JPS63123737U - - Google Patents
Info
- Publication number
- JPS63123737U JPS63123737U JP1586687U JP1586687U JPS63123737U JP S63123737 U JPS63123737 U JP S63123737U JP 1586687 U JP1586687 U JP 1586687U JP 1586687 U JP1586687 U JP 1586687U JP S63123737 U JPS63123737 U JP S63123737U
- Authority
- JP
- Japan
- Prior art keywords
- flow rate
- outputting
- deceleration
- bypass
- signal
- 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
- 239000000446 fuel Substances 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 230000007423 decrease Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 11
- 230000001105 regulatory effect Effects 0.000 description 2
Landscapes
- Engine Equipment That Uses Special Cycles (AREA)
Description
第１図はこの考案の概念構成図、第２図はこの
考案の第１実施例のガスタービンの系統図、第３
図はこの実施例の制御系の系統図、第４図、第５
図はこの実施例に使用される係数ＫＢＶ１，ＫＢ
Ｖ２の内容を示す線図、第６図はこの考案の第２
実施例の流れ図、第７図はこの考案の第３実施例
のガスタービンの系統図である。第８図と第９図
はそれぞれ減速時以外の運転時と減速時における
ノズルの作動状態を示すこの考案の第４実施例の
断面図、第１０図と第１１図はそれぞれ減速時以
外の運転時と減速時における環状部材の作動状態
を示すこの考案の第５実施例の一部断面平面図、
第１２図は第１０図の断面側面図である。第１３
図は従来例のガスタービンの系統図、第１４図は
従来例の制御系の系統図、第１５図はコンプレツ
サの圧力比特性を示す線図である。
１……ガスジエネレータ、２……コンプレツサ
、２Ａ……空気吐出部、３……コンプレツサター
ビン、４……燃焼器、５……燃料噴射弁、６……
パワータービン、７……負荷、８……熱交換器、
８Ａ……高圧側入口部、８Ｂ……低圧側入口部、
９……バリアブルノズル、１２……アクセルペダ
ル、１４……回転センサ、１８，１９……アクチ
ユエータ、２２……主路、２４……バイパス路、
２５……第１の調整弁、２６……アクチユエータ
、３３……関数器、４１……ガスジエネレータ回
転数設定手段、４２……燃料流量制御手段、４３
……バイパス路、４４……第１の機構、４５……
主路、４６……第２の機構、４７……減速度演算
手段、４８……バイパス流量制御手段、４９……
主流量制御手段、６１……主路、６２……第２の
調整弁、６３……アクチユエータ、６５……コン
トロールユニツト、６６……関数器、８１……ガ
スジエネレータ回転軸、８２……パワータービン
回転軸、８３……パワートランスフアー機構、９
１……管路、９２……主路、９３……分岐路、９
４……ノズル、１０３……デイフユーザ流路、１
０５……環状部材、１０６……放射状流路、１０
８……溝、１０９……孔、１１０……管路、１１
１ないし１１３……ギヤ、１１４……アクチユエ
ータ。
Fig. 1 is a conceptual configuration diagram of this invention, Fig. 2 is a system diagram of a gas turbine according to the first embodiment of this invention, and Fig. 3 is a system diagram of a gas turbine according to the first embodiment of this invention.
The diagrams are system diagrams of the control system of this embodiment, Figures 4 and 5.
The figure shows the coefficients KBV 1 and KB used in this example.
A diagram showing the contents of V2 , Figure 6 is the second diagram of this invention.
Flowchart of the Embodiment FIG. 7 is a system diagram of a gas turbine according to the third embodiment of this invention. Figures 8 and 9 are cross-sectional views of the fourth embodiment of this invention showing the operating states of the nozzle during operation other than deceleration and during deceleration, respectively, and Figures 10 and 11 are respectively sectional views of the nozzle during operation other than deceleration. A partially sectional plan view of the fifth embodiment of the invention showing the operating state of the annular member during time and deceleration;
FIG. 12 is a cross-sectional side view of FIG. 10. 13th
14 is a system diagram of a conventional gas turbine, FIG. 14 is a system diagram of a conventional control system, and FIG. 15 is a diagram showing pressure ratio characteristics of a compressor. DESCRIPTION OF SYMBOLS 1... Gas generator, 2... Compressor, 2A... Air discharge part, 3... Compressor turbine, 4... Combustor, 5... Fuel injection valve, 6...
Power turbine, 7...load, 8...heat exchanger,
8A...High pressure side inlet section, 8B...Low pressure side inlet section,
9... Variable nozzle, 12... Accelerator pedal, 14... Rotation sensor, 18, 19... Actuator, 22... Main path, 24... Bypass path,
25... First regulating valve, 26... Actuator, 33... Function device, 41... Gas generator rotation speed setting means, 42... Fuel flow rate control means, 43
...Bypass path, 44...First mechanism, 45...
Main path, 46... Second mechanism, 47... Deceleration calculation means, 48... Bypass flow rate control means, 49...
