JPH0137575B2 - - Google Patents
Info
- Publication number
- JPH0137575B2 JPH0137575B2 JP58032707A JP3270783A JPH0137575B2 JP H0137575 B2 JPH0137575 B2 JP H0137575B2 JP 58032707 A JP58032707 A JP 58032707A JP 3270783 A JP3270783 A JP 3270783A JP H0137575 B2 JPH0137575 B2 JP H0137575B2
- Authority
- JP
- Japan
- Prior art keywords
- combustor
- cooling air
- turbine
- transition piece
- gas
- 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
- 238000001816 cooling Methods 0.000 claims description 48
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 24
- 230000007704 transition Effects 0.000 claims description 22
- 239000007921 spray Substances 0.000 claims description 11
- 238000000638 solvent extraction Methods 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 24
- 239000000567 combustion gas Substances 0.000 description 5
- 238000005507 spraying Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000009423 ventilation Methods 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
Description
【発明の詳細な説明】
本発明はガスタービンに関する。更に詳しくは
冷却用空気中に水を噴霧することに起因する燃焼
器尾筒の損傷を防止することに関するものであ
る。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to gas turbines. More particularly, the present invention relates to preventing damage to the combustor transition piece caused by spraying water into the cooling air.
近年、ガスタービンは、その性能向上および出
力上昇のため、使用ガス温度がますます高温化の
傾向にある。 In recent years, in order to improve the performance and output of gas turbines, the gas temperature used in gas turbines has tended to become higher and higher.
しかしながら、ガスタービンのタービン翼は、
その強度を保持するために一定の温度以下に保つ
必要があり、この手段としてタービン翼を冷却す
る方法が採用されている。 However, the turbine blades of a gas turbine are
In order to maintain its strength, it is necessary to maintain the temperature below a certain level, and a method of cooling the turbine blades is used as a means for this purpose.
そこで、タービン翼の冷却は、圧縮機で圧縮し
た空気の一部を冷却空気として翼内に導き、フイ
ルムを冷却、インピンジ冷却及び対流冷却等を行
なつているが、ここで冷却空気の使用量は、翼を
一定の温度以下に保つため、使用ガス温度の高温
化にともなつて増加する必要がある。 Therefore, to cool the turbine blades, a part of the air compressed by the compressor is guided into the blades as cooling air to perform film cooling, impingement cooling, convection cooling, etc., but the amount of cooling air used is In order to keep the blade below a certain temperature, it is necessary to increase as the gas temperature increases.
しかしながら、冷却空気使用量の増加は、冷却
空気圧縮のための所要動力の増加および主流ガス
に混合する冷却空気量の増加に伴う平均ガス温度
の低下によるガスタービンサイクル効率の低下に
つながるという問題がある。 However, an increase in the amount of cooling air used leads to a decrease in gas turbine cycle efficiency due to an increase in the power required for compressing the cooling air and a decrease in the average gas temperature due to the increase in the amount of cooling air mixed with the mainstream gas. be.
また、冷却空気は、そのタービンにより駆動さ
れる圧縮機で圧縮した空気を用いるため、燃焼ガ
スに比しては温度が低いものの、ガスタービンの
高出力化にともなつて、圧縮機での圧縮比が高く
なり、その温度も高くなつている。 In addition, since the cooling air uses air compressed by the compressor driven by the turbine, its temperature is lower than that of combustion gas, but as the output of gas turbines increases, the compressor As the ratio increases, so does the temperature.
従つて、タービン翼を冷却する際に、冷却空気
と主流ガスとの温度差は、その分小さくなり、冷
却効果は悪くなる。 Therefore, when cooling the turbine blades, the temperature difference between the cooling air and the mainstream gas becomes correspondingly smaller, and the cooling effect becomes worse.
