Gas turbine control system

• US 6,945,030 B2
• Filed: 05/20/2003
• Issued: 09/20/2005
• Est. Priority Date: 05/20/2002
• Status: Expired due to Fees

• Current Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Original Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Inventors: Mizuno, Takashi, Katauri, Tomoo, Ootsuki, Yasuhiko, Hirayama, Kaiichirou
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US10/441,106
• Publication Number:
  US 20040055273A1
• Time in Patent Office: 854 Days
• Field of Search: 60/390.91, 60/392.81, 60/392.7
• US Class Current: 60/39.27
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F02C 9/32 characterised by throttling of fuel F02C9/38 takes precedence
• CPC Class Codes: F02C 9/54 by throttling the working fluid, by adjusting vanes
• CPC Class Codes: F05D 2270/024 to keep rotational speed constant
• CPC Class Codes: F05D 2270/042 by keeping it below damagingly high values
• CPC Class Codes: F05D 2270/06 to match engine to driven device
• CPC Class Codes: F05D 2270/061 in particular the electrical frequency of driven generator
• CPC Class Codes: F05D 2270/091 in particular sudden load loss
• CPC Class Codes: F05D 2270/095 by temporary overriding set control limits
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: F05D 2270/304 Spool rotational speed
• CPC Class Codes: F05D 2270/42 passive or reactive, e.g. using large wind vanes
• CPC Class Codes: G05B 23/0291 Switching into safety or degraded mode, e.g. protection and supervision after failure
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine control system is disclosed which operates to stabilize the system frequency in a case of transitional variations of the system frequency without making the strength of hot gas path parts of the gas turbine below a maximum stress value of the hot gas path parts. When a system frequency abnormality is detected, the output of the gas turbine is adjusted to recover the system frequency by making a gas turbine combustion gas temperature control inoperative. For this purpose, there are provided a logical circuit operative to make the gas turbine combustion gas temperature control disabled or inoperative in response to an abnormal system frequency detection signal, and a recovery circuit that operates to cancel the inoperative state of the gas turbine combustion gas temperature control. The detection of an abnormal system frequency may be carried out by an outside signal. An abnormality detection unit may be provided in a combined cycle plant.

Claims

1. A gas turbine control system for controlling a gas turbine unit including an air compressor for producing compressed air, said compressor having inlet guide vanes or blades for adjusting an air flow rate into the compressor, a combustor for combusting a fuel mixed with the compressed air from the compressor to produce a combustion gas, a gas turbine receiving the combustion gas from the combustor and driven by the combustion gas to drive the compressor;

and an electric generator connected to an electric power system;

said gas turbine control system comprising;

inlet guide blade control means that controls the inlet guide vanes or blades to change the air flow rate into the compressor;

a fuel control valve provided to change flow rate of the fuel into the combustor;

speed-load control means including a speed control means and a load control means, said speed-load control means operating on said fuel control valve to control the flow rate of the fuel so that the gas turbine has a rotational speed coinciding with a set speed value;

normal combustion gas temperature control means that controls the flow rate of the fuel so that the combustion gas temperature does not exceed a normal combustion gas temperature limit value;

emergency combustion gas temperature control means that controls the flow rate of the fuel so that the combustion gas temperature does not exceed an emergency combustion gas temperature limit value; and

a system frequency abnormality sensor that operates to detect such a variation of frequency of the electric power system as to cause the power system to go out of normal operation;

switching means that operates in response to operation of said system frequency abnormality sensor to make said normal combustion gas temperature control means inoperative and make said emergency combustion gas temperature control means operative, whereby output of the gas turbine is controlled to stabilize a system frequency.

2. The gas turbine control system according to claim 1, wherein said normal combustion gas temperature control means includes means for comparing a detected turbine exhaust gas temperature with a normal exhaust gas temperature limit value determined as a function of a ratio of a compressor inlet air pressure to a compressor outlet air pressure, to output a signal for controlling the flow rate of the fuel to consequently prevent the combustion gas temperature from exceeding the normal combustion gas temperature limit value, and said emergency combustion gas temperature control means includes means for comparing the turbine exhaust gas temperature with an emergency exhaust gas temperature limit value determined as a function of a ratio of a compressor inlet air pressure to a compressor outlet air pressure, to output a signal for controlling the flow rate of the fuel to consequently prevent the combustion gas temperature from exceeding the emergency combustion gas temperature limit value.

3. The gas turbine control system according to claim 1, wherein said normal combustion gas temperature control means includes means for comparing a detected combustion gas temperature with a normal combustion gas temperature limit value, to output a signal for controlling the flow rate of the fuel so as to prevent the combustion gas temperature from exceeding the normal combustion gas temperature limit value, and said emergency combustion gas temperature control means includes means for comparing the combustion gas temperature with an emergency combustion gas temperature limit value, to output a signal for controlling the flow rate of the fuel so as to prevent the combustion gas temperature from exceeding the emergency combustion gas temperature limit value.

4. The gas turbine control system according to claim 1, wherein said normal combustion gas temperature control means includes an arithmetic unit that receives as inputs thereto a compressor air flow rate, a compressor outlet air temperature and the fuel flow rate to calculate and output a combustion gas temperature, said normal combustion gas temperature control means further including means for controlling the flow rate of the fuel to the combustor so as to prevent the combustion gas temperature from exceeding a normal combustion gas temperature limit value, and wherein said emergency combustion gas temperature control means includes an arithmetic unit that receives as inputs thereto the compressor air flow rate, the compressor outlet air temperature and the fuel flow rate to calculate and output the combustion gas temperature, said emergency combustion gas temperature control means further including means for controlling the flow rate of the fuel to the combustor so as to prevent the combustion gas temperature from exceeding an emergency combustion gas temperature limit value.

5. The gas turbine control system according to claim 1, wherein said normal combustion gas temperature control means has the normal combustion gas temperature limit value which is a combustion gas temperature at which a sum of the fuel cost and hot gas path parts replacement cost takes a minimum value when the gas turbine is operated for a long term.

6. The gas turbine control system according to claim 1, wherein said emergency combustion gas temperature control means has the emergency combustion gas temperature limit value which is a temperature selected from any one or a smallest one of Ta, Tb, Tc and Td, where Ta is a combustion gas upper limit value determined on the basis of a short-term allowable creep strength of a material of hot gas path parts used in the gas turbine, Tb is a combustion gas upper limit value determined on the basis of an allowable yield strength of the hot gas path parts, Tc is a combustion gas upper limit value corresponding to an allowable upper limit temperature value of a heat-resistant coating on the hot gas path parts, and Td is a combustion gas upper limit value determined on the basis of a surging limit of the compressor.

7. The gas turbine control system according to claim 1, wherein said switching means has means to make said normal combustion gas temperature control means inoperative and make said emergency combustion gas temperature control means operative for a length of time within which the system frequency is expected to recover.