JPS59173527A - Gas turbine exhaust frame cooling air system - Google Patents
Gas turbine exhaust frame cooling air systemInfo
- Publication number
- JPS59173527A JPS59173527A JP4600083A JP4600083A JPS59173527A JP S59173527 A JPS59173527 A JP S59173527A JP 4600083 A JP4600083 A JP 4600083A JP 4600083 A JP4600083 A JP 4600083A JP S59173527 A JPS59173527 A JP S59173527A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- cooling
- cooling air
- air
- air system
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- 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
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明はガスタービンの排気フレーム冷却用の冷気系統
に係シ、特に、外部電源喪失時にも起動し得る機能を備
えた（いわゆるブラックスタート機能を有する）ガスタ
ービン発電設備に好適なように改良した排気フレーム冷
却空気系統に関するものである。[Detailed Description of the Invention] [Field of Application of the Invention] The present invention relates to a cold air system for cooling the exhaust frame of a gas turbine. This invention relates to an improved exhaust frame cooling air system suitable for gas turbine power generation equipment.
ガスタービンは高温ガスを作動流体として用いるため、
作動流体に接触する講成部材を耐熱性の材料にすると共
に、冷却手段を講じなければならない。Because gas turbines use high-temperature gas as the working fluid,
The course members that come into contact with the working fluid must be made of heat-resistant materials, and cooling means must be provided.
ガスタービンの静止体の中で冷却を必要とする部材バタ
ービンシェルおよび排気フレームでアル。The parts that require cooling in the stationary body of a gas turbine are the butter turbine shell and exhaust frame.
第１図にガスタービン部分断面図の代表例を示す。FIG. 1 shows a typical example of a partial cross-sectional view of a gas turbine.
第１図に於いて排気フレーム冷却管より矢印Ａのごとく
導入された空気は、タービンシェル４内に円周状に配置
され、その長さ方向に【ａつて該壁部分を貫通して延び
ている複数の冷却孔１５を通過し、タービンシェルを内
部冷却し、排気フレーム１６とアラ〉ディフューザ１９
とに囲まれた排気フレーム上部隔室１７へ導入される。Air introduced from the exhaust frame cooling pipe as shown by arrow A in FIG. It passes through a plurality of cooling holes 15 to internally cool the turbine shell, and connects the exhaust frame 16 and diffuser 19.
The air is introduced into the upper compartment 17 of the exhaust frame surrounded by.
次に排気フレーム１６内にその半径方向に配置された複
数個のストラット１８とエアホイル２０によって囲まれ
たストラット隔室２１内を流れ、該ストラット１８を表
面冷却し、次に、排気フレーム１６及びインナーディフ
ューザ２２によって囲まれた排気フレーム下部隔室２３
へ導入され、その一部は、ガスタービン軸方向に沿って
タービン下流側へ、又一部は、上流側へ流れて第３段タ
ービン後側ホイールスペース内へ流れる。本冷却空気は
上述の各部を冷却する７ビけでなく、アクタディフュー
ザとインナーディフューザを流れる高温作動ガスの冷却
系統内への洩れを防止する作用も兼オコるため、高温作
動ガス圧とバランスするに必要な空気圧力を維持してい
る。上述した様に年々作動流体温度は上昇しておシ、又
、公害対策として排気ガス系統に脱硝装置が、さらに、
省エネ対策として排年回収ボイラが設置され、本排気フ
ード内の作動流体圧力も上昇している。従って本排気フ
レーム冷却空気系統に要求される空気流量ならびに圧力
も、増加しており、ガスタービン全体性能を最適化する
冷却空気系統を選択する必要がある。It then flows through a strut compartment 21 surrounded by a plurality of struts 18 and airfoils 20 disposed radially within the exhaust frame 16 to surface cool the struts 18, and then to the exhaust frame 16 and the inner Exhaust frame lower compartment 23 surrounded by diffuser 22
A portion of the gas flows toward the downstream side of the turbine along the axial direction of the gas turbine, and a portion of it flows upstream into the rear wheel space of the third stage turbine. This cooling air not only cools the above-mentioned parts, but also prevents the high-temperature working gas flowing through the acta diffuser and inner diffuser from leaking into the cooling system, so it balances with the high-temperature working gas pressure. maintains the air pressure necessary for As mentioned above, the temperature of the working fluid is rising year by year, and denitrification devices are being installed in the exhaust gas system as a pollution control measure.
