JPH0125886B2 - - Google Patents
Info
- Publication number
- JPH0125886B2 JPH0125886B2 JP18533884A JP18533884A JPH0125886B2 JP H0125886 B2 JPH0125886 B2 JP H0125886B2 JP 18533884 A JP18533884 A JP 18533884A JP 18533884 A JP18533884 A JP 18533884A JP H0125886 B2 JPH0125886 B2 JP H0125886B2
- Authority
- JP
- Japan
- Prior art keywords
- differential pressure
- mmaq
- stage stator
- stage
- stator vane
- 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
- 238000012544 monitoring process Methods 0.000 claims description 3
- 239000000428 dust Substances 0.000 description 10
- 150000001875 compounds Chemical class 0.000 description 6
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012806 monitoring device Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/10—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to unwanted deposits on blades, in working-fluid conduits or the like
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
【発明の詳細な説明】
〔発明の技術分野〕
本発明はガスタービン監視装置、特に炉頂圧タ
ービン監視装置に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to a gas turbine monitoring system, and more particularly to a top pressure turbine monitoring system.
一般に、炉頂圧タービンは駆動ガスとして溶鉱
炉で発生するガスを利用するものであり、その回
転力によつて発電機を回転させて溶鉱炉ガスの持
つエネルギーを電力に変換し、そのエネルギーを
有効利用しようとするものである。
Generally, a furnace top pressure turbine uses gas generated in a blast furnace as the driving gas, and the rotational force of the turbine rotates a generator to convert the energy of the blast furnace gas into electricity, making effective use of that energy. This is what I am trying to do.
ところで、上記溶鉱炉ガスは炉頂圧タービンに
導入される前に除塵器によりダストが除去される
が、それでも静翼、特に１段静翼にはダストが付
着して目詰りを生じ、種々のトラブルの原因にな
つている。 Incidentally, although dust is removed from the blast furnace gas by a dust remover before it is introduced into the furnace top pressure turbine, dust still adheres to the stator blades, especially the first stage stator blades, causing clogging, which can cause various troubles. It's getting old.
他方、１段静翼は、その仰角が可変であり、従
来の固定式の場合のように、１段静翼の前後の圧
力差のみではダストの付着量を知ることが困難で
ある。 On the other hand, the angle of elevation of the first-stage stator vane is variable, and it is difficult to know the amount of dust attached only from the pressure difference before and after the first-stage stator vane, as in the case of a conventional fixed type.
そこで、本発明は１段静翼の前後の差圧を定量
的に捕捉することにより１段静翼に付着したダス
トを間接的に検知することを目的とするものであ
る。
Therefore, an object of the present invention is to indirectly detect the dust attached to the first stage stator vane by quantitatively capturing the pressure difference before and after the first stage stator vane.
すなわち、本発明は、
(a) ガスタービンの１段静翼前後の差圧△Pact
（mmAq）を検出し、その差圧を演算器に入力す
る差圧発信器、
(b) １段静翼の迎角ξ（゜）を検出し、その値を
演算器に入力する開度発信器、
(c) ガスタービンに供給されるガス流量Ｑ（Ｎ
m3／Ｈ）を検出し、その値を演算器に入力する
流量発信器、
(d) １段静翼の仰角ξ（゜）及びガス流量Ｑ（Ｎ
m3／Ｈ）から求めた正常差圧△Pcal（mmAq）と
１段静翼前後の実測差圧△Pact（mmAq）との差
を演算する演算器、
(e) １段静翼の仰角ξ（゜）及びガス流量Ｑ（Ｎ
m3／Ｈ）から求めた正常差圧△Pcal（mmAq）と
１段静翼前後の実測差圧△Pact（mmAq）との差
が所定値を超えたときに警報を発する警報器、
とを備えたことを特徴とするものである。
That is, the present invention provides (a) differential pressure △Pact before and after the first stage stationary blade of the gas turbine;
(b) A differential pressure transmitter that detects the angle of attack ξ (°) of the first stage stator vane and inputs that value to the calculator; (c) Gas flow rate Q (N
m 3 /H) and inputs the value to the calculator; (d) the elevation angle ξ (°) of the first stage stator vane and the gas flow rate Q (N
a computing unit that calculates the difference between the normal differential pressure △Pcal (mmAq) obtained from m 3 /H) and the actually measured differential pressure △Pact (mmAq) before and after the first stage stator blade; (e) the elevation angle ξ (°) of the first stage stator vane; Gas flow rate Q (N
m 3 /H) and the actual differential pressure △Pact (mmAq) before and after the first stage stationary blade exceeds a predetermined value. It is characterized by this.
