Gas turbine engine controls for minimizing combustion dynamics and emissions

• US 8,504,276 B2
• Filed: 02/28/2008
• Issued: 08/06/2013
• Est. Priority Date: 02/28/2008
• Status: Active Grant

• Current Assignee: Ansaldo Energia Switzerland AG (Ansaldo Energia SPA)
• Original Assignee: Power Systems Mfg. LLC (Hanwha Corporation)
• Inventors: Martling, Vincent C., So, Peter, Xiao, Zhenhua, Ricklin, Plazi
• Primary Examiner(s): Dager, Jonathan M
• Application Number:
  US12/039,183
• Publication Number:
  US 20090222187A1
• Time in Patent Office: 1,986 Days
• Field of Search: 73112-114, 700286-297, 701 99-110
• US Class Current: 701/100
• 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 2270/303 Temperature
• CPC Class Codes: F05D 2270/708 with comparison tables
• CPC Class Codes: F23N 2241/20 Gas turbines

Abstract

Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.

Claims

1. A method of controlling a gas turbine engine having a compressor, at least one combustor, a turbine, and a control system comprising:

measuring a compressor inlet temperature;

calculating a turbine reference temperature as a function of at least compressor discharge pressure, exhaust pressure, and pressure across the combustor;

selecting a baseline fuel schedule for a fuel circuit corresponding to the turbine reference temperature;

determining whether a baseline fuel split corresponds to the turbine reference temperature;

determining a bias parameter so as to increase or decrease the baseline fuel split wherein the bias parameter is a percentage change in fuel split that varies as a function of the measured compressor inlet temperature for a given turbine reference temperature; and

,

adjusting the fuel flow for the fuel circuit to a sum of the baseline fuel split and the bias parameter.

2. The method of claim 1, further comprising the step of interpolating the baseline fuel split from two known fuel splits associated with two known turbine reference temperatures listed in the baseline fuel schedule if the calculated turbine reference temperature is not listed in the baseline fuel schedule.

3. The method of claim 1, further comprising the step of interpolating the bias parameter from two known compressor inlet temperatures.

4. The method of claim 1, wherein the bias parameter varies for each turbine reference temperature.

5. The method of claim 1, wherein the combustor has fuel splits determined for four fuel circuits.

6. The method of claim 1, wherein the bias parameter results in an increase, a decrease, or no change to the fuel split.

7. A gas turbine engine comprising:

an inlet;

a compressor;

at least one combustor having at least two fuel circuits;

a turbine; and

,

a control system having a processor and a memory component containing a series of computer-readable instructions that measures a compressor inlet temperature in real-time and calculates a turbine reference temperature that is a function of at least compressor discharge pressure, exhaust pressure and pressure across the combustor, wherein the compressor inlet temperature and turbine reference temperature are utilized to identify a fuel split for each fuel circuit of the combustor with each fuel split biased higher or lower based on measured compressor inlet temperature.

8. The gas turbine engine of claim 7, wherein the fuel split is a percentage of an available fuel balance.

9. The gas turbine engine of claim 7, wherein the computer-readable instructions consult look-up tables and interpolate between listed values in order to identify an optimal fuel split for a given compressor inlet temperature and turbine reference temperature.