JPS59160034A - Gas turbine - Google Patents
Gas turbineInfo
- Publication number
- JPS59160034A JPS59160034A JP3270783A JP3270783A JPS59160034A JP S59160034 A JPS59160034 A JP S59160034A JP 3270783 A JP3270783 A JP 3270783A JP 3270783 A JP3270783 A JP 3270783A JP S59160034 A JPS59160034 A JP S59160034A
- Authority
- JP
- Japan
- Prior art keywords
- combustor
- air
- cooling
- chamber
- cooling air
- 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.)
- Granted
Links
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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
気の一部を、噴霧装置からの噴霧氷により効果的に冷却
の上、冷却空気として使用しているガスタービンに関す
るものであるっ
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。DETAILED DESCRIPTION OF THE INVENTION This invention relates to a gas turbine that effectively cools a part of the air with sprayed ice from a spraying device and then uses it as cooling air.In recent years, the performance of gas turbines has improved. Due to the increase in power and output, the gas temperature used is becoming increasingly high.
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, in order to maintain the strength of the turbine blades of a gas turbine, it is necessary to maintain the temperature below a certain level, and a method of cooling the turbine blades is adopted 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、フィルム冷却、イン
ピンジ冷却及び対流冷却等を行なっているが、ここで冷
却空気の使用量は、翼を一定の温度以下に保つだめ、使
用ガス温度の高温化にともなっ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, and film cooling, impingement cooling, convection cooling, etc. are performed, but the amount of cooling air used here is In order to keep the blade below a certain temperature, it must 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って
、圧縮機での圧縮比が高くなり、その温度も高くなって
いる。In addition, since cooling air uses air compressed by a compressor driven by the turbine, its temperature is lower than that of combustion gas, but as the output of gas turbines increases, the compression ratio of the compressor increases. is rising, and its temperature is also rising.
従って、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ぐ°途中におい
て、周囲の高温の雰囲気にさらされるだめ、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。Furthermore, while the cooling air is being led to the turbine blades, it is exposed to the surrounding high-temperature atmosphere, so its temperature increases, and this tendency increases as the combustion gas temperature increases.
従っ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 directly as cooling air, even if the amount of cooling air is increased, it will not be used as long as the temperature of the turbine blades is kept below a certain level necessary to maintain its strength. It is not possible to increase the gas temperature above a certain value.
この対策として、冷却空気をいったんガスタービン外に
導き、エアフィ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
静翼のフィ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 once guided outside the gas turbine and cooled using an air fin cooler, etc., but in this case, although the cooling air temperature decreases, the structure becomes 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 film cooling of the first stage stationary blade impossible.
そこで、本発明は前記従来の問題点を解消し、ガスター
ビンの冷却空気をガスタービン内に設けた水の噴霧装置
により効果的に冷却することにより、ガスタービンのサ
イクル効率を向上させることを目的としたものである。SUMMARY OF THE INVENTION Therefore, an object of the present invention is to solve the above-mentioned conventional problems and to improve the cycle efficiency of a gas turbine by effectively cooling the cooling air of the gas turbine with a water spray device installed in the gas turbine. That is.
即ち、本発明は、ガスタービンの圧縮機で圧縮した空気
の一部を冷却空気としてそのタービン翼に導き、タービ
ン翼を冷却するガスタービンにおいて、該ガスタービン
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
と共に、燃焼器尾筒の外周側には保護筒を設け、その燃
焼器尾筒側に形成された冷却空気室内に、水を噴霧可能
な噴霧装置を設けることにより構成される。That is, the present invention provides a gas turbine in which a part of the air compressed by the compressor of the gas turbine is guided as cooling air to the turbine blades to cool the turbine blades. In addition to partitioning the combustor into a tail piece, a protective tube is provided on the outer circumferential side of the combustor tail piece, and a spray device capable of spraying water is installed in the cooling air chamber formed on the combustor tail piece side. configured.
