JPH02183721A - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- JPH02183721A JPH02183721A JP89346A JP34689A JPH02183721A JP H02183721 A JPH02183721 A JP H02183721A JP 89346 A JP89346 A JP 89346A JP 34689 A JP34689 A JP 34689A JP H02183721 A JPH02183721 A JP H02183721A
- Authority
- JP
- Japan
- Prior art keywords
- inner cylinder
- air
- flow
- combustion gas
- cylinder
- 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
- 239000000567 combustion gas Substances 0.000 claims abstract description 15
- 239000000446 fuel Substances 0.000 claims abstract description 6
- 239000007789 gas Substances 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 6
- 239000010419 fine particle Substances 0.000 claims description 5
- 238000007750 plasma spraying Methods 0.000 claims description 4
- 238000001816 cooling Methods 0.000 abstract description 20
- 230000000694 effects Effects 0.000 abstract description 8
- 230000008646 thermal stress Effects 0.000 abstract description 5
- 239000004020 conductor Substances 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 239000002245 particle Substances 0.000 abstract 1
- 238000000034 method Methods 0.000 description 3
- 238000005524 ceramic coating Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000011859 microparticle Substances 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000002470 thermal conductor Substances 0.000 description 1
- 238000007751 thermal spraying Methods 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Landscapes
- Air Supply (AREA)
Abstract
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燃焼器に係り、特に、冷却手段を
改良した高温燃焼器に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a gas turbine combustor, and more particularly to a high temperature combustor with improved cooling means.
従来のガスタービン燃焼器の内筒の冷却構造は、特公昭
５７−５７６８７号公報に記載のように、燃焼ガス側表
面に低温の空気層を形成して燃焼ガスからの入熱を抑制
し、空気側の表面は衝突冷却によって放熱を促進する構
造となっている。その構造を第４図を用いて説明する。As described in Japanese Patent Publication No. 57-57687, a conventional cooling structure for the inner cylinder of a gas turbine combustor suppresses heat input from the combustion gas by forming a low-temperature air layer on the combustion gas side surface. The air-side surface has a structure that promotes heat dissipation through impingement cooling. Its structure will be explained using FIG.
燃焼ガス側表面に低温の空気層を形成するためのリップ
９を設け、内筒本体１に設けた小孔１０を通して、内筒
本体１とリップ９によって形成される冷却空気通路１４
に冷却空気を供給し、この冷却空気を内筒本体１のガス
側表面に沿って流し、高温の燃焼ガスが直接。A cooling air passage 14 formed by the inner cylinder body 1 and the lip 9 is provided with a lip 9 for forming a low-temperature air layer on the combustion gas side surface, and passes through a small hole 10 provided in the inner cylinder body 1.
This cooling air is flowed along the gas side surface of the inner cylinder main body 1, and the high temperature combustion gas is directly supplied to the cylinder.
壁面に接しないようにして入熱を抑制している。Heat input is suppressed by avoiding contact with walls.
また、ガスから放射伝熱によって伝わった熱を放熱する
作用もある。一方、内筒本体１の外側では入熱量の大部
分を放熱している。この放熱性能を高めるために、内筒
本体１の外周にカバー壁１２を設け、カバー壁の小孔１
３から流入する空気を内筒本体１に衝突させている。衝
突した空気は内筒本体１の小孔１０を通して、再度、冷
却空気として使用される。内筒本体１とカバー壁１２と
は接続部材１５によって接続されている。It also has the effect of radiating heat transferred from the gas by radiant heat transfer. On the other hand, most of the heat input is radiated outside the inner cylinder main body 1. In order to improve this heat dissipation performance, a cover wall 12 is provided on the outer periphery of the inner cylinder body 1, and small holes 1 in the cover wall are provided.
Air flowing in from 3 is made to collide with the inner cylinder body 1. The collided air passes through the small holes 10 of the inner cylinder main body 1 and is used again as cooling air. The inner cylinder main body 1 and the cover wall 12 are connected by a connecting member 15.
上記従来技術は温度の高い内筒本体１と温度の低いカバ
ー壁１２とを接続部材１５で接続していることにより、
熱膨張差による熱応力が発生して製品寿命が短くなるこ
と、外筒４とカバー壁１２の間を流れる空気の対流冷却
を利用できないことにより、小孔１３から流入する空気
流速を高めて衝突冷却することになり、圧力損失が大き
くなるという問題があった。The above-mentioned conventional technology connects the inner cylinder main body 1, which has a high temperature, and the cover wall 12, which has a low temperature, by a connecting member 15.
The product life is shortened due to thermal stress due to the difference in thermal expansion, and convection cooling of the air flowing between the outer cylinder 4 and the cover wall 12 cannot be used, so the air flow velocity flowing in from the small holes 13 is increased and collisions occur. There was a problem in that the pressure loss would increase due to cooling.
本発明の目的は熱応力の発生を防止して冷却性能の高い
構造を提供することにある。An object of the present invention is to provide a structure with high cooling performance by preventing the occurrence of thermal stress.