Main flow control means, 61...Main path, 62...Second regulating valve, 63...Actuator, 65...Control unit, 66...Function unit, 81...Gas generator rotation shaft, 82...Power turbine rotation Shaft, 83... Power transfer mechanism, 9
1...pipeline, 92...main route, 93...branch route, 9
4... Nozzle, 103... Diffuser flow path, 1
05... Annular member, 106... Radial flow path, 10
8...groove, 109...hole, 110...pipeline, 11
1 to 113...gear, 114...actuator.
Claims (1)
設定する手段と、設定された回転数に応じて燃料
噴射弁からの燃料流量を制御する信号を出力する
手段とを備える２軸ガスタービンの減速制御装置
において、コンプレツサの空気吐出部と熱交換器
の低圧側入口部とを連通するバイパス路と、この
バイパス路に介装されバイパス流量を調節する第
１の機構と、前記コンプレツサの空気吐出部と熱
交換器の高圧側入口部とを連通する主路に介装さ
れ主流量を調節する第２の機構と、減速度を演算
する手段と、演算された減速度が大きいほど前記
バイパス流量を増加させる制御信号を前記第１の
機構に出力する手段と、同じく演算された減速度
が大きいほど前記主流量を減少させる制御信号を
前記第２の機構に出力する手段とを設けたことを
特徴とする２軸ガスタービンの減速制御装置。 A deceleration control device for a two-shaft gas turbine, comprising means for setting the rotation speed of a gas generator according to operating conditions, and means for outputting a signal for controlling the fuel flow rate from a fuel injection valve according to the set rotation speed. , a bypass passage that communicates the air discharge part of the compressor with the low-pressure side inlet part of the heat exchanger; a first mechanism that is interposed in the bypass passage and adjusts the bypass flow rate; and a heat exchanger with the air discharge part of the compressor. a second mechanism interposed in the main passage communicating with the high-pressure side inlet of the vessel and adjusting the main flow rate; means for calculating deceleration; and control for increasing the bypass flow rate as the calculated deceleration increases. 2, characterized in that it is provided with means for outputting a signal to the first mechanism, and means for outputting a control signal to the second mechanism that decreases the main flow rate as the calculated deceleration increases. Axial gas turbine reduction control device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1586687U JPS63123737U (en) | 1987-02-05 | 1987-02-05 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1586687U JPS63123737U (en) | 1987-02-05 | 1987-02-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63123737U true JPS63123737U (en) | 1988-08-11 |
Family
ID=30807194
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1586687U Pending JPS63123737U (en) | 1987-02-05 | 1987-02-05 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63123737U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITCO20100023A1 (en) * | 2010-04-30 | 2011-10-31 | Nuovo Pignone Spa | METHOD AND SYSTEM FOR THE DETECTION OF LOCKED NOZZLE AND REMEDY |
-
1987
- 1987-02-05 JP JP1586687U patent/JPS63123737U/ja active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITCO20100023A1 (en) * | 2010-04-30 | 2011-10-31 | Nuovo Pignone Spa | METHOD AND SYSTEM FOR THE DETECTION OF LOCKED NOZZLE AND REMEDY |
| EP2383452A1 (en) * | 2010-04-30 | 2011-11-02 | Nuovo Pignone S.p.A. | Blocked nozzle detection and remedial method and system |
| US8676391B2 (en) | 2010-04-30 | 2014-03-18 | Nuovo Pignone S.P.A. | Blocked nozzle detection and remedial method and system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20030101723A1 (en) | Method for controlling a charge pressure in an internal combustion engine with an exhaust gas turbocharger | |
| EP0037786B1 (en) | Fuel control apparatus | |
| JPS6233071Y2 (en) | ||
| JPH02534B2 (en) | ||
| JPS6060222A (en) | Fuel control system for gas turbine engine | |
| US4422296A (en) | Internal combustion engine with supercharging by exhaust gas turbochargers and an auxiliary combustion chamber | |
| JPS63123737U (en) | ||
| JPS6130142B2 (en) | ||
| JPH02227522A (en) | Supercharging pressure control device | |
| JPS626258Y2 (en) | ||
| US4763474A (en) | Control system for a variable inlet area turbocharger turbine | |
| JP3968710B2 (en) | Intake control and negative pressure generator | |
| JPH0371142U (en) | ||
| JPH066208Y2 (en) | Control device for catalytic combustion type gas turbine | |
| JPS61123718A (en) | Variable nozzle controller for turbosupercharger | |
| JPH0216331A (en) | Turbocharger control device | |
| JPH059463Y2 (en) | ||
| JPH07310561A (en) | Operating method of gas turbine | |
| JPS61185622A (en) | Supercharging pressure controller for turbocharger with variable throat nozzle | |
| JPH0242123A (en) | Control device for engine with supercharger | |
| JPS58170827A (en) | Supercharging device for internal-combustion engine | |
| JPH0435535Y2 (en) | ||
| JPH068741U (en) | Gas engine controller | |
| JPH0341142U (en) | ||
| JPS61228300A (en) | Drive for propeller of underwater sailing body |