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. 1 is a schematic system diagram of the gas turbine according to the embodiment of the present invention. 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と接するようになっており、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、燃焼器尾筒１３側とに仕切っており、燃焼器尾筒１
６側に冷却空気室６０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 inner cylinder
It is partitioned into a combustor main body 31 side having a combustor flow guide 11 and a combustor transition piece 13 side.
A cooling air chamber 60 is formed on the 6 side.
また、上記燃焼器尾筒１６の外周側は保護筒４ンにより
大部分をおおわれている。Further, the outer peripheral side of the combustor transition pipe 16 is mostly covered by a protection pipe 4.
なお、燃焼器中間支持板１２は燃焼器室９を完全に仕切
っているのではなく、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。
−
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が設けである。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.
- Next, the cooling air chamber 30 is provided with a spraying device 5 that sprays water, and the spraying device 5 is connected to a water supply source 8 outside the gas turbine 1 through a pipe 6. A valve 7 is provided to stop the spraying.
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ってい
る。In addition, the combustor transition piece 13 has a double structure consisting of an inner plate 14 and an outer plate 15, with a large number of small holes 17 and 18 bored in both, and a spacer 16 provided in the middle to maintain a gap. ing.
また、連結部材２０と、トルクチューブ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２６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によって冷却空気室６０とトルク
チューブ２１内の空間２７とを連通している。Moreover, between the connecting member 20 and the torque tube 21,
A space 26 sealed by a compressor high pressure side seal ring 22 and a turbine inlet side seal ring 26 is provided, and a cooling air chamber 60 and a space 27 inside the torque tube 21 are communicated through cooling air bleed holes 24 and 25. .
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
６０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 combustion/combustor chamber 9, and most of it is supplied to the combustion machine main body 31, but a part passes through the opening 29 of the combustor intermediate support plate 12 and is cooled. It enters the air chamber 60, where it is cooled by spraying water from the spray device 5.
冷却空気室６０で冷却された冷却空気Ａの一部は、ター
ビン翼環６２の冷却空気孔３３．３３を通ってタービン
静翼３４．６６に供給される。A part of the cooling air A cooled in the cooling air chamber 60 is supplied to the turbine stationary blade 34.66 through the cooling air hole 33.33 of the turbine blade ring 62.
また、一部は燃焼器尾筒１６の外板１５の小孔１７がら
空間部６８に入り、内板１４の小孔１８から主流に吹き
出す。A part of the gas also enters the space 68 through the small hole 17 in the outer plate 15 of the combustor transition piece 16 and is blown out from the small hole 18 in the inner plate 14 into the mainstream.
さらに一部は連結部材２０の冷却空気抽気孔２４から空
間２６に入り、トルクチューブ２１の冷却空気抽気孔２
５からトルクチューブ２１内の 空間２７に入り、ター
ビンディスク３９の通気孔４２、またスペーサディスク
４１の通気孔４６よりタービンディスク３９．４０間の
空間４４．４４に入り、冷却空気孔４５，４５および４
６．４６を通ってタービン動翼３５．３７に供給される
。Further, a portion enters the space 26 from the cooling air bleed hole 24 of the connecting member 20 and enters the space 26 from the cooling air bleed hole 24 of the torque tube 21.
5, enters the space 27 in the torque tube 21, enters the air hole 42 of the turbine disk 39, and enters the space 44, 44 between the turbine disks 39, 40 through the air hole 46 of the spacer disk 41, and enters the cooling air holes 45, 45 and 4
6.46 to the turbine rotor blades 35.37.
本発明のガスタービンは、以上のように構成されており
、圧縮機で圧縮され、温度が高くなり、また周囲の高温
の雰囲気にさらされて、さらに温度の高くなった空気中
に水を噴霧することにより、その空気を冷却することが
できる。The gas turbine of the present invention is configured as described above, and is compressed by a compressor to increase the temperature, and is exposed to the surrounding high temperature atmosphere to spray water into the air that has become even hotter. By doing so, the air can be cooled.