An annual recovery boiler has been installed as an energy-saving measure, and the working fluid pressure inside the main exhaust hood has also increased. Accordingly, the air flow rate and pressure required for the present exhaust frame cooling air system are also increasing, and it is necessary to select a cooling air system that optimizes the overall performance of the gas turbine.
以前においてはガスタービンのタービンシェル及び排気
フレームはガスタービン圧縮機の抽気で冷却されていた
が、排気圧損増加ならびに燃焼温度増加に伴ない、冷却
空気圧力及び流散増加が顕著となり、従米通り圧縮機抽
気を１吏用するとガスタービン性能に少なからず影＃を
及ぼすようになった。即ち、圧縮機抽気でタービンシェ
ル及び排気フレームを冷却しようとすると、その抽気部
は圧縮機空′Ａ破の約０．７％に達する。抽気量が増加
すると、タービン通過ガス量の低下を招き、ガスタービ
ンの出力低下が発生する。In the past, the turbine shell and exhaust frame of gas turbines were cooled by the extracted air from the gas turbine compressor, but as the exhaust pressure drop and combustion temperature increased, the cooling air pressure and dissipation increased significantly. Using just one bleed air has started to have a considerable effect on the performance of the gas turbine. That is, when attempting to cool the turbine shell and exhaust frame with compressor bleed air, the bleed portion reaches approximately 0.7% of the compressor air failure. When the amount of extracted air increases, the amount of gas passing through the turbine decreases, resulting in a decrease in the output of the gas turbine.
こうした不具合を解消するンｔめ、最近は、電動機で、
不動される＃Ａフ゛ロワを用いて刀スタービンの静止部
材を冷却する冷却空気系統が設けられる。In order to solve these problems, recently electric motors have been
A cooling air system is provided that uses stationary #A followers to cool the stationary components of the sword turbine.
ブロワによる込風は圧縮機の油気に比して低温で冷却効
率が良い。第２図は従来の排執フレーム冷却空気系統を
示す。１は圧縮機、２はタービン、３は燃ｍ器、４はタ
ービンシェル、５は排気フード、６は第１軸受、７は第
２軸受、８は逆止弁、９はブロワ、１０は電動機、１１
は吸気サイレンサである。ま／ζ、’ Ａ Ｅ ｓは
上記の圧縮機ｌの５段油気口、ＡＥ−１１は同じく１１
段抽気口である。前記の冷却用ブロワ９は２台設置され
、１台はランニングスペアである。従って、１台故障時
も安全に運転継続できる。大気よシ吸い込まれた冷却空
気は当該ブロワで必要圧力に加圧され、マニホルドを通
った後、タービンシェル内へ導入され、前述した通シ、
タービンシェル及び排、２（７レームを冷却する。上記
ブロワ９は電動機駆動の為、父流戒源を必要とするが、
ブラックスタート機能が必要な場合、ガスタービンは外
部交流電源の供給を受けずに起動する必要がある。とこ
ろがガスタービン発電設備においては、原動機であるガ
スタービンが起動した後の過渡的状態を過ぎて定格状態
になるまでの間、発電が正常に行われないので、ブロワ
９を駆動する電動機１０の運転ができない。The air generated by the blower is lower in temperature and has better cooling efficiency than the oil from the compressor. FIG. 2 shows a conventional exclusive frame cooling air system. 1 is a compressor, 2 is a turbine, 3 is a combustor, 4 is a turbine shell, 5 is an exhaust hood, 6 is a first bearing, 7 is a second bearing, 8 is a check valve, 9 is a blower, 10 is an electric motor , 11
is an intake silencer. M/ζ,' A E s is the 5th stage oil port of the above compressor l, and AE-11 is also the 11
It is a stage bleed port. Two cooling blowers 9 are installed, one of which is a running spare. Therefore, even if one unit fails, operation can be continued safely. Cooling air sucked in from the atmosphere is pressurized to the required pressure by the blower, passes through the manifold, and is introduced into the turbine shell, and is then
Cools the turbine shell and exhaust gas, 2 (7 rams).The blower 9 is driven by an electric motor, so it requires a father flow source.
