JPS59220609A - Clearance measuring method during turbine operation - Google Patents
Clearance measuring method during turbine operationInfo
- Publication number
- JPS59220609A JPS59220609A JP9410583A JP9410583A JPS59220609A JP S59220609 A JPS59220609 A JP S59220609A JP 9410583 A JP9410583 A JP 9410583A JP 9410583 A JP9410583 A JP 9410583A JP S59220609 A JPS59220609 A JP S59220609A
- Authority
- JP
- Japan
- Prior art keywords
- clearance
- gas
- turbine
- temp
- turbine rotor
- 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
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/16—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance of clearance between spaced objects
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Length Measuring Devices With Unspecified Measuring Means (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
この発明は、ガスタービンエンジンのタービン運転中の
クリアランス測定方法に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a method for measuring clearance during turbine operation of a gas turbine engine.
回転機械のクリアランスを測定する従来の測定方法して
は、例えば第１図に示すようなガスタービンのコールド
セクションにある圧縮機のインペラと固定壁間のクリア
ランス測定方法がある。A conventional method for measuring the clearance of a rotating machine is, for example, a method for measuring the clearance between an impeller and a fixed wall of a compressor in the cold section of a gas turbine, as shown in FIG.
すなわち、高速軸１に固定された圧縮機インペラ２と固
定壁６とのクリアランスδＣを測定するには、コイルを
内蔵したギャップセンサ４をインペラ出口部の固定壁３
に埋設し、そのギャップセンサ４は、ギャップδＣの大
きさに応じてコイルのりアクタンスが変化するので、第
２図に示すように、オシレータおよびディモジュレータ
等からなる検出回路５に接続し、その発振周波数し；応
じた出力電圧■ｏを記録計等に記録して、第３図に示す
ような■。−δＣ線図によりクリアランスδＣを求めて
いた。That is, in order to measure the clearance δC between the compressor impeller 2 fixed to the high-speed shaft 1 and the fixed wall 6, the gap sensor 4 with a built-in coil is connected to the fixed wall 3 at the impeller outlet.
Since the coil actance of the gap sensor 4 changes depending on the size of the gap δC, the gap sensor 4 is connected to a detection circuit 5 consisting of an oscillator, a demodulator, etc., as shown in FIG. Record the corresponding output voltage (2) on a recorder, etc., as shown in Figure 3. The clearance δC was determined using the −δC diagram.
しかしながら、このような従来の回転機械のクリアラン
ス測定方法に使用されているギャップセンサ４の耐熱温
度は１００℃以下であるのに対し、第１図に示すような
コールドセレクションにある圧縮機の場合でも、ギャッ
プセンサ４を装着したインペラ出口部では、圧力比が高
い場合、例えば圧力比５．０では空気温度がほぼ２５０
℃となり、図示していないが何等かの冷却装置を必要と
する。However, while the heat resistance temperature of the gap sensor 4 used in the conventional clearance measurement method for rotating machinery is 100°C or less, even in the case of a compressor in cold selection as shown in Fig. 1. , at the impeller outlet where the gap sensor 4 is installed, when the pressure ratio is high, for example, when the pressure ratio is 5.0, the air temperature is approximately 250°C.
℃, and requires some kind of cooling device (not shown).
したがって、その冷却にもおのずから限界があリ、ター
ビンロータのようなホットセクションには到底使用する
ことはできず、タービン運転中のクリアランス測定はき
わめて困難であった。Therefore, there is a limit to its cooling, and it cannot be used in a hot section such as a turbine rotor, making it extremely difficult to measure the clearance during turbine operation.
この発明は上記の点に鑑みてなされたもので、高温のタ
ービンロータ先端とこれに近接して設けられたシュラウ
ド壁面との間のクリアランスを、タービン運転中に計測
するクリアランス測定方法を提供することを目的とする
ものである。The present invention has been made in view of the above points, and an object of the present invention is to provide a clearance measurement method for measuring the clearance between a high-temperature turbine rotor tip and a shroud wall surface provided in close proximity thereto during turbine operation. The purpose is to
そのため、この発明によるタービン運転中のクリアラン
ス測定方法は、軸流タイプのタービンロータの出口から
所定距離下流のシュラウド壁面近傍のガス温度が、ター
ビンロータ先端とシュラウド壁面とのクリアランスの大
きさに関連することに着目し、上記ガス温度を温度セン
サによって計測するようにしたものである。Therefore, in the method for measuring clearance during turbine operation according to the present invention, the gas temperature near the shroud wall surface a predetermined distance downstream from the outlet of an axial flow type turbine rotor is related to the size of the clearance between the tip of the turbine rotor and the shroud wall surface. Taking this into consideration, the gas temperature is measured by a temperature sensor.