以下、図面を斟酌しながら本発明の一実施例に
ついて説明する。
An embodiment of the present invention will be described below with reference to the drawings.
図は本発明にかかるガスタービン監視装置の系
統図であり、図示しない溶鉱炉で生成したガスは
除塵器（図示せず）で大部分のダストが除去され
たあと、ダクト１１を通つてガスタービン１に供
給される。 The figure is a system diagram of a gas turbine monitoring device according to the present invention, in which gas generated in a blast furnace (not shown) is passed through a duct 11 to the gas turbine after most of the dust is removed by a dust remover (not shown). is supplied to
このガスタービン１はタービンケーシング２の
内部に動翼を多段に持つロータ４を回転自在に設
けており、また前記タービンケーシング２は、そ
の内壁面に静翼を多段に設けている。この図で
は、便宜上、１段静翼３と１段動翼５のみを図示
することとする。ここで、符号１０はガス導入口
を示している。 This gas turbine 1 has a rotor 4 rotatably provided inside a turbine casing 2 having rotor blades in multiple stages, and the turbine casing 2 has stationary blades in multiple stages on its inner wall surface. In this figure, for convenience, only the first-stage stationary blade 3 and the first-stage rotor blade 5 are shown. Here, the reference numeral 10 indicates a gas inlet.
前記１段静翼３は当該１段静翼３に固定した軸
６を介して前記タービンケーシング２に回動自在
に取付けられている。そして、１段静翼３の軸６
はリンク機構、或いはラツクとピニオン等の公知
の手段を介して例えば油圧シリンダ等の流体圧シ
リンダ７により回動されるように構成されてい
る。 The first stage stator vane 3 is rotatably attached to the turbine casing 2 via a shaft 6 fixed to the first stage stator vane 3. Then, the shaft 6 of the first stage stationary blade 3
is configured to be rotated by a fluid pressure cylinder 7 such as a hydraulic cylinder via a link mechanism or a known means such as a rack and pinion.
この１段静翼３の仰角ξ（゜）は図示しない角
度検知器に付随する開度発信器３５により複合演
算器６０に入力される。 The elevation angle ξ (°) of the first-stage stationary blade 3 is inputted to the compound calculator 60 by an opening transmitter 35 attached to an angle detector (not shown).
他方、上記ダクト１１には、ガスの供給方向に
見て上流側から順に、流量計１２、緊急遮断弁１
３、及び調速弁１４を設けており、前記流量計１
２により計量したガス流量Ｑ（Ｎm3／Ｈ）は当該
流量計１２に付随する流量発信器１５によつて複
合演算器６０に入力される。 On the other hand, the duct 11 includes a flow meter 12 and an emergency shutoff valve 1 in order from the upstream side when viewed in the gas supply direction.
3, and a regulating valve 14 are provided, and the flow meter 1
The gas flow rate Q (Nm 3 /H) measured by No. 2 is inputted to the compound calculator 60 by the flow rate transmitter 15 attached to the flow meter 12.
更に、１次側圧力検出器２１を上記ダクト１１
内に有し、２次側圧力検出器２２を１段静翼３と
１段動翼５との間に有する差圧検出管２０によつ
て検出した１段静翼３前後の実際の差圧△Pact
（mmAq）は前記差圧検出管２０に付随する差圧発
信器２５により複合演算器６０に入力される。 Furthermore, the primary side pressure detector 21 is connected to the duct 11.
Actual differential pressure △Pact before and after the first stage stator blade 3 detected by a differential pressure detection tube 20 having a secondary side pressure detector 22 between the first stage stator blade 3 and the first stage rotor blade 5.
(mmAq) is inputted to the compound arithmetic unit 60 by the differential pressure transmitter 25 attached to the differential pressure detection tube 20.
上記複合演算器６０は指令によつて、常時、下
記の(1)式を演算し、その演算結果を記録計５０に
記憶させると共に、その結果を保存している。 The compound arithmetic unit 60 always calculates the following equation (1) according to a command, stores the result of the calculation in the recorder 50, and saves the result.
そして、その値が許容差圧Ａ（mmAq）以上のと
きに警報器４０が作動するように構成している。 The alarm 40 is configured to operate when the value is equal to or greater than the allowable differential pressure A (mmAq).
