Stabilizing a gas turbine engine via incremental tuning during transients

• US 9,927,818 B2
• Filed: 03/14/2014
• Issued: 03/27/2018
• Est. Priority Date: 05/24/2010
• Status: Active Grant

• Current Assignee: H2 IP UK Limited
• Original Assignee: Ansaldo Energia IP UK Limited (Ansaldo Energia SPA)
• Inventors: Rizkalla, Hany, Gauthier, Donald, Soni, Sumit, Stuttaford, Peter John
• Primary Examiner(s): Besler, Christopher
• Application Number:
  US14/213,122
• Publication Number:
  US 20140200721A1
• Time in Patent Office: 1,474 Days
• CPC Class Codes: F02C 7/228 Dividing fuel between various burners
• 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 9/34 Joint control of separate flows to main and auxiliary burners
• CPC Class Codes: F05D 2270/082 with as little NOx as possible
• CPC Class Codes: F05D 2270/301 Pressure
• CPC Class Codes: F05D 2270/31 Fuel schedule for stage combustors
• CPC Class Codes: F23N 2241/20 Gas turbines
• CPC Class Codes: F23R 3/343 Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00
• CPC Class Codes: F23R 3/346 for staged combustion
• CPC Class Codes: G05D 7/0676 by action on flow sources G05D7/0688, G05D7/0694 take precedence

Abstract

Methods and systems are provided for automatically tuning a combustor of a gas turbine engine during a transient period, such as when a state of the gas turbine engine is changing. Once it has been determined whether the state of the gas turbine engine is changing, it is then determined whether a lean blowout is imminent, which is based conditions being monitored. A stability bias is applied to the system if either the state is changing or if lean blowout is imminent until the lean blowout is no longer determined to be imminent. The stability bias monitors operating conditions of the gas turbine engine and determines when one of the operating conditions has overcome a threshold value. Once a threshold value is overcome, a fuel flow fraction is adjusted by a predefined increment. The application of the stability bias is gradually terminated once it is determined that the lean blowout is no longer imminent.

Claims

1. A method of operating a system for automatically stabilizing combustor dynamics or emissions of a gas turbine engine by employing a tuning process during transients, the method of operating the system comprising:

providing a gas turbine engine including one or more combustors that are each provided with a fuel flow fraction for governing a portion of a total fuel flow that is directed to each fuel nozzle of the combustor'"'"'s fuel circuit; and

carrying out a tuning process comprising;

(a) determining, with an auto-tune controller, that a load of the gas turbine engine is changing from a steady state to an unsteady state,

(b) determining, with the auto-tune controller, that a lean blowout parameter overcomes a predetermined threshold value, and

(c) applying, using the auto-tune controller, a stability bias to the gas turbine engine in response to determining that the lean blowout parameter overcomes the predetermined threshold value, the stability bias comprising adjusting the fuel flow fraction based on the lean blowout parameter overcoming the predetermined threshold value.

2. The method of claim 1, wherein the lean blowout parameter includes one or more of a lean blowout dynamics amplitude, a ratio of a lean blowout dynamics amplitude to a hot tones dynamics amplitude, or a cold tones dynamics amplitude.

3. The method of claim 1, further comprising:

accessing a schedule to select an appropriate fuel flow fraction to alter; and

selecting a first fuel flow fraction to alter upon inspecting the schedule.

4. The method of claim 3, wherein the tuning process further comprises:

utilizing the schedule to determine an incremental amount to adjust the first fuel flow fraction; and

utilizing the schedule to determine a direction in which to make the adjustment to the first fuel flow fraction.

5. The method of claim 4, wherein the tuning process further comprises:

upon making the adjustment to the first fuel flow fraction, determining a number of adjustments recursively made to first fuel flow fraction; and

when the number of recursive adjustments reaches an allowable number of iterations, taking an action prescribed by the schedule.

6. The method of claim 5, wherein the action prescribed by the schedule includes at least one of adjusting a second fuel flow fraction, alerting an operator, adjusting a fuel gas temperature, or adjusting a firing temperature.