If a black start function is required, the gas turbine must be started without external AC power supply. However, in gas turbine power generation equipment, power generation does not occur normally until the rated state is reached after the gas turbine, which is the prime mover, passes through a transient state after starting, so the operation of the electric motor 10 that drives the blower 9 is interrupted. I can't.
一方、排気フレームの冷却はガスタービンの起動と同時
に開始しなければならない。On the other hand, cooling of the exhaust frame must begin at the same time as the gas turbine is started.
従来技術においてこの問題を解消して、定格運転状態に
謹する以前にブロワ９のｇ動電動機を運転しようとする
と、低周波低電圧供給装置などを設置する必要がある。In the prior art, if this problem is solved and the g-dynamic motor of the blower 9 is operated before the rated operating state is reached, it is necessary to install a low frequency, low voltage supply device or the like.
又、試運転時等に、クランキング速度（２０％速度）又
は、無負荷連続運転する場合など、従来技術では、電動
機吏用に制約が発生する。Further, in the conventional technology, there are restrictions on the electric motor when cranking speed (20% speed) or continuous no-load operation is performed during trial operation.
本発明は上述の＄情に鑑みて為され、ブロワを駆動する
ための狩殊な電気機器類を設ける必要無く、ガスタービ
ンの起動操作における過渡的状態、並びにガスタービン
の停止操作にお・ける過渡的枦態で当該ガスタービンの
空気作動を行うことカニでき、しかも当該ガスタービン
発電設備の定常運転における出力や効率に悪影響を及ば
ず虞れの無いガスタービン排気フレーム冷却空気系統を
提供することを目的とする。The present invention has been made in view of the above-mentioned circumstances, and is capable of handling transient conditions during gas turbine startup operations and gas turbine shutdown operations without requiring special electrical equipment for driving the blower. To provide a gas turbine exhaust frame cooling air system capable of air-operating the gas turbine in a transient state and without causing any risk of adversely affecting the output or efficiency during steady operation of the gas turbine power generation equipment. With the goal.
〔発明の概要〕
上記の目的を達成するため、本発明は、外部電源喪失時
に起動し得る機能を備えたガスタービン発電設備におい
て、電動機１駆動のブロワを有する冷却空気系統に、ガ
スタービン用圧縮機の抽気部を空気源とする抽出空気ラ
インを接続すると共に、上記の抽出空気ライン中に空気
流量制御手段を設け、当該ガスタービンの起動操作時お
よび停止操作時に圧縮機油気を冷却空気系統に供給し得
べく、かつ、定常運転時に圧縮機抽気と冷却空気系統と
を遮断し得べくなしたることを特徴とする。[Summary of the Invention] In order to achieve the above-mentioned object, the present invention provides a gas turbine compressor for a cooling air system having a blower driven by an electric motor 1 in a gas turbine power generation facility equipped with a function that can be activated when an external power source is lost. In addition to connecting an extracted air line that uses the air bleed section of the turbine as an air source, an air flow control means is installed in the extracted air line to control compressor oil and air to the cooling air system when starting and stopping the gas turbine. The compressor bleed air and the cooling air system can be shut off during steady operation.
次に、本発明の１実施例を４３図について説明する。 Next, one embodiment of the present invention will be described with reference to FIG.