また、冷却空気はさらにタービン翼に導く途中
において、周囲の高温の雰囲気にさらされるた
め、温度が上昇するが、この傾向は燃焼ガス温度
が高くなる程大きい。 In addition, the cooling air is further exposed to the surrounding high-temperature atmosphere on the way to the turbine blades, so its temperature increases, and this tendency increases as the combustion gas temperature increases.
従つて圧縮機で圧縮された空気をそのまま冷却
空気として用いる場合、タービン翼の温度を、そ
の強度を保持するに必要な一定の温度以下に保つ
条件の下では、冷却空気量を増加しても主流ガス
温度をある値以上に上げることは不可能である。 Therefore, if the air compressed by the compressor is used as cooling air, even if the amount of cooling air is increased, as long as the temperature of the turbine blade is kept below a certain level necessary to maintain its strength. It is impossible to raise the mainstream gas temperature above a certain value.
この対策として、冷却空気をいつたんガスター
ビン外に導き、エアフインクーラ等を用いて冷却
したものもあるが、この場合、冷却空気温度は低
下するものの、構造が複雑となり、また圧損が増
大し、冷却空気の圧力とタービン入口のガス圧力
との差が小さくなり、このため初段静翼のフイル
ム冷却が不可能であるという問題がある。 As a countermeasure to this problem, there is a method in which the cooling air is guided outside the gas turbine and cooled using an air-fin cooler, etc., but in this case, although the cooling air temperature is lowered, the structure is complicated and the pressure drop increases. There is a problem in that the difference between the pressure of the cooling air and the gas pressure at the turbine inlet becomes small, making it impossible to film-cool the first-stage stationary blades.
一方、タービン翼冷却用の空気中に水を噴霧す
ることによつて冷却効果を向上らせることが知ら
れているが、この場合、冷却空気室内の空気が水
噴霧装置によつて噴霧された水を速やかに蒸発さ
せるに十分な温度でない時に噴霧を行つたり、或
いは水が水滴状態でしたたり落ちたりした場合、
高温になつたタービン構成部材に水滴が直接当た
り、この部分を急冷することになる。前記タービ
ン構成部材、特に燃焼器尾筒は比較的薄い板で構
成されているばかりでなく、直接、燃焼ガスに触
れるため、僅かな水滴が当たつても水滴の接触個
所が急冷され、クラツク発生の原因になる。 On the other hand, it is known that the cooling effect can be improved by spraying water into the air for cooling the turbine blades, but in this case, the air in the cooling air chamber is sprayed by a water spray device. If you spray at a time when the temperature is not high enough to evaporate the water quickly, or if the water drips down,
The water droplets directly hit the hot turbine components, rapidly cooling those parts. The turbine components, especially the combustor transition piece, are not only made of relatively thin plates, but also come into direct contact with the combustion gas, so even if a small drop of water hits, the point of contact with the water droplets will be rapidly cooled, causing a crack. It causes
そこで、本発明の目的は、燃焼器の尾筒に直接
水滴が当たることを防止し、もつて燃焼器尾筒の
損傷を未然に防止することにある。 Therefore, an object of the present invention is to prevent water droplets from directly hitting the transition piece of the combustor, thereby preventing damage to the transition piece of the combustor.
即ち、本発明は、燃焼器支持板によつてガスタ
ービンの燃焼器室内を、燃焼器本体側と燃焼器尾
筒側とに仕切ることにより燃焼器尾筒側に冷却空
気室を形成すると共に、該冷却空気室に水噴霧装
置を配設し、かつ前記燃焼器尾筒の外側に当該燃
焼器尾筒を覆うための保護筒を配設したことを特
徴とするものである。 That is, the present invention forms a cooling air chamber on the combustor transition pipe side by partitioning the combustor chamber of the gas turbine into the combustor main body side and the combustor transition pipe side using a combustor support plate, and The present invention is characterized in that a water spray device is disposed in the cooling air chamber, and a protection tube for covering the combustor transition piece is disposed outside the combustor transition piece.
