JPH01124338U

JPH01124338U -

Info

Publication number: JPH01124338U
Application number: JP1942988U
Authority: JP
Priority date: 1988-02-17
Filing date: 1988-02-17
Publication date: 1989-08-24

Description

[Brief explanation of drawings]

第１図はこの考案のクレーム対応図、第２図は
この考案の一実施例のガスタービンの系統図、第
３図はこの実施例の燃料制御系のブロツク図、第
４図はこの実施例の制御動作を説明するための流
れ図、第５図はこの実施例のタービン軸回転数に
対する設定軸加速度の特性図、第６図はこの実施
例の作用を説明するための波形図である。第７図
は従来例のガスタービンの系統図、第８図は従来
例の燃料制御系のブロツク図、第９図と第１０図
は従来例の作用を説明するための波形図である。１…コンプレツサ、２…コンプレツサタービン
、３…タービン軸、４…燃焼器、６…スタータ、
１１…タービン軸回転数センサ、１２…コンプレ
ツサ入口圧力センサ、１３…コンプレツサ入口温
度センサ、２１…コントロールユニツト、２２…
軸加速度設定部、２３…微分部、２４…除算部、
２５…引算部、２６…ＰＩＤ制御部、３１…ター
ビン軸回転数センサ、３４…実軸加速度算出手段
、３５…軸加速度設定手段、３６…燃料流量フイ
ードバツク制御手段、３８…タービン入口温度セ
ンサ、３９…着火判定手段、４０…燃料流量制限
手段、４１…設定軸加速度変更手段、６１…着火
判定部、６２…着火燃料流量制限部、６３…設定
軸加速度変更部。 Fig. 1 is a diagram corresponding to claims of this invention, Fig. 2 is a system diagram of a gas turbine according to an embodiment of this invention, Fig. 3 is a block diagram of a fuel control system of this embodiment, and Fig. 4 is a diagram of this embodiment. FIG. 5 is a characteristic diagram of the set shaft acceleration with respect to the turbine shaft rotation speed of this embodiment, and FIG. 6 is a waveform diagram for explaining the operation of this embodiment. FIG. 7 is a system diagram of a conventional gas turbine, FIG. 8 is a block diagram of a conventional fuel control system, and FIGS. 9 and 10 are waveform diagrams for explaining the operation of the conventional gas turbine. 1...Compressor, 2...Compressor turbine, 3...Turbine shaft, 4...Combustor, 6...Starter,
DESCRIPTION OF SYMBOLS 11... Turbine shaft rotation speed sensor, 12... Compressor inlet pressure sensor, 13... Compressor inlet temperature sensor, 21... Control unit, 22...
Axial acceleration setting section, 23...differentiation section, 24...division section,
25...Subtraction unit, 26...PID control unit, 31...Turbine shaft rotation speed sensor, 34...Actual shaft acceleration calculation means, 35...Shaft acceleration setting means, 36...Fuel flow rate feedback control means, 38...Turbine inlet temperature sensor, 39... Ignition determining means, 40... Fuel flow rate limiting means, 41... Setting axis acceleration changing means, 61... Ignition determining section, 62... Ignition fuel flow rate limiting section, 63... Setting axis acceleration changing section.

Claims

[Scope of utility model registration request]

a sensor for detecting the turbine shaft rotation speed; a means for calculating an actual turbine shaft acceleration from the detected turbine shaft rotation speed; and a means for presetting an optimal turbine shaft acceleration for the turbine shaft rotation speed;
A sensor for detecting a turbine inlet temperature in a gas turbine startup control device comprising means for determining a fuel flow rate instruction value by increasing or decreasing a fuel flow rate so that the actual axial acceleration matches a set axial acceleration; means for determining whether ignition has occurred based on the detected turbine inlet temperature; means for limiting the fuel flow rate instruction value to a certain value or less from the start of fuel injection until it is determined that ignition has occurred; 1. A gas turbine startup control device, comprising: means for changing the set shaft acceleration according to an actual shaft acceleration.