すなわち、
△Pact―△Pcal≧Ａ（mmAq） ……(1)
ここで、許容差圧Ａはガスタービンの機種等に
より決定されるが、100〜2000の範囲が好ましい。 That is, △Pact-△Pcal≧A (mmAq) (1) Here, the allowable differential pressure A is determined depending on the model of the gas turbine, etc., but is preferably in the range of 100 to 2000.
他方、上記正常差圧△Pcal（mmAq）は、予め１
段静翼３にダストが付着しない正常状態のときの
ガス流量Ｑ（Ｎm3／Ｈ）及び１段静翼３の仰角ξ
（゜）のときの値を複合演算器６０に記憶させて
おき、実測時におけるガス流量Ｑ（Ｎm3／Ｈ）及
び１段静翼３の仰角ξ（゜）から直ちに正常差圧
△Pcal（mmｑ）が引き出せるようになつている。 On the other hand, the above normal differential pressure △Pcal (mmAq) is set to 1 in advance.
Gas flow rate Q (Nm 3 /H) and elevation angle ξ of the first stage stator vane 3 in a normal state where no dust adheres to the stage stator vane 3
(°) is stored in the compound calculator 60, and the normal differential pressure △Pcal (mmq) is immediately calculated from the actual gas flow rate Q (Nm 3 /H) and the elevation angle ξ (°) of the first stage stationary blade 3. can now be pulled out.
而して、指令によつて総合演算器６０で上記(1)
式を演算し、その演算結果を記録計５０に記憶さ
せる。そして、実測差圧△Pact（mmAq）と正常差
圧△Pcal（mmAAq）との差がと許容差圧Ａ（mm
Aq）以上になると警報器４０が作動する。 Therefore, according to the command, the general arithmetic unit 60 performs the above (1).
The formula is calculated and the result of the calculation is stored in the recorder 50. Then, the difference between the measured differential pressure △Pact (mmAq) and the normal differential pressure △Pcal (mmAAq) is the allowable differential pressure A (mmAq).
Aq) or higher, the alarm 40 is activated.
このとき、ガスタービン１を停止させて、１段
静翼３等に付着したダストを除去し、しかる後
に、ガスタービン１を再スタートさせる。 At this time, the gas turbine 1 is stopped, dust attached to the first stage stator blades 3, etc. is removed, and then the gas turbine 1 is restarted.
上記のように、本発明は、
(a) ガスタービンの１段静翼前後の差圧△Pact
（mmAq）を検出し、その差圧を演算器に入力す
る差圧発信器、
(b) １段静翼の迎角ξ（゜）を検出し、その値を
演算器に入力する開度発信器、
(c) ガスタービンに供給されるガス流量Ｑ（Ｎ
m3／Ｈ）を検出し、その値を演算器に入力する
流量発信器、
(d) １段静翼の仰角ξ（゜）及びガス流量Ｑ（Ｎ
m3／Ｈ）から求めた正常差圧△Pcal（mmAq）と
１段静翼前後の実測差圧△Pact（mmAq）との差
を演算する演算器、
(e) １段静翼の仰角ξ（゜）及びガス流量Ｑ（Ｎ
m3／Ｈ）から求めた正常差圧△Pcal（mmAq）と
１段静翼前後の実測差圧△Pact（mmAq）との差
が所定値を超えたときに警報を発する警報器、
とを備えたから、定量的に差圧を捉えることが不
可能であつた可変静翼をするガスタービンでも可
変静翼前後の差圧を定量的に捉えることができ、
静翼に付着したダストの量を精度良く把握するこ
とができる。
As described above, the present invention provides (a) differential pressure △Pact before and after the first stage stationary blade of a gas turbine;
(b) A differential pressure transmitter that detects the angle of attack ξ (°) of the first stage stator vane and inputs that value to the calculator; (c) Gas flow rate Q (N
m 3 /H) and inputs the value to the calculator; (d) the elevation angle ξ (°) of the first stage stator vane and the gas flow rate Q (N
a computing unit that calculates the difference between the normal differential pressure △Pcal (mmAq) obtained from m 3 /H) and the actually measured differential pressure △Pact (mmAq) before and after the first stage stator blade; (e) the elevation angle ξ (°) of the first stage stator vane; Gas flow rate Q (N
This is because it is equipped with an alarm that issues an alarm when the difference between the normal differential pressure △Pcal (mmAq) calculated from m 3 /H) and the actually measured differential pressure △Pact (mmAq) before and after the first stage stator vane exceeds a predetermined value. Even in gas turbines with variable stator blades, where it was impossible to quantitatively determine the differential pressure, it is now possible to quantitatively determine the differential pressure before and after the variable stator blades.
