SYSTEMS AND METHODS FOR STARTING A GAS TURBINE ENGINE

An operating method is provided during which a plurality of start parameters for a gas turbine engine are determined (402). A first of the start parameters is indicative of a temperature of air at an inlet into the gas turbine engine. A second of the start parameters is indicative of a pressure of the air at the inlet. Rotation of a rotating assembly of the gas turbine engine (22) is driven (404). The rotating assembly includes a compressor rotor and a turbine rotor. Fuel is directed (408) into a combustion chamber of the gas turbine engine based on the start parameters and a speed parameter. The speed parameter is indicative of a speed of the rotation of the rotating assembly. A mixture of the fuel and compressed air within the combustion chamber is ignited (410) to start the gas turbine engine.