以下、図面を参照して本発明のガスタービンの
実施例を説明するが、第１図は本発明の実施例に
おけるガスタービンの概略系統図であり、図中圧
縮機２、燃焼器３、タービン４等によりこのガス
タービン１は構成されている。 Embodiments of the gas turbine according to the present invention will be described below with reference to the drawings. FIG. This gas turbine 1 is composed of 4 and the like.
次に、第２図は上記ガスタービン１の要部側断
面図であり、図中冷却空気は矢印Ａのごとく流
れ、また第２図の燃焼器室９は燃焼器中間支持板
１２が、第３図の要部正面図に示すごとく、それ
ぞれの両側が隣りの燃焼器中間支持板１２と接す
るようになつており、燃焼器内筒１０及び燃焼器
フローガイド１１を有する燃焼器本体３１側と、
燃焼器尾頭１３側とに仕切つており、燃焼器尾筒
１３側に冷却空気室３０を形成している。 Next, FIG. 2 is a side sectional view of the main part of the gas turbine 1, in which cooling air flows as indicated by arrow A, and the combustor chamber 9 in FIG. As shown in the main part front view of FIG. 3, each side is in contact with the adjacent combustor intermediate support plate 12, and the combustor main body 31 side, which has the combustor inner cylinder 10 and the combustor flow guide 11, ,
A cooling air chamber 30 is formed on the combustor tailpiece 13 side.
また、上記燃焼器尾筒１３の外周側は保護筒４
７により大部分をおおわれている。 Further, the outer peripheral side of the combustor transition pipe 13 is provided with a protection pipe 4.
Most of the area is covered by 7.
なお、燃焼器中間支持板１２は燃焼器室９を完
全に仕切つているのではなく、第３図に示すよう
に、その外周部等の一部には開口部２９を設けて
いる。 Note that the combustor intermediate support plate 12 does not completely partition the combustor chamber 9, but has an opening 29 in a part of its outer periphery, etc., as shown in FIG.
次に、冷却空気室３０には、水を噴霧する噴霧
装置５を設けてあり、噴霧装置５はガスタービン
１外部の水の供給源８に配管６で接続されてお
り、この途中には噴霧を停止する弁７が設けてあ
る。 Next, the cooling air chamber 30 is provided with a spray device 5 that sprays water, and the spray device 5 is connected to a water supply source 8 outside the gas turbine 1 through a pipe 6, and a pipe 6 is connected to the water supply source 8 outside the gas turbine 1. A valve 7 is provided to stop the operation.
また、燃焼器尾筒１３は内板１４と外板１５と
の二重構造とし、双方に多数の小孔１７，１８を
穿設し、その中間にスペーサ１６を設けて間隙を
保つ構造になつている。 In addition, the combustor transition piece 13 has a double structure consisting of an inner plate 14 and an outer plate 15, and a large number of small holes 17 and 18 are bored in both, and a spacer 16 is provided in the middle to maintain a gap. ing.
また、連結部材２０と、トルクチユーブ２１と
の間に、圧縮機高圧側シールリング２２とタービ
ン入口側シールリング２３とでシールされた空間
２６を設け、冷却空気抽気孔２４および２５によ
つて冷却空気室３０とトルクチユーブ２１内の空
間２７とを連通している。 Further, a space 26 sealed by a compressor high pressure side seal ring 22 and a turbine inlet side seal ring 23 is provided between the connecting member 20 and the torque tube 21, and is cooled by cooling air bleed holes 24 and 25. The air chamber 30 and the space 27 within the torque tube 21 are communicated with each other.
そこで、圧縮機２で圧縮された空気は、燃焼器
室９に入り、大部分は燃焼機本体３１に供給され
るが、一部は燃焼器中間支持板１２の開口部２９
を通り、冷却空気室３０に入り、ここで噴霧装置
５より水を噴霧して冷却される。 Therefore, the air compressed by the compressor 2 enters the combustor chamber 9, and most of it is supplied to the combustor main body 31, but some of it is supplied to the opening 29 of the combustor intermediate support plate 12.