この実施例は、第２図に示した従来のガスタービンの排
気フレーム冷却空気系統に本発明を適用して改良したも
ので、第２図と同一の図面参照番号を附した圧ｍ機１．
タービン２．燃焼器３．タービンシェル４．排気フード
５．４１ｑ’＋Ｈ受６．第２軸受７．逆止弁８．プロワ
９，１ＪＩＪＪ機１０．及び吸気サイレンサ１１は従来
装置にｋけると同様乃至は類似の構成部材である。前述
の理由によりプロワ９を２基設置し、それぞれ逆止弁８
．電動機１０．及び吸気サイレンサ１１を備えている。This embodiment is an improved version of the conventional gas turbine exhaust frame cooling air system shown in FIG. 2 by applying the present invention.
Turbine 2. Combustor 3. Turbine shell 4. Exhaust hood 5.41q'+H receiver 6. Second bearing7. Check valve8. Prowa 9,1JIJJ machine 10. The intake silencer 11 is the same or similar component to the conventional device. For the reasons mentioned above, two blowers 9 were installed, each with a check valve 8.
．． Electric motor 10. and an intake silencer 11.
上記２個の逆止弁８の流出口の合流点Ｂはタービンシェ
ル４に連辿する排気フレーム冷却管１４に接続しである
。A confluence point B of the outlet ports of the two check valves 8 is connected to an exhaust frame cooling pipe 14 that continues to the turbine shell 4.
当該ガスタービンの圧縮機１の抽気口ＡＥ−５と、前記
の合流点Ｂとの間を抽出空気ライン２４で接続し、この
抽出空気ライン２４ Ｖ（、シャットオフ弁１２とオリ
フィス１３とを設けて抽出空気ライン２４日の生気流は
をｎｌＪ婢し得るように１我する。The extraction air line 24 connects the extraction port AE-5 of the compressor 1 of the gas turbine and the above-mentioned confluence B, and the extraction air line 24V (which is provided with a shutoff valve 12 and an orifice 13) The extraction air line is 24 days old so that the fresh air flow can be increased.
不発明全実施する場合、上記の空気流績を側脚する手段
ｉｆま、上記夷惰例のごとくシャットオフ弁とオリフィ
スとの併用に限ら）Ｌるものではなく、適宜の空気機器
を任意に選定して用い得るが、抽出空気ライン２４の締
切シが０Ｔ目ヒなように構成する。If the invention is fully implemented, the means for controlling the air flow as described above is not limited to the combination of a shut-off valve and an orifice as in the above example, but any suitable air equipment may be used. Although it can be used selectively, the extraction air line 24 is configured so that the cut-off point is 0T.
以上のように構成した排気７ンーム［相］却臣気系ａｆ
ｃ設けたガスタービン発醒設備に、ｊ・・いては、ガス
タービンの始動後、定格運転に移行するまでの過渡的期
間においてはシャットオフ弁１２を開き、圧縮機１の抽
気を抽気空気ライン２４．排気フレーム冷却管１４を介
してタービンシェル４に供給して空気冷却を行わせる。Exhaust 7-meter [phase] air system af configured as above
In the gas turbine start-up equipment equipped with c..., the shutoff valve 12 is opened during the transition period after the gas turbine starts and before the transition to rated operation, and the bleed air of the compressor 1 is diverted to the bleed air line. 24. Air is supplied to the turbine shell 4 through an exhaust frame cooling pipe 14 for air cooling.
ガスタービンに発電負荷を掛けるまでの間の排気ガス温
度は、例えば約３００Ｃというように比較的低温である
ため、圧縮機の抽気で充分に冷却し得る。Since the temperature of the exhaust gas until the power generation load is applied to the gas turbine is relatively low, for example, about 300 C, it can be sufficiently cooled by the bleed air of the compressor.
ガスタービンが定格、：！に転に移行して発電機を、駆
動し、定格電圧、定格周波数の発電が開始されると、シ
ャットオフ弁１２を全閉にする。これによシ圧縮機１の
抽気口ＡＥ−５は排気フレーム冷却管１４と遮断される
ので、圧縮機１に別設の悪影響を及ぼす！４れが無くな
る。そして、ガスタービンによる発電が開始された後、
定常運転中は発電電力の１部によシ准動４−７１）１０
を運転してプロワ９を駆動し、空気冷却を行わせる。Gas turbines are rated:! When the power generator is shifted to the next stage and the generator is driven, and power generation at the rated voltage and frequency is started, the shutoff valve 12 is fully closed. As a result, the air bleed port AE-5 of the compressor 1 is cut off from the exhaust frame cooling pipe 14, which has a separate adverse effect on the compressor 1! 4. After the gas turbine starts generating electricity,
During steady operation, a part of the generated power is used as a sub-activation 4-71) 10
is operated to drive the blower 9 and perform air cooling.