しかも、礒度の高くなった空気中に水を直接噴霧するの
で、その空気は泳が蒸発するための蒸発潜熱として約６
００ｋｃａｌ／ｋｇもの熱をうばゎれるため、エアフィ
ンクー２等をｍ−て間接的に冷却する従来の場合に比し
て、十分に効果的な冷却ができるという利点がある。Moreover, since the water is directly sprayed into the highly hot air, the air absorbs about 6 % of the latent heat of vaporization for the evaporation of the water.
Since it can dissipate as much as 1,000 kcal/kg of heat, it has the advantage that sufficiently effective cooling can be achieved compared to the conventional case in which the air fin cooler 2 and the like are indirectly cooled.
また、本発明によれば、ガスタービン内の冷却空気通路
中に水噴霧装置を設け、水噴霧を行なうだけであるため
、いったんガスタービンの外部に冷却空気を導いて冷却
する場合のように圧損の増加なしに冷却を行なうことが
できるという利点もある。In addition, according to the present invention, a water spray device is provided in the cooling air passage inside the gas turbine and only water spray is performed, so that once the cooling air is guided outside the gas turbine, there is no pressure drop. Another advantage is that cooling can be carried out without increasing the amount of water.
ここで、冷却空気室内の空気が水噴霧装置により噴霧さ
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
を行なったり、水が水滴状態でしたたり落ちたりした場
合、高温となっ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 is not hot enough to quickly evaporate the water sprayed by the water spray device, or if the water drips down in the form of droplets, the high temperature turbine Water droplets directly impinge on the component, rapidly cooling this area.
冷却空気室のタービン構成部材で特に燃焼器尾筒は、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Ｌ水滴が当っても、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, especially the combustor transition piece, the temperature is high because it comes into direct contact with combustion gas, and it is made of relatively thin plates, so even if a small amount of water drops hit this part, it will cool down rapidly. , which causes the occurrence of cracks.
しかも、燃焼器尾筒にクラックが発生すれば、燃焼ガス
が洩れることになる。Moreover, if a crack occurs in the combustor transition piece, combustion gas will leak.
そこで、特に本発明では、燃焼器尾筒に保護筒を設け、
仮に上記のような現象が起きても、尾筒に直接水滴が当
たることを防止し、有効に冷却を行なうことができると
いう効果がある。Therefore, especially in the present invention, a protection tube is provided in the combustor tail tube,
Even if the above-mentioned phenomenon occurs, there is an effect that water droplets can be prevented from directly hitting the transition piece and cooling can be carried out effectively.
一方、冷却空気を冷却し、その温度を下げる１、ことが
できれば、冷却空気量の増加なしにガスタービンの使用
ガス温度を上げることができる。On the other hand, if it is possible to cool the cooling air and lower its temperature, the temperature of the gas used in the gas turbine can be increased without increasing the amount of cooling air.
ここで従来の方法は冷却空気量を増すことによってもタ
ービン翼を冷却する能力が増し、使用ガス温度を上げる
ことができるが、使用ガス温度が上がるに伴い、タービ
ン翼の受ける熱量が増す一方、冷却空気自体の温度もが
なり高くなり、タービン翼との温度差が小さくなること
から、冷却空気量を増やしても冷却効果を大巾に良くす
ることはできないのに対して、本発明のガスタービンの
ごとく冷却空気の温度を下げれば、タービン翼との温度
差が大きくなり、冷却効果が大巾に改善される。Here, in the conventional method, the ability to cool the turbine blades increases by increasing the amount of cooling air, and the temperature of the gas used can be raised, but as the temperature of the gas used increases, the amount of heat received by the turbine blades increases. The temperature of the cooling air itself becomes higher and the temperature difference with the turbine blades becomes smaller, so even if the amount of cooling air is increased, the cooling effect cannot be greatly improved. If the temperature of the cooling air is lowered, as in a turbine, the temperature difference between it and the turbine blades will increase, and the cooling effect will be greatly improved.
しかも、冷却効果が向上すれば、冷却空気量を増加する
必要もなくなる。Furthermore, if the cooling effect is improved, there is no need to increase the amount of cooling air.
することなく、使用ガス温度を上げることができ、ガス
タービン′サイクル効率が向上する。It is possible to raise the temperature of the gas used without the need to increase the temperature, thereby improving the gas turbine's cycle efficiency.
