A simplified program to predict the temperature distribution in gas turbine components as a function of the mission profile of the aircraft

Abstract

One of the main thrusts of the modem aerospace industry is to reduce the operating costs of aircraft This requires a longer on-wing time for the gas turbines and subsequently reduced maintenance. Such a program can only be effectively implemented if the effects of operating conditions on the aircraft can be evaluated continuously. This paper presents a simplified computer program, operating on a personal computer, to predict the temperature distribution in components as a function of the operating condition of the aircraft. This information is then used to determine the deterioration of the engine under the specified operating conditions. The program consists of a simplified model to calculate the conditions in the different modules of the engine as a function of parameters like throttle position, altitude, speed of the aircraft etc. The detailed heat transfer to components is calculated using simplified analytical formulations accounting for three-dimensional effects. As a test case, the temperature change on a semi-cooled nozzle guide vane (NGV) is shown as the engine accelerates to full load conditions. It can be concluded that this approach produces realistic values for the thermal loading on components that can be used to predict long-term engine deterioration.