It enters the cooling air chamber 30, where it is cooled by spraying water from the spray device 5.
冷却空気室３０で冷却された冷却空気Ａの一部
は、タービン翼環３２の冷却空気孔３３，３３を
通つてタービン静翼３４，３６に供給される。 A part of the cooling air A cooled in the cooling air chamber 30 is supplied to the turbine stationary blades 34 and 36 through the cooling air holes 33 and 33 of the turbine blade ring 32.
また、一部は燃焼器尾筒１３の外板１５の小孔
１７から空間部３８に入り、内板１４の小孔１８
から主流に吹き出す。 In addition, a portion enters the space 38 from the small hole 17 in the outer plate 15 of the combustor transition piece 13, and enters the small hole 18 in the inner plate 14.
It bursts out into the mainstream.
さらに一部は連結部材２０の冷却空気抽気孔２
４から空間２６に入り、トルクチユーブ２１の冷
却空気抽気孔２５からトルクチユーブ２１内の空
間２７に入り、タービンデイスク３９の通気孔４
２、またスペーサデイスク４１の通気孔４３より
タービンデイスク３９，４０間の空間４４，４４
に入り、冷却空気孔４５，４５および４６，４６
を通つてタービン動翼３５，３７に供給される。 Further, a part of the cooling air bleed hole 2 of the connecting member 20
4, enters the space 26 from the cooling air bleed hole 25 of the torque tube 21, enters the space 27 in the torque tube 21, and enters the space 27 in the torque tube 21 from the cooling air bleed hole 25 of the torque tube 21, and enters the space 27 from the cooling air bleed hole 25 of the torque tube 21.
2. Also, the space 44, 44 between the turbine disks 39, 40 is opened from the ventilation hole 43 of the spacer disk 41.
cooling air holes 45, 45 and 46, 46
It is supplied to the turbine rotor blades 35, 37 through.
ここで、冷却空気室３０内の空気が水噴霧装置
５により噴霧された水を速やかに蒸発させるに十
分な温度でない時噴霧を行なつたり、水が水滴状
態でしたたり落ちたりした場合、高温となつたタ
ービン構成部材に水滴が直接当たり、この部分を
急冷することになる。 Here, if spraying is performed when the air in the cooling air chamber 30 is not at a temperature sufficient to quickly evaporate the water sprayed by the water spray device 5, or if the water drips down in the form of water droplets, high temperatures may occur. Water droplets directly hit the deteriorated turbine components, rapidly cooling these parts.
冷却空気室のタービン構成部材で特に燃焼器尾
筒１３は、直接燃焼ガスにふれるため、温度が高
く、比較的うす板で構成されているため、僅かな
水滴が当つても、この部分が急冷され、クラツク
発生の原因となる。 Among the turbine components in the cooling air chamber, the combustor transition piece 13 in particular has a high temperature because it comes into direct contact with the combustion gas, and is made of relatively thin plates, so even if a small drop of water hits this part, it will cool down rapidly. This may cause cracks to occur.
しかも、燃焼器尾筒１３にクラツクが発生すれ
ば、燃焼ガスが洩れることになる。 Furthermore, if a crack occurs in the combustor transition piece 13, combustion gas will leak.
そこで、特に本発明では、燃焼器尾筒１３に保
護筒４７を設け、燃焼器尾筒１３に直接水滴が当
たるのを防止している。 Therefore, particularly in the present invention, a protection tube 47 is provided on the combustor transition piece 13 to prevent water droplets from directly hitting the combustor transition piece 13.