以下、添付図面の第４図乃至第６図を参照してこの発明
の詳細な説明する。The present invention will now be described in detail with reference to FIGS. 4 to 6 of the accompanying drawings.
軸流タイプのタービンロータＳの先端と、こ九し；近接
して設けられたシュラウド壁面７の間にはクリアランス
δＴを有し、タービンロータ６の上流側には静止タービ
ンノズル８が設けられている。There is a clearance δT between the tip of the axial flow type turbine rotor S and the shroud wall surface 7 provided closely, and a stationary turbine nozzle 8 is provided on the upstream side of the turbine rotor 6. There is.
このタービンロータ６の出口部の下流のシュラウド壁面
７に、熱電対等の温度センサ９を設けてシュラウド壁面
７の近傍のガス温度を測定し得るようにし、温度センサ
９のタービンロータ６の出口からの距離を、第５図に示
すようにクリアランスδＴを通過したガスＡとタービン
ロータ６を通過したガスＢとが混合する点までの所定距
離りとする。A temperature sensor 9 such as a thermocouple is provided on the shroud wall surface 7 downstream of the outlet of the turbine rotor 6 so that the gas temperature near the shroud wall surface 7 can be measured. The distance is a predetermined distance from the point where the gas A that has passed through the clearance δT and the gas B that has passed through the turbine rotor 6 mix, as shown in FIG.
この場合、タービンロータ６の先端とシュラウド壁面７
とのクリアランス６丁を通過するガスはタービンによっ
て膨張することはないので、その温度は入口温度に近い
まま通過するが、タービンロータ６を通過するガスはタ
ービンによって膨張するので、通過後のガスは温度が降
下する。In this case, the tip of the turbine rotor 6 and the shroud wall surface 7
The gas passing through the clearance 6 between the turbine rotor 6 is not expanded by the turbine, so its temperature remains close to the inlet temperature. However, the gas passing through the turbine rotor 6 is expanded by the turbine, so the gas after passing is The temperature drops.
これらの２つのガスはタービンロータ６の出口を出た後
、所定の助走距離りを経て混合されるが混合後のガスの
温度は次式で表わされる。After these two gases exit the outlet of the turbine rotor 6, they are mixed after a predetermined run-up distance, and the temperature of the gases after mixing is expressed by the following equation.
但し、Ｔｍ１ｘ ：混合後のガス温度
Ｇ１ ：クリアランスを通過するガス流量Ｇ２：ロータ
通過後混合に寄与するガス流量Ｔ１ ：タービン入口の
ガス温度
Ｔ２：ロータ出口のガス温度
ＣＰＩ ：タービン入口のガスの比熱比ＣＰ２：ロー
タ出口のガスの比熱比
ここで通常Ｃｐ１”＋Ｃｐｚであるので、上記（１）式
は次のように書き換えることができる。However, Tm1x: Gas temperature after mixing G1: Gas flow rate passing through the clearance G2: Gas flow rate contributing to mixing after passing through the rotor T1: Gas temperature at the turbine inlet T2: Gas temperature at the rotor outlet CPI: Specific heat of the gas at the turbine inlet Ratio CP2: Specific heat ratio of gas at the rotor outlet Since it is usually Cp1''+Cpz, the above equation (1) can be rewritten as follows.
この（２）式から分かるように、混合後のガス温度はク
リアランスδＴを通過するガス流量Ｇ１に関係し、また
クリアランスδＴを通過するガス流量はクリアランスδ
Ｔの大きさに比例するので、タービン入口のガス温度が
一定の場合には、混合後のガス温度を計測することによ
りクリアランスの量を求めることができる。As can be seen from equation (2), the gas temperature after mixing is related to the gas flow rate G1 passing through the clearance δT, and the gas flow rate passing through the clearance δT is related to the gas flow rate G1 passing through the clearance δT.
Since it is proportional to the magnitude of T, if the gas temperature at the turbine inlet is constant, the amount of clearance can be determined by measuring the gas temperature after mixing.
第６図はクリアランスδＴと測定点での混合ガス温度Ｔ
ｍｉｘとの関係を示す線図であり、クリアランスδＴ
は混合後のガス温度Ｔｍ１ｘに比例することが判る。Figure 6 shows the clearance δT and the mixed gas temperature T at the measurement point.
It is a diagram showing the relationship between the clearance δT and the mix.
It can be seen that is proportional to the gas temperature Tm1x after mixing.
