Fuel supply apparatus for gas turbine and control unit for the same

• US 5,899,073 A
• Filed: 12/24/1996
• Issued: 05/04/1999
• Est. Priority Date: 12/26/1995
• Status: Expired due to Fees

• Current Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Original Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Inventors: Akimaru, Satoru
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US08/773,321
• Time in Patent Office: 861 Days
• Field of Search: 60/39.091, 60/734, 60/736, 60/39.465
• US Class Current: 60/736
• CPC Class Codes: F02C 3/22 the fuel or oxidant being gaseous at standard temperature and pressure F02C3/28 takes precedence
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: F02C 9/42 specially adapted for the control of two or more plants simultaneously

Abstract

A fuel supply apparatus for a gas turbine comprises a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors, a heater provided for the fuel supply system for heating the fuel, a pressure reducing valve for reducing a pressure of the fuel, which has been heated, according to a required fuel pressure of a gas turbine, and a surge tank absorbing a change of the fuel pressure after the pressure reduction. A fuel supply control unit for a gas turbine comprises a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors, a heater provided for the fuel supply system for heating the fuel, a pressure reducing valve and a gas turbine combustor inlet fuel cutoff valve disposed downstream of the heater, and a pressure reducing valve controller which detects an inlet fuel pressure of the gas turbine combustor inlet fuel cutoff valve and applies a pressure reduction control signal to the pressure reducing valve if a detected pressure is higher than a required fuel pressure of the gas turbine.

Claims

1. A fuel supply apparatus for a gas turbine, comprising:

a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors;

a heater provided for the fuel supply system for heating the fuel;

a pressure reducing means for reducing a pressure of the fuel, which has been heated, according to a required fuel pressure of a gas turbine; and

a surge tank disposed between said pressure reducing means and a gas turbine for absorbing a change of the fuel pressure after the pressure reduction.

2. A fuel supply apparatus for a gas turbine according to claim 1, wherein said pressure reducing means comprises at least either one or more of pressure reducing valves and orifices.

3. A fuel supply apparatus of a gas turbine according to claim 2, wherein said pressure reducing valves are divided into a large pressure reducing valve and a small pressure reducing valve, which are disposed in parallel to each other.

4. A fuel supply apparatus according to claim 2, wherein said orifices are divided into a large diameter orifice and a small diameter orifice, which are disposed in parallel to each other.

5. A fuel supply apparatus for a gas turbine comprising:

a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors;

a heater provided for the fuel supply system for heating the fuel;

a heating medium supply system provided for the heater for supplying a heating medium serving as a heating source for the fuel;

a vent system provided for the heater for releasing a noncondensable gas, which is generated during the heating of the fuel, out of the heater; and

a drain system provided for the heater for discharging a liquid, which is generated during the heating of the fuel, out of the heater.

6. A fuel supply apparatus for a gas turbine according to claim 5, wherein said heating medium supplied to the heater is either one of steam and hot water.

7. A fuel supply apparatus for a gas turbine comprising:

a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors;

a heater provided for the fuel supply system for heating the fuel; and

an inert gas supply system for supplying an inert gas to the heater while the heater is in a non-operational mode.

8. A fuel supply apparatus for a gas turbine according to claim 7, wherein said inert gas is either one of nitrogen gas and argon gas.

9. A fuel supply apparatus for a gas turbine, comprising:

a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors;

a heater provided for the fuel supply system for heating the fuel;

a pressure reducing means for reducing a pressure of the fuel, which has been heated, according to a required fuel pressure of a gas turbine; and

a surge tank absorbing a change of the fuel pressure after the pressure reduction,

wherein said pressure reducing means comprises at least either one or more of pressure reducing valves and orifices, and

wherein said pressure reducing valves are divided into a large pressure reducing valve and a small pressure reducing valve, which are disposed in parallel to each other.

10. A fuel supply apparatus for a gas turbine comprising:

a fuel supply system for sending fuel in a fuel reservoir to a plurality of gas turbine combustors;

a heater provided for the fuel supply system for heating the fuel;

a pressure reducing means for reducing a pressure of the fuel, which has been heated, according to a required fuel pressure of a gas turbine; and

a surge tank absorbing a change of the fuel pressure after the pressure reduction,

wherein said pressure reducing means comprises at least either one or more of pressure reducing valves and orifices, and

wherein said orifices are divided into a large diameter orifice and a small diameter orifice, which are disposed in parallel to each other.