上記のように、本発明は、ガスタービンの燃焼
器室内を、燃焼器支持板によつて燃焼器大体側と
燃焼器尾筒側とに仕切ることにより前記燃焼器尾
筒側に冷却空気室を形成し、該冷却空気室に水噴
霧装置を配設し、かつ前記燃焼器尾筒の外側に当
該燃焼器尾筒を覆うための保護筒を配設したの
で、燃焼器の尾筒に直接水滴が当たらなくなり、
もつて燃焼器尾筒の損傷を未然に防止することが
できるようになる。 As described above, the present invention provides a cooling air chamber on the combustor tail piece side by partitioning the combustor chamber of a gas turbine into the combustor main side and the combustor tail piece side by a combustor support plate. A water spray device is provided in the cooling air chamber, and a protective tube is provided outside the combustor transition piece to cover the combustor transition piece, so that water droplets are not directly applied to the combustor transition piece. is no longer hit,
This makes it possible to prevent damage to the combustor transition piece.
第１図は本発明のガスタービンの一実施例にお
ける概略系統図、第２図は第１図のガスタービン
の要部側断面図、第３図は第２図の燃焼器中間支
持板の要部正面図である。
１……ガスタービン、２……圧縮機、３……燃
焼器、４……タービン、５……噴霧装置、９……
燃焼器室、１２……燃焼器中間支持板、１３……
燃焼器尾筒、３０……冷却空気室、３１……燃焼
器室本体、３４，３６……タービン静翼、３５，
３７……タービン動翼、４７……保護筒、Ａ……
冷却空気。
FIG. 1 is a schematic system diagram of an embodiment of the gas turbine of the present invention, FIG. 2 is a sectional side view of the main part of the gas turbine shown in FIG. 1, and FIG. 3 is a main part of the combustor intermediate support plate shown in FIG. 2. FIG. 1...Gas turbine, 2...Compressor, 3...Combustor, 4...Turbine, 5...Spray device, 9...
Combustor chamber, 12... Combustor intermediate support plate, 13...
Combustor transition piece, 30...Cooling air chamber, 31...Combustor chamber main body, 34, 36...Turbine stationary blade, 35,
37...Turbine rotor blade, 47...Protection tube, A...
cooling air.
Claims (1)
によつて燃焼器本体側と燃焼器尾筒側とに仕切る
ことにより前記燃焼器尾筒側に冷却空気室を形成
し、該冷却空気室に水噴霧装置を配設し、かつ前
記燃焼器尾筒の外側に当該燃焼器尾筒を覆うため
の保護筒を配設したことを特徴とするガスタービ
ン。1. A cooling air chamber is formed on the combustor tailpiece side by partitioning the combustor chamber of the gas turbine into a combustor main body side and a combustor tailpiece side using a combustor support plate, and a cooling air chamber is formed on the combustor tailpiece side. A gas turbine characterized in that a water spray device is disposed, and a protection tube for covering the combustor transition piece is disposed outside the combustor transition piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3270783A JPS59160034A (en) | 1983-03-01 | 1983-03-01 | Gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3270783A JPS59160034A (en) | 1983-03-01 | 1983-03-01 | Gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS59160034A JPS59160034A (en) | 1984-09-10 |
| JPH0137575B2 true JPH0137575B2 (en) | 1989-08-08 |
Family
ID=12366309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3270783A Granted JPS59160034A (en) | 1983-03-01 | 1983-03-01 | Gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59160034A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1283338B1 (en) * | 2001-08-09 | 2005-03-30 | Siemens Aktiengesellschaft | Gas turbine and method for operating a gas turbine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4965406A (en) * | 1972-10-30 | 1974-06-25 | ||
| JPS5477820A (en) * | 1977-12-02 | 1979-06-21 | Hitachi Ltd | Method of cooling gas turbine blade |
-
1983
- 1983-03-01 JP JP3270783A patent/JPS59160034A/en active Granted
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4965406A (en) * | 1972-10-30 | 1974-06-25 | ||
| JPS5477820A (en) * | 1977-12-02 | 1979-06-21 | Hitachi Ltd | Method of cooling gas turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS59160034A (en) | 1984-09-10 |
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