It is possible to accurately determine the amount of dust attached to the stationary blades.
以上の説明では、上記(1)式を複合演算器６０で
演算する場合について説明したが、上記(1)式の代
りに下記の(2)式を使用してもよい。 In the above description, the case where the above equation (1) is calculated by the compound arithmetic unit 60 has been explained, but the following equation (2) may be used instead of the above equation (1).
すなわち、 △Pact≧△Pcal（１×α） ……(2) ここで、αは許容係数である。 That is, △Pact≧△Pcal (1×α) ……(2) Here, α is the tolerance coefficient.
図面は本発明にかかるガスタービン監視装置の
系統図である。
１……ガスタービン、３……１段静翼、１５…
…流量発信器、２５……差圧発信器、３５……開
度発信器、４０……警報器、６０……演算器。
The drawing is a system diagram of a gas turbine monitoring device according to the present invention. 1...Gas turbine, 3...1st stage stationary blade, 15...
...Flow rate transmitter, 25...Differential pressure transmitter, 35...Opening degree transmitter, 40...Alarm, 60...Arithmetic unit.
Claims (1)
Pact（mmAq）を検出し、その差圧を演算器に入
力する差圧発信器、 (b) １段静翼の迎角ξ（゜）を検出し、その値を
演算器に入力する開度発信器、 (c) ガスタービンに供給されるガス流量Ｑ（Ｎ
m3／Ｈ）を検出し、その値を演算器に入力する
流量発信器、 (d) １段静翼の仰角ξ（゜）及びガス流量Ｑ（Ｎ
m3／Ｈ）から求めた正常差圧△Pcal（mmAq）と
１段静翼前後の実測差圧△Pact（mmAq）との差
を演算する演算器、 (e) １段静翼の仰角ξ（゜）及びガス量Ｑ（Ｎm3／
Ｈ）から求めた正常差圧△Pcal（mmAq）と１段
静翼前後の実測差圧△Pact（mmAq）との差が所
定値を超えたときに警報を発する警報器、 とを備えたことを特徴とするガスタービン監視装
置。[Claims] 1 (a) Differential pressure △ before and after the first stage stationary blade of a gas turbine
(b) A differential pressure transmitter that detects the Pact (mmAq) and inputs the differential pressure to the calculator. (b) A position transmitter that detects the angle of attack ξ (°) of the first stage stator vane and inputs that value to the calculator. , (c) Gas flow rate Q (N
m 3 /H) and inputs the value to the calculator; (d) the elevation angle ξ (°) of the first stage stator vane and the gas flow rate Q (N
a computing unit that calculates the difference between the normal differential pressure △Pcal (mmAq) obtained from m 3 /H) and the actually measured differential pressure △Pact (mmAq) before and after the first stage stator blade; (e) the elevation angle ξ (°) of the first stage stator vane; Gas amount Q (Nm 3 /
H) and an alarm that issues an alarm when the difference between the normal differential pressure △Pcal (mmAq) obtained from H) and the actually measured differential pressure △Pact (mmAq) before and after the first stage stator vane exceeds a predetermined value. gas turbine monitoring equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP18533884A JPS6165001A (en) | 1984-09-06 | 1984-09-06 | Gas turbine monitoring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP18533884A JPS6165001A (en) | 1984-09-06 | 1984-09-06 | Gas turbine monitoring device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6165001A JPS6165001A (en) | 1986-04-03 |
| JPH0125886B2 true JPH0125886B2 (en) | 1989-05-19 |
Family
ID=16169049
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP18533884A Granted JPS6165001A (en) | 1984-09-06 | 1984-09-06 | Gas turbine monitoring device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6165001A (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101680662B (en) * | 2007-03-30 | 2011-05-18 | 川崎成套设备股份有限公司 | Monitoring device and detection method of rubber-like substance and gas turbine equipment |
| JP5551645B2 (en) * | 2011-03-30 | 2014-07-16 | 三井造船株式会社 | Device for preventing dust from adhering to stationary blades of furnace top pressure recovery turbine |
-
1984
- 1984-09-06 JP JP18533884A patent/JPS6165001A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6165001A (en) | 1986-04-03 |
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