発電機の負荷を遮断してガスタービンの停止操作を行う
場合も、シャットオフ弁１２を用いて圧縮機１の抽気に
よυ空気冷却を行う。Even when the gas turbine is stopped by cutting off the load on the generator, the shutoff valve 12 is used to perform υ air cooling by extracting air from the compressor 1.
本実施例におけるプロワ駆動用電動機出力は４５ｋＷで
、発電機定格出力の約０．２％に相当する。The blower drive electric motor output in this example is 45 kW, which corresponds to about 0.2% of the generator rated output.
一方、圧縮機１の抽気によってガスタービン定格運転時
の空気冷却を行う場合について試算すると、圧縮空気量
の０．７％を抽気する必要があシ、これによってガスタ
ービン出力が約５００ｋＷｌｉ下し、発電機定格出力の
約２％低下を招く。On the other hand, when calculating the case where air is cooled during rated operation of the gas turbine by extracting air from the compressor 1, it is necessary to extract 0.7% of the compressed air amount, which reduces the gas turbine output by about 500kWli. This results in a decrease of approximately 2% in the generator's rated output.
従って、本発明の適用により、空気冷却のだめの損失が
５００ｋＷから４５ｋＷにＩ軽減され、冷却空気損が従
来装置に比して４５ ｋＷ／ ５００ｋＷ＝ ０．０９
（９％）に軽減される。Therefore, by applying the present invention, the loss of the air cooling tank is reduced from 500 kW to 45 kW, and the cooling air loss is 45 kW/500 kW = 0.09 compared to the conventional device.
(9%).
以上詳述したように、本発明は、外部１源喪失時に起動
し得る機能を備えたガスタービン発電設備において、電
動機駆動のプロワを竹する冷却空気系統に、ガスタービ
ン用圧縮機の抽気部を空気源とする抽出２ ”Ａライン
を接続すると共に、上記の抽出空気ライン中に空気流量
制御手段を設け、当該ガスタービンの起動操作時および
停止操作時に圧縮機抽気を冷却空気系統に供給し得べく
、かつ、定常運転時に圧縮機抽気と冷却空気系統とを遮
断し得べく為すことにより、当該ガスタービンに冷却空
気を供給するプロワを、駆動するだめの特殊な電気機器
類を設ける必要無く、ガスタービンの起動操作における
過渡的状態、並びにガスタービンの停止操作における過
渡的状態で当該ガスタービン静止部材の空気冷却を行う
ことができ、しかも当該ガスタービン発電設備の定常運
転における出力や効率に悪影響を及ぼす虞れが無いとい
う優れた実用的効果を奏し、ガスタービン発電設備の効
率向上および出力増加に貢献するところ多大である。As described in detail above, the present invention provides a gas turbine power generation facility that includes a bleed section of a gas turbine compressor in a cooling air system that connects an electric motor-driven blower in a gas turbine power generation facility that is equipped with a function that can be activated when one external source is lost. Extraction 2 as an air source In addition to connecting the A line, an air flow rate control means can be provided in the above extraction air line to supply compressor bleed air to the cooling air system during startup and shutdown operations of the gas turbine. By making it possible to cut off the compressor bleed air and the cooling air system during steady operation, there is no need to install special electrical equipment to drive the blower that supplies cooling air to the gas turbine. Air cooling of the gas turbine stationary components can be performed in a transient state during a gas turbine startup operation and a transient state during a gas turbine shutdown operation, and it does not have an adverse effect on the output or efficiency during steady operation of the gas turbine power generation equipment. It has an excellent practical effect in that there is no risk of causing damage, and it greatly contributes to improving the efficiency and increasing the output of gas turbine power generation equipment.