上記目的を達成するために良熱伝導物質の微小粒子を内
筒空気側表面に固着して粗面化したものである。In order to achieve the above object, fine particles of a good heat conductive material are fixed to the air-side surface of the inner cylinder to make the surface rough.
さらに、微小粒子を固着するために溶射法を用いたもの
である。Furthermore, a thermal spraying method is used to fix the fine particles.
内筒空気側表面に固着した微小粒子は金属の表面積を増
す。一方、金属表面凹凸高さが小さい場合には近傍流れ
の減速割合が小さい。従って、近傍流れの減速による熱
伝達率の減少よりも表面積増加による効果の方が大きく
なって熱伝達率が大きくなる。また、内筒本体を他の温
度の異なる部材と接合していないので、熱応力は内筒本
体の温度分布によって発生する値だけとなり、低く抑え
ることができる。The microparticles that adhere to the air-side surface of the inner cylinder increase the surface area of the metal. On the other hand, when the height of the metal surface unevenness is small, the deceleration rate of the nearby flow is small. Therefore, the effect of increasing the surface area is greater than the decrease in heat transfer coefficient due to the deceleration of the nearby flow, and the heat transfer coefficient increases. Further, since the inner cylinder main body is not joined to other members having different temperatures, the thermal stress is only a value generated by the temperature distribution of the inner cylinder main body, and can be suppressed to a low level.
以下、本発明の一実施例を第１図により説明する。ガス
タービンでは図示しない圧縮機によって加圧された空気
が圧縮機デイフユーザ６を通って燃焼器部に供給され、
尾筒２の周囲を流れた空気は案内筒５と内筒本体１との
間を流れ、内筒本体１に設けた図示しない空気孔を通っ
て内筒本体１の内部へはいる。内筒内部では燃料ノズル
３から供給される燃料が空気と混合して燃焼し、高温の
燃焼ガスを生成する。この燃焼ガスは尾筒２の内側を通
って図示しないタービンに導かれ、膨張した後に排出さ
れる。An embodiment of the present invention will be described below with reference to FIG. In the gas turbine, air pressurized by a compressor (not shown) is supplied to a combustor section through a compressor differential user 6,
The air that has flowed around the transition piece 2 flows between the guide tube 5 and the inner cylinder main body 1, and enters the inside of the inner cylinder main body 1 through an air hole (not shown) provided in the inner cylinder main body 1. Inside the inner cylinder, fuel supplied from the fuel nozzle 3 mixes with air and burns, producing high-temperature combustion gas. This combustion gas passes through the inside of the transition piece 2, is guided to a turbine (not shown), and is discharged after being expanded.
内筒本体１．及び、尾筒２は内側を高温の燃焼ガスが流
れるために加熱されるが、その外周を流れる空気を用い
て冷却しており、本発明の冷却促進体を内筒本体１に固
着した状態が粗表面体７であり、尾筒２に固着した状態
が粗表面体８である。Inner cylinder body 1. The transition piece 2 is heated because high-temperature combustion gas flows inside, but it is cooled using air flowing around its outer periphery. The rough surface body 7 is the rough surface body 7, and the rough surface body 8 is the rough surface body 8 that is fixed to the transition piece 2.
内筒本体１の具体的な構造を第２図により説明する。内
筒本体１の燃焼ガス側表面に冷却空気をフィルム状に流
すためにリップ９を設け、小孔１０から流入する空気を
壁面に沿って流し、高温燃焼ガスが壁面と、直接、接し
ないようにするとともに、放射伝熱によって加熱された
壁面と空気との温度差によって対流冷却も行なっている
。内筒本体１の外側は案内筒５との間を内筒に供給され
る空気が全量流れており、内筒に供給される冷却空気が
流れる小孔１０の近傍を除く表面に良熱伝導体の微小粒
子を固着して粗表面体７を形成している。The specific structure of the inner cylinder main body 1 will be explained with reference to FIG. A lip 9 is provided on the combustion gas side surface of the inner cylinder body 1 to allow cooling air to flow in a film form, and the air flowing in from the small holes 10 is flowed along the wall surface so that the high temperature combustion gas does not come into direct contact with the wall surface. At the same time, convection cooling is also performed by the temperature difference between the wall surface heated by radiation heat transfer and the air. The entire amount of air supplied to the inner cylinder flows between the outer side of the inner cylinder main body 1 and the guide cylinder 5, and a good thermal conductor is formed on the surface except for the vicinity of the small hole 10 through which cooling air supplied to the inner cylinder flows. The rough surface body 7 is formed by fixing the fine particles.
