freedom in operation and design is increased.
又、定格運転時においても、主燃焼室へ空気を
導入して予混合を行なわせるので、NOX低減が
達成される。 Furthermore, even during rated operation, air is introduced into the main combustion chamber for premixing, thereby achieving NOx reduction.
更に又、定格運転時に水噴射するので、該水噴
射によつて燃焼温度が低下し、排出物質中の
NOX量が低減すると同時に、黒煙の生成量も低
減される。この黒煙排出量の低減は水分の中の水
素分が関与し、燃料のＨ／Ｃ比を大きくしたのと
同様の効果を与えることによる。 Furthermore, since water is injected during rated operation, the water injection lowers the combustion temperature and reduces the amount of exhaust gas.
At the same time as the amount of NOX is reduced, the amount of black smoke generated is also reduced. This reduction in the amount of black smoke emissions is due to the involvement of the hydrogen content in the water, which provides the same effect as increasing the H/C ratio of the fuel.
第１図はガスタービンの排出物質の特性線図、
第２図は本発明の一実施例を示す概略断面図であ
る。
１：燃焼器ケーシング、２：主燃焼室、３：ラ
イナ、４：１次空気孔、５：冷却空気孔、６：主
燃料噴射弁、７：スワーラ、８：点火プラグ、
９：空気予熱燃焼室、１０：パイロツトバーナ
部、１１：混合部、１２：覆体、１３：小空気
孔、１４：空気孔、１５：弁。
Figure 1 is a characteristic diagram of gas turbine exhaust substances.
FIG. 2 is a schematic sectional view showing an embodiment of the present invention. 1: Combustor casing, 2: Main combustion chamber, 3: Liner, 4: Primary air hole, 5: Cooling air hole, 6: Main fuel injection valve, 7: Swirler, 8: Spark plug,
9: Air preheating combustion chamber, 10: Pilot burner section, 11: Mixing section, 12: Cover, 13: Small air hole, 14: Air hole, 15: Valve.
Claims (1)
れた空気予熱燃焼室とからなり、始動時からアイ
ドル時に該空気予熱燃焼室によつて主燃焼室流入
空気の一部を所定温度に予熱し、該予熱された空
気を主燃焼室へ導入して燃料噴射によつて主燃焼
を行なわせ、更に前記予熱された空気の残部で主
燃焼室を構成するライナを加熱し、該ライナ加熱
後の空気をライナに形成された空気孔を介して主
燃焼室へ導入させるとともに、定格運転時には前
記空気予熱燃焼室の燃焼を停止させ、前記空気予
熱燃焼室に水を噴射し、該噴射された水を気化さ
せて主燃焼室へ導入させてなることを特徴とする
ガスタービンの燃焼方法。 ２ 下流側のライナ部に希釈空気流入孔を有する
と共に内部に点火プラグが設置された主燃焼室
と、該主燃焼室よりも上流に配設された空気予熱
燃焼室とからなり、該空気予熱燃焼室は多数の小
空気孔を有するパイロツトバーナ部と円錐状に拡
開するとともに複数個の空気孔を有する混合部
と、主燃焼室の前記希釈空気流入孔よりも上流ま
で覆う覆体とからなり、始動時からアイドル時に
前記パイロツトバーナ部の上流中心にパイロツト
燃料を噴射すると共に定格運転時には該パイロツ
ト燃料の噴射を停止する弁と、定格運転時に前記
パイロツトバーナ部の上流中心に水噴射する弁を
設けたことを特徴とするガスタービンの燃焼装
置。[Claims] 1. Consisting of a main combustion chamber and an air preheating combustion chamber disposed upstream of the main combustion chamber, the air flowing into the main combustion chamber is controlled by the air preheating combustion chamber from startup to idle. A liner that preheats a part of the air to a predetermined temperature, introduces the preheated air into the main combustion chamber to perform main combustion by fuel injection, and further configures the main combustion chamber with the remainder of the preheated air. The air after heating the liner is introduced into the main combustion chamber through the air hole formed in the liner, and during rated operation, combustion in the air preheating combustion chamber is stopped, and water is introduced into the air preheating combustion chamber. A combustion method for a gas turbine, characterized in that the injected water is vaporized and introduced into a main combustion chamber. 2 Consists of a main combustion chamber that has a dilution air inflow hole in the downstream liner part and has a spark plug installed inside, and an air preheating combustion chamber that is disposed upstream of the main combustion chamber. The combustion chamber is composed of a pilot burner section having a large number of small air holes, a mixing section expanding into a conical shape and having a plurality of air holes, and a cover covering upstream of the dilution air inflow hole of the main combustion chamber. a valve that injects pilot fuel at the upstream center of the pilot burner section from startup to idling and stops injection of the pilot fuel during rated operation, and a valve that injects water at the upstream center of the pilot burner section during rated operation. A gas turbine combustion device characterized by being provided with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP980081A JPS57124621A (en) | 1981-01-26 | 1981-01-26 | Combustion method for gas turbine and apparatus therefor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP980081A JPS57124621A (en) | 1981-01-26 | 1981-01-26 | Combustion method for gas turbine and apparatus therefor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS57124621A JPS57124621A (en) | 1982-08-03 |
| JPS6356444B2 true JPS6356444B2 (en) | 1988-11-08 |
Family
ID=11730264
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP980081A Granted JPS57124621A (en) | 1981-01-26 | 1981-01-26 | Combustion method for gas turbine and apparatus therefor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS57124621A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63240616A (en) * | 1987-03-28 | 1988-10-06 | Toshiba Corp | Rom/ram disk device |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005028960A2 (en) * | 2003-09-05 | 2005-03-31 | Delavan Inc. | Pilot combustor for stabilizing combustion in gas turbine engines |
| CN115183273A (en) * | 2022-07-21 | 2022-10-14 | 中国航发沈阳发动机研究所 | Afterburning engine combustion chamber |
-
1981
- 1981-01-26 JP JP980081A patent/JPS57124621A/en active Granted
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63240616A (en) * | 1987-03-28 | 1988-10-06 | Toshiba Corp | Rom/ram disk device |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS57124621A (en) | 1982-08-03 |
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