US 11,859,555 B2
Systems and methods for starting a gas turbine engine
Jasmin Turcotte, Mont-Saint-Hilaire (CA); and Ioan Sabau, Montréal (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jan. 12, 2023, as Appl. No. 18/096,140.
Application 18/096,140 is a continuation of application No. 16/576,031, filed on Sep. 19, 2019, granted, now 11,578,661.
Prior Publication US 2023/0143279 A1, May 11, 2023
Int. Cl. F02C 7/26 (2006.01); F02C 9/26 (2006.01)
CPC F02C 7/26 (2013.01) [F02C 9/26 (2013.01); F05D 2260/85 (2013.01); F05D 2260/99 (2013.01); F05D 2270/70 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An adaptive method for starting an aircraft gas turbine engine based on operating parameters of the gas turbine engine, the method comprising:
setting a fuel flow rate and an ignition frequency based on the operating parameters of the gas turbine engine;
in a first phase of a startup causing light-up, upon receipt of a start request:
providing fuel to a combustor of the gas turbine engine according to the fuel flow rate;
driving an ignitor system of the gas turbine engine according to the ignition frequency when fuel is provided to the combustor; and
when light-up is not detected, increasing the fuel flow rate of the fuel being provided to the combustor based on the operating parameters of the gas turbine engine;
in a second phase of the startup causing light-around, driving the ignitor system when providing fuel to the combustor of the gas turbine engine; and
in a third phase of the startup causing a flame to propagate around the combustor of the gas turbine engine, transitioning a fuel divider valve to change a fuel flow distribution between different fuel nozzles associated with the combustor while keeping the fuel flow rate to the combustor constant, the transitioning of the fuel divider valve being based on the operating parameters of the gas turbine engine.