以上述べたように、この発明によれば、タービンロータ
出口から所定距離下流のシュラウド壁面近傍のガス温度
を計測することにより、タービン運転中のクリアランス
を測定するようにしたので、従来の回転機械のクリアラ
ンス測定に必要とした耐熱温度の低いギャップセンサを
用いる必要がなく、これまで計測が困難であったホット
セクションであるタービンロータとシュラウド壁面との
クリアランスを運転中に容易に計測することができる。As described above, according to the present invention, the clearance during turbine operation is measured by measuring the gas temperature near the shroud wall a predetermined distance downstream from the turbine rotor outlet. There is no need to use a gap sensor with a low heat resistance that was required for clearance measurement, and the clearance between the turbine rotor and the shroud wall surface, which is a hot section that has been difficult to measure, can be easily measured during operation.
それにより、タービンロータとシュラウド壁面とが接触
してタービンが破損する危険を未然に防止できると共に
、クリアランスを最適値に保つことにより、タービンの
性能を最高の状態に維持し得る優れた効果を有する。As a result, it is possible to prevent the risk of damage to the turbine due to contact between the turbine rotor and the shroud wall, and by keeping the clearance at an optimal value, it has the excellent effect of maintaining the performance of the turbine at its best. .
第１図は、従来の回転機械のクリアランス測定装置の一
例を示す説明図、
第２図は、同じくその測定装置を示すブロック図、第３
図は、同しくその測定装置の出力電圧とクリアランスと
の関係を示す線図である。
第４図は、この発明によるタービン運転中のクリアラン
ス測定方法を実施するために温度センサを配設したガス
タービンエンジンのタービンロータ付近の断面図、
第５図は、この発明によるクリアランス測定原理の説明
図、
第６図は、タービンロータ出口から所定距離下流のシュ
ラウド壁面近傍のガス温度とクリアランスとの関係を示
す線図である。
６・・・タービンロータ ７・ シュラウド壁面近傍
例・温度センサ Ｄ・・所定距離第１図
第２図
ら
第４図゛FIG. 1 is an explanatory diagram showing an example of a conventional clearance measuring device for a rotating machine, FIG. 2 is a block diagram similarly showing the measuring device, and FIG.
The figure is a diagram showing the relationship between the output voltage and clearance of the measuring device. FIG. 4 is a cross-sectional view of the vicinity of the turbine rotor of a gas turbine engine in which a temperature sensor is installed to carry out the method of measuring clearance during turbine operation according to the present invention. FIG. 5 is an explanation of the principle of clearance measurement according to the present invention. FIG. 6 is a diagram showing the relationship between gas temperature and clearance near the shroud wall surface a predetermined distance downstream from the turbine rotor outlet. 6... Turbine rotor 7. Example near shroud wall surface/Temperature sensor D... Predetermined distance Fig. 1 Fig. 2 to Fig. 4
Claims (1)
、タービンロータ出口から所定距離下流のシュラウド壁
面近傍のガス温度を温度センサによって計測することに
より、タービン運転中のタービンロータ先端とこれに近
接して設けられたシュラウド壁面とのクリアランスを測
定するようにしたことを特徴とするタービン運転中のク
リアランス測定方法。1. In an axial flow turbine of a gas turbine engine, by measuring the gas temperature near the shroud wall surface a predetermined distance downstream from the turbine rotor outlet using a temperature sensor, A method for measuring clearance during turbine operation, characterized in that the clearance between a shroud and a shroud wall is measured.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9410583A JPS59220609A (en) | 1983-05-30 | 1983-05-30 | Clearance measuring method during turbine operation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9410583A JPS59220609A (en) | 1983-05-30 | 1983-05-30 | Clearance measuring method during turbine operation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS59220609A true JPS59220609A (en) | 1984-12-12 |
Family
ID=14101155
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9410583A Pending JPS59220609A (en) | 1983-05-30 | 1983-05-30 | Clearance measuring method during turbine operation |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59220609A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0330492A2 (en) * | 1988-02-24 | 1989-08-30 | General Electric Company | Active clearance control |
| US7013718B2 (en) * | 2003-04-28 | 2006-03-21 | Watson Cogeneration Company | Method for monitoring the performance of a turbine |
| JP2006292535A (en) * | 2005-04-11 | 2006-10-26 | Omron Corp | Distance estimating device, abnormality detection device, temperature controller and heat treatment device |
| CN107576293A (en) * | 2017-10-11 | 2018-01-12 | 中国航发南方工业有限公司 | Cantilever fulcrum glitch detection frock and detection method |
| US11802257B2 (en) | 2022-01-31 | 2023-10-31 | Marathon Petroleum Company Lp | Systems and methods for reducing rendered fats pour point |
| US11860069B2 (en) | 2021-02-25 | 2024-01-02 | Marathon Petroleum Company Lp | Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers |
| US11891581B2 (en) | 2017-09-29 | 2024-02-06 | Marathon Petroleum Company Lp | Tower bottoms coke catching device |