粗表面体７は従来から燃焼ガス側の遮熱に用いられてい
るセラミックコーティングと同程度で熱伝達が促進され
るので、２０μｍ以上が良い。材質は熱伝導率が大きく
、線膨張係数が内筒金属に近いものが望ましいため、従
来のセラミックスコーティングの金属側に用いられるＭ
ＣｒＡＱＹ合金、又は、内筒と同−金属を用いる。微小
粒子を固着する方法はプラズマ溶射である。従って、内
筒形状にかかわらず、成形が完了した後に施行が可能で
ある。Since the rough surface body 7 promotes heat transfer to the same extent as a ceramic coating conventionally used for heat shielding on the combustion gas side, the rough surface body 7 preferably has a thickness of 20 μm or more. It is desirable that the material has a high thermal conductivity and a coefficient of linear expansion close to that of the inner cylinder metal, so M is used on the metal side of conventional ceramic coatings.
Use CrAQY alloy or the same metal as the inner cylinder. Plasma spraying is a method for fixing microparticles. Therefore, regardless of the shape of the inner cylinder, the process can be performed after molding is completed.
他の実施例を第３図により説明する。内筒本体１の内部
に冷却空気通路１６を設けた構造においても、空気流路
側表面に粗表面体７を固着することが可能であり、冷却
空気通路１６の内部での冷却効果と空気流路側表面での
冷却効果のなかの後者の効果を高めることができる。Another embodiment will be explained with reference to FIG. Even in a structure in which the cooling air passage 16 is provided inside the inner cylinder main body 1, it is possible to fix the rough surface body 7 to the surface on the air passage side, thereby achieving a cooling effect inside the cooling air passage 16 and improving the air passage side. The latter of the cooling effects on the surface can be enhanced.
また、粗表面体７をプラズマ溶射によって固着するだけ
であり、内筒本体１と温度の異なる部材を接続すること
がないため熱応力を低減できる。Further, since the rough surface body 7 is simply fixed by plasma spraying, and there is no need to connect members having different temperatures from the inner cylinder main body 1, thermal stress can be reduced.
さらに、粗表面体７をプラズマ溶射によって固着するだ
けであるので、任意形状、任意材質への適用が可能であ
る。Furthermore, since the rough surface body 7 is simply fixed by plasma spraying, it can be applied to any shape and any material.
本発明によれば案内筒と内筒本体との間を流れる空気に
よる冷却効果を、粗表面体による熱伝達率向上により、
高めることができる。According to the present invention, the cooling effect of the air flowing between the guide cylinder and the inner cylinder body is improved by improving the heat transfer coefficient by the rough surface body.
can be increased.
第１図は本発明の一実施例の断面図、第２図は内筒本体
の部分断面図、第３図は本発明の他の実施例の断面図、
第４図は従来構造の部分断面図である。
猶FIG. 1 is a sectional view of one embodiment of the present invention, FIG. 2 is a partial sectional view of the inner cylinder main body, and FIG. 3 is a sectional view of another embodiment of the present invention.
FIG. 4 is a partial sectional view of a conventional structure. grace
Claims (1)
ら供給される空気と反応させて燃焼ガスを生成する内筒
と、前記燃焼ガスをタービンに導く尾筒から成るガスタ
ービン燃焼器において、前記内筒、前記尾筒の少なくと
も一方の空気側メタル表面に熱伝導率の大きい微小粒子
を固着したことを特徴とするガスタービン燃焼器。 ２、特許請求項第１項の前記微小粒子をプラズマ溶射に
よつて固着したことを特徴とするガスタービン燃焼器。[Claims] 1. Consisting of a fuel nozzle that supplies fuel, an inner cylinder that reacts the fuel with air supplied from a compressor to generate combustion gas, and a transition piece that guides the combustion gas to a turbine. A gas turbine combustor, characterized in that fine particles with high thermal conductivity are fixed to an air-side metal surface of at least one of the inner tube and the transition tube. 2. A gas turbine combustor characterized in that the fine particles according to claim 1 are fixed by plasma spraying.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP89346A JPH02183721A (en) | 1989-01-06 | 1989-01-06 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP89346A JPH02183721A (en) | 1989-01-06 | 1989-01-06 | Gas turbine combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH02183721A true JPH02183721A (en) | 1990-07-18 |
Family
ID=11471293
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP89346A Pending JPH02183721A (en) | 1989-01-06 | 1989-01-06 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH02183721A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0658527A (en) * | 1992-06-24 | 1994-03-01 | Niigata Eng Co Ltd | Cooling structure for burner |
| JP2010203439A (en) * | 2009-03-02 | 2010-09-16 | General Electric Co <Ge> | Effusion cooled one-piece can combustor |
| JP2010210229A (en) * | 2009-03-06 | 2010-09-24 | General Electric Co <Ge> | Injection device for turbomachine |
-
1989
- 1989-01-06 JP JP89346A patent/JPH02183721A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0658527A (en) * | 1992-06-24 | 1994-03-01 | Niigata Eng Co Ltd | Cooling structure for burner |
| JP2010203439A (en) * | 2009-03-02 | 2010-09-16 | General Electric Co <Ge> | Effusion cooled one-piece can combustor |
| JP2010210229A (en) * | 2009-03-06 | 2010-09-24 | General Electric Co <Ge> | Injection device for turbomachine |
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