更に、本発明によれば、冷却空気中に水噴霧を行なうた
め、その分冷却空気の容積が増加するので、圧縮機で圧
縮した冷却空気の使用量が減り、ガスタービンのサイク
ル効率が向上する。Furthermore, according to the present invention, since water is sprayed into the cooling air, the volume of the cooling air increases accordingly, which reduces the amount of cooling air compressed by the compressor and improves the cycle efficiency of the gas turbine. .
また、本発明によれば、冷却空気中に水分が加わるため
、冷却空気の比熱が増し、この面か°らも冷却空気のみ
の冷却よりも冷却効果が高く′なり、この分冷却空気の
使用量を減じるか、使用ガス温度を上げることができ、
ガスタービンのサイクル効率が向上する。In addition, according to the present invention, since moisture is added to the cooling air, the specific heat of the cooling air increases, and from this point of view, the cooling effect is higher than that of cooling using only the cooling air. You can reduce the amount or increase the gas temperature used,
The cycle efficiency of gas turbines is improved.
加えて、本発明によれば、ガスタービン内部の冷却空気
通路中で水を噴霧するため、いったんガスタービン外へ
導き、エアフィンクーラ等で冷却する場合のように圧損
の増加がなく、この方式では不可能であったタービン第
１段静翼のフィルム冷却も問題なく行なうことができる
という利点もある。In addition, according to the present invention, since water is sprayed in the cooling air passage inside the gas turbine, there is no increase in pressure loss, unlike when the water is once guided outside the gas turbine and cooled with an air fin cooler or the like. Another advantage is that film cooling of the first stage stator blades of the turbine, which was not possible in the conventional method, can be performed without any problem.
第１図は本発明のガスタービンの一実ＭＭ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。FIG. 1 is a schematic system diagram of an actual MM example of the gas turbine of the present invention, FIG. 2 is a sectional side view of the main part of the gas turbine of FIG. 1, and FIG. 3 is a combustor intermediate support plate of FIG. 2. It is a main part front view.
１・・・ガスタービン、２・・・圧縮機、６・・・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、１６・・・燃焼
器尾筒、３０・・・冷却空気室、６１・・・燃焼器本体
、３４．３６・・・タービン静翼”１ ３５ｔ ３７・
・・タービン動翼、４７・・・保護筒、Ａ・・・冷却空
気。DESCRIPTION OF SYMBOLS 1...Gas turbine, 2...Compressor, 6...Combustor, 4...Turbine, 5...Spray device, 9...Combustor chamber, 12...Combustor intermediate support Plate, 16...Combustor tail piece, 30...Cooling air chamber, 61...Combustor main body, 34.36...Turbine stationary blade"1 35t 37.
...Turbine rotor blade, 47...Protection tube, A...Cooling air.
Claims (1)
としてそのタービン翼に導き、タービン翼を冷却するガ
スタービンにおいて、該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と共に、燃焼器
尾筒の外周側には保護筒を設け、その燃焼器尾筒側に形
成された冷却空気室内に、水を噴霧可能な噴霧装置を設
けたことを特徴とするガスタービン。In a gas turbine that cools the turbine blades by guiding part of the air compressed by the compressor of the gas turbine to the turbine blades as cooling air, the inside of the combustor chamber of the gas turbine is divided into a combustor main body side and a combustor transition piece side. In addition, a protective tube is provided on the outer circumferential side of the combustor transition piece, and a spray device capable of spraying water is provided in the cooling air chamber formed on the combustor transition piece side. turbine.
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 true JPS59160034A (en) | 1984-09-10 |
| JPH0137575B2 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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1283338A1 (en) * | 2001-08-09 | 2003-02-12 | 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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1283338A1 (en) * | 2001-08-09 | 2003-02-12 | Siemens Aktiengesellschaft | Gas turbine and method for operating a gas turbine |
| US6786694B2 (en) | 2001-08-09 | 2004-09-07 | Siemens Aktiengesellschaft | Gas turbine and method of operating a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0137575B2 (en) | 1989-08-08 |
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