| US11898109B2 (en) | 2021-02-25 | 2024-02-13 | Marathon Petroleum Company Lp | Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers |
| US11905468B2 (en) | 2021-02-25 | 2024-02-20 | Marathon Petroleum Company Lp | Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers |
| US11905479B2 (en) | 2020-02-19 | 2024-02-20 | Marathon Petroleum Company Lp | Low sulfur fuel oil blends for stability enhancement and associated methods |
| US11970664B2 (en) | 2021-10-10 | 2024-04-30 | Marathon Petroleum Company Lp | Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive |
| US11975316B2 (en) | 2019-05-09 | 2024-05-07 | Marathon Petroleum Company Lp | Methods and reforming systems for re-dispersing platinum on reforming catalyst |
| US12000720B2 (en) | 2018-09-10 | 2024-06-04 | Marathon Petroleum Company Lp | Product inventory monitoring |
| US12031094B2 (en) | 2023-06-22 | 2024-07-09 | Marathon Petroleum Company Lp | Assemblies and methods for enhancing fluid catalytic cracking (FCC) processes during the FCC process using spectroscopic analyzers |
-
1983
- 1983-05-30 JP JP9410583A patent/JPS59220609A/en active Pending
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0330492A2 (en) * | 1988-02-24 | 1989-08-30 | General Electric Company | Active clearance control |
| US7013718B2 (en) * | 2003-04-28 | 2006-03-21 | Watson Cogeneration Company | Method for monitoring the performance of a turbine |
| JP2006292535A (en) * | 2005-04-11 | 2006-10-26 | Omron Corp | Distance estimating device, abnormality detection device, temperature controller and heat treatment device |
| US11891581B2 (en) | 2017-09-29 | 2024-02-06 | Marathon Petroleum Company Lp | Tower bottoms coke catching device |
| CN107576293B (en) * | 2017-10-11 | 2020-02-07 | 中国航发南方工业有限公司 | Cantilever fulcrum bounce detection tool and detection method |
| CN107576293A (en) * | 2017-10-11 | 2018-01-12 | 中国航发南方工业有限公司 | Cantilever fulcrum glitch detection frock and detection method |
| US12000720B2 (en) | 2018-09-10 | 2024-06-04 | Marathon Petroleum Company Lp | Product inventory monitoring |
| US11975316B2 (en) | 2019-05-09 | 2024-05-07 | Marathon Petroleum Company Lp | Methods and reforming systems for re-dispersing platinum on reforming catalyst |
| US11905479B2 (en) | 2020-02-19 | 2024-02-20 | Marathon Petroleum Company Lp | Low sulfur fuel oil blends for stability enhancement and associated methods |
| US11920096B2 (en) | 2020-02-19 | 2024-03-05 | Marathon Petroleum Company Lp | Low sulfur fuel oil blends for paraffinic resid stability and associated methods |
| US12031676B2 (en) | 2020-03-24 | 2024-07-09 | Marathon Petroleum Company Lp | Insulation securement system and associated methods |
| US11860069B2 (en) | 2021-02-25 | 2024-01-02 | Marathon Petroleum Company Lp | Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers |
| US11885739B2 (en) | 2021-02-25 | 2024-01-30 | Marathon Petroleum Company Lp | Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers |
| US11898109B2 (en) | 2021-02-25 | 2024-02-13 | Marathon Petroleum Company Lp | Assemblies and methods for enhancing control of hydrotreating and fluid catalytic cracking (FCC) processes using spectroscopic analyzers |
| US11905468B2 (en) | 2021-02-25 | 2024-02-20 | Marathon Petroleum Company Lp | Assemblies and methods for enhancing control of fluid catalytic cracking (FCC) processes using spectroscopic analyzers |
| US11906423B2 (en) | 2021-02-25 | 2024-02-20 | Marathon Petroleum Company Lp | Methods, assemblies, and controllers for determining and using standardized spectral responses for calibration of spectroscopic analyzers |
| US11921035B2 (en) | 2021-02-25 | 2024-03-05 | Marathon Petroleum Company Lp | Methods and assemblies for determining and using standardized spectral responses for calibration of spectroscopic analyzers |
| US11970664B2 (en) | 2021-10-10 | 2024-04-30 | Marathon Petroleum Company Lp | Methods and systems for enhancing processing of hydrocarbons in a fluid catalytic cracking unit using a renewable additive |
| US11802257B2 (en) | 2022-01-31 | 2023-10-31 | Marathon Petroleum Company Lp | Systems and methods for reducing rendered fats pour point |
| US12031094B2 (en) | 2023-06-22 | 2024-07-09 | Marathon Petroleum Company Lp | Assemblies and methods for enhancing fluid catalytic cracking (FCC) processes during the FCC process using spectroscopic analyzers |
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