Patent ID: 7698897
Filing Date: 2010-04-20
Classification: F02C,F05D

Abstract:
1. An engine control method for a gas turbine engine, the method comprising: operating a gas turbine engine at a first thrust setting demanding a first normal fuel flow and having a first engine operating temperature; increasing the thrust to a second thrust setting and operating the gas turbine engine at a steady state, the second thrust setting demanding a second normal fuel flow and having a second engine operating temperature, the second engine operating temperature being greater than the first engine operating temperature; obtaining at least one engine temperature dependent variable of the engine and using the engine temperature dependent variable to determine a heat soak fuel flow to account for a thermal inertia of raising an operating temperature of the engine from the first operating temperature to the second operating temperature; and adjusting said second normal fuel flow by subtracting the heat soak fuel flow from said second normal fuel flow to reduce a size and duration of overshoot of power or thrust of the engine while operating the engine at the steady state.