第１図はガスタービンの空気冷却経路を示すだめの縦断
面図、第２図は従来の排気フレーム冷却空気系統を付記
したカスタービンの縦断面図、第３図は本発明の排ズ（
フレーム冷却空気系統の１実施例を・浦えたガスタービ
ンの縦断面図である。
１・・・圧縮ｄ、’２・・・タービン、４・・・タービ
ンシェル、５・・・排気フード、８・・・逆止弁、９・
・・プロワ、１０・・・嵯動１４．１１・・・吸気サイ
レンサ、１２・・・シャットオフ弁、１３・・・オリフ
ィス、１４・・・排気フレーム冷却管、１５・・・ター
ビンシェル冷却孔、１６・・・排気フレーム、２４・・
・抽出空気ライン。
代壊Δ−弁理士 −秋塞玉区Fig. 1 is a vertical cross-sectional view of a gas turbine showing the air cooling path, Fig. 2 is a longitudinal cross-sectional view of a gas turbine with a conventional exhaust frame cooling air system added, and Fig. 3 is a longitudinal cross-sectional view of the gas turbine according to the present invention.
1 is a longitudinal cross-sectional view of a gas turbine showing one embodiment of a frame cooling air system. 1... Compression d, '2... Turbine, 4... Turbine shell, 5... Exhaust hood, 8... Check valve, 9...
...Prower, 10...Driving 14.11...Intake silencer, 12...Shutoff valve, 13...Orifice, 14...Exhaust frame cooling pipe, 15...Turbine shell cooling hole , 16...exhaust frame, 24...
-Extraction air line. Substitute Δ - Patent Attorney - Qiu Seiyu District
Claims (1)
タービン発電設備において、電動機駆動のブロワ分有す
る冷却空気系統に、ガスタービン用圧縮機の抽気部を空
気源とする抽出空気ラインを接続すると共に、上記の抽
出空気ライン中に空気流量制御手段を設け、当該ガスタ
ービンの起動操作時および停止操作時に圧縮機抽気を冷
却空気系統に供給し得べく、かつ、定常運転時に圧縮機
油気と冷却空気系統とを遮断し得べくなしたることを特
徴とするガスタービン排気フレーム冷却空気系統。1. In gas turbine power generation equipment equipped with a function that can be activated when an external power source is lost, an extraction air line whose air source is the extraction part of the gas turbine compressor is connected to the cooling air system that includes a motor-driven blower. At the same time, an air flow rate control means is provided in the above-mentioned extraction air line to supply compressor bleed air to the cooling air system during startup and shutdown operations of the gas turbine, and to supply compressor oil and gas during steady operation. A gas turbine exhaust frame cooling air system characterized in that the cooling air system is isolated from the cooling air system as much as possible.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4600083A JPS59173527A (en) | 1983-03-22 | 1983-03-22 | Gas turbine exhaust frame cooling air system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4600083A JPS59173527A (en) | 1983-03-22 | 1983-03-22 | Gas turbine exhaust frame cooling air system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS59173527A true JPS59173527A (en) | 1984-10-01 |
| JPH0114408B2 JPH0114408B2 (en) | 1989-03-10 |
Family
ID=12734813
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4600083A Granted JPS59173527A (en) | 1983-03-22 | 1983-03-22 | Gas turbine exhaust frame cooling air system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59173527A (en) |
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| JP2002054458A (en) * | 2000-08-08 | 2002-02-20 | General Electric Co <Ge> | Control of tongue and groove joint load and air/oil seal temperature of turbine |
| JP2007138930A (en) * | 2005-11-15 | 2007-06-07 | General Electric Co <Ge> | Integrated turbine sealing air and active clearance control system and method |
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-
1983
- 1983-03-22 JP JP4600083A patent/JPS59173527A/en active Granted
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Also Published As
| Publication number | Publication date |
|---|---|
| JPH0114408B2 (en) | 1989-03-10 |
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