JPH0315502A - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- JPH0315502A JPH0315502A JP17902088A JP17902088A JPH0315502A JP H0315502 A JPH0315502 A JP H0315502A JP 17902088 A JP17902088 A JP 17902088A JP 17902088 A JP17902088 A JP 17902088A JP H0315502 A JPH0315502 A JP H0315502A
- Authority
- JP
- Japan
- Prior art keywords
- face
- nozzle
- gas turbine
- wall
- combustor
- 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
- 239000000446 fuel Substances 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 claims abstract description 11
- 239000000567 combustion gas Substances 0.000 claims abstract description 3
- 238000002485 combustion reaction Methods 0.000 abstract description 12
- 238000011144 upstream manufacturing Methods 0.000 abstract description 2
- 239000013013 elastic material Substances 0.000 abstract 2
- 238000001816 cooling Methods 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000003993 interaction Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Landscapes
- Combustion Of Fluid Fuel (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業」二の利用分野〕
本発明はガスタービン燃焼器に係り、特に、旋回器を備
えたガスタービン燃焼器に関する。DETAILED DESCRIPTION OF THE INVENTION [Industrial Field of Application] The present invention relates to a gas turbine combustor, and particularly to a gas turbine combustor equipped with a swirler.
旋回器を備えたガスタービン燃焼器の、旋回流に起因す
る燃焼振動の低減には、従来、シングルノズルからマル
チノズルに代える方法がとられていた。これは，同一構
造の旋回器付燃料ノズルを一個使用するものから複数個
使用するものに代え、燃料ノズル近傍での燃焼ガスの流
れを変え、また、複数箇所から発生する燃焼振動の相万
干渉により、振動の低減を図るものである。Conventionally, a method of replacing a single nozzle with a multi-nozzle has been used to reduce combustion vibration caused by swirling flow in a gas turbine combustor equipped with a swirler. This replaces the use of one fuel nozzle with a swirler of the same structure to the use of multiple fuel nozzles with a swirler, which changes the flow of combustion gas near the fuel nozzle, and also allows the interference of combustion vibrations generated from multiple locations. This aims to reduce vibration.
（ＥＰＲＩ−ＡＰ３８８５ （１９８５−５） Ｉｌｉ
ｇｈ−ＲｅｌｉａｂｉｌｉｔｙＧａｓ Ｔｕｒｂｉｎｅ
Ｃｏｍｂｕｓｔｏｒ Ｐｒｏｊｅｃｔ）〔発明が解決
しようとする課題〕
上記の従来技術では、その実用化に莫大な開発費用と多
大の時間が必要であり、問題があった。(EPRI-AP3885 (1985-5) Ili
gh-Reliability Gas Turbine
Combustor Project) [Problems to be Solved by the Invention] The above-mentioned conventional technology has a problem in that it requires a huge amount of development cost and a lot of time to put it into practical use.
本発明の目的は、簡単で効果的に燃焼振動を低減するガ
スタービン燃焼器を提供することにある。An object of the present invention is to provide a gas turbine combustor that simply and effectively reduces combustion oscillations.
燃焼器の燃料ノズル近傍での器壁面を滑らかな面から粗
い面に代えることにより、上記の目的は達威される。The above objective is achieved by replacing the smooth surface of the combustor wall near the fuel nozzle with a rough surface.
燃焼器の燃料ノズル近傍での器壁面が粗いとき、そこで
の旋回流によっても、燃焼器周方向に沿った渦層ができ
難くなり、このような渦層が燃焼器壁と相互作用をする
条件がなくなる。これによって、燃焼振動が発生しなく
なる。When the combustor wall surface near the fuel nozzle of the combustor is rough, the swirling flow there makes it difficult to form a vortex layer along the circumferential direction of the combustor, and there are conditions for such a vortex layer to interact with the combustor wall. disappears. This prevents combustion vibration from occurring.
本発明の一実施例を第１図に示す。 An embodiment of the present invention is shown in FIG.
ガスタービン燃焼器１の上流端に、燃料ノズル３とこれ
を取り巻くように旋回８′＃２が設けてある。At the upstream end of the gas turbine combustor 1, a fuel nozzle 3 and a swirl 8'#2 are provided to surround the fuel nozzle 3.
燃焼器↓の燃料ノズル３の近傍での器壁面４には、二方
向に交叉した格子状の溝、すなわち、やすり状面５が施
され、粗面を形威している。The combustor wall surface 4 in the vicinity of the fuel nozzle 3 of the combustor ↓ is provided with lattice-like grooves that intersect in two directions, that is, a file-like surface 5, giving the appearance of a rough surface.
ところで、旋回流に基づく燃焼振動が発生するとき、そ
の発生原因は、燃料ノズル３の近傍での器壁面４が滑ら
かなため，そこに旋回流によって生じる渦層にあり、こ
の渦層が燃焼器壁となる弾性体と相互作用して生じる自
励振動にある。By the way, when combustion oscillations occur due to swirling flow, the cause of the occurrence is a vortex layer generated there by the swirling flow because the vessel wall surface 4 near the fuel nozzle 3 is smooth. This is due to self-excited vibrations that occur due to interaction with the elastic body that forms the wall.
ここに、器壁面４をやすり状面５にすると、そこの表面
摩擦が増加して、旋回流によっても渦層が形成されなく
なる。これによって、燃焼器壁となる弾性体と相互作用
するものがなくなり、燃焼振動が発生しなくなる。If the vessel wall surface 4 is made into a file-like surface 5, the surface friction there will increase and no vortex layer will be formed even by the swirling flow. This eliminates anything that interacts with the elastic body that forms the combustor wall, and combustion vibrations no longer occur.
なお、このようなやすり状面５を作るに当っては、器壁
面４の冷却面、強度面からの考慮が必要である。その点
からやすり状面５は燃焼器１に直接設ける代りに、別の
板を用意しておき、これにやすり面５設けて、これを器
壁面４に裏貼りすることがよいと考えられる。When creating such a file-like surface 5, consideration must be given to the cooling and strength aspects of the vessel wall surface 4. From this point of view, instead of providing the file-like surface 5 directly on the combustor 1, it is thought to be better to prepare another plate, provide the file-like surface 5 on this, and attach it to the back of the vessel wall surface 4.
本実施例によれば，燃焼器の冷却性能や燃焼性態に大き
い影響を与えることなく、旋回流に起因する燃焼振動の
低減を図る効果が得られる。また、本実施例によれば、
従来のガスタービン燃焼器の極く僅かな設計変更ですむ
、簡単な構造が得られる。According to this embodiment, the effect of reducing combustion vibration caused by swirling flow can be obtained without significantly affecting the cooling performance or combustion properties of the combustor. Furthermore, according to this embodiment,
A simple structure is obtained requiring only minimal design changes to conventional gas turbine combustors.
本発明によれば、燃焼器の燃料ノズル近傍での器壁面で
、旋回流による渦層が、表面摩擦によって生じないため
、燃焼振動が発生しない。According to the present invention, a vortex layer due to swirling flow is not generated on the wall surface of the combustor in the vicinity of the fuel nozzle due to surface friction, so that combustion vibration does not occur.
第１図は本発明の一実施例のガスタービン燃焼器部分の
断面図である。
１・・・燃焼器、２・・・旋回器、３・・・燃料ノズル
、４３
＝４−FIG. 1 is a sectional view of a gas turbine combustor portion according to an embodiment of the present invention. 1... Combustor, 2... Swirl device, 3... Fuel nozzle, 43 = 4-
Claims (1)
ノズルの近傍で燃焼ガスが通過する器壁面を粗面にした
ことを特徴とするガスタービン燃焼器。 ２、特許請求の範囲第１項において、 器壁面に二方向に交叉した格子状の溝を設けて粗面を作
つたことを特徴とするガスタービン燃焼器。[Scope of Claims] 1. A gas turbine combustor equipped with a swirler, characterized in that a wall surface through which combustion gas passes near a fuel nozzle is roughened. 2. A gas turbine combustor according to claim 1, characterized in that a lattice-shaped groove intersecting in two directions is provided on the vessel wall surface to create a rough surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17902088A JPH0315502A (en) | 1988-07-20 | 1988-07-20 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17902088A JPH0315502A (en) | 1988-07-20 | 1988-07-20 | Gas turbine combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0315502A true JPH0315502A (en) | 1991-01-23 |
Family
ID=16058707
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17902088A Pending JPH0315502A (en) | 1988-07-20 | 1988-07-20 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0315502A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6126595A (en) * | 1995-05-12 | 2000-10-03 | Seiko Epson Corporation | Device for diagnosing physiological state and device for controlling the same |
| DE10159668A1 (en) * | 2001-12-05 | 2003-06-18 | Rolls Royce Deutschland | Combustion chamber head has at least one turbulence-creating element on flow surface of cover |
-
1988
- 1988-07-20 JP JP17902088A patent/JPH0315502A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6126595A (en) * | 1995-05-12 | 2000-10-03 | Seiko Epson Corporation | Device for diagnosing physiological state and device for controlling the same |
| US6890304B1 (en) | 1995-05-12 | 2005-05-10 | Seiko Epson Corporation | Device for diagnosing physiological state and device for controlling the same |
| DE10159668A1 (en) * | 2001-12-05 | 2003-06-18 | Rolls Royce Deutschland | Combustion chamber head has at least one turbulence-creating element on flow surface of cover |
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