THE CALCULATING OF THE TRANSIENT TEMPERATURE FIELD OF THE FIRST STAGE SEGMENT RING OF A GAS TURBINE

Abstract

In this paper, a rapid method for calculating the transient temperature of the hot components of gas turbines is presented, which contains the following steps: 1. The key factors affecting the heat transfer boundary conditions of the hot component are analyzed, and then link these key factors to gas turbine operation parameters, such as: compressor inlet mass flow, compressor exhaust pressure, turbine inlet gas temperature, etc.. 2. Obtain the gas turbine operation parameters mentioned above at each transient time step. 3. Based on dimensionless criterion number analysis, the external and internal heat transfer boundary conditions of the component at each transient time step are obtained by scaling those at the design point. 4. Load the external and internal heat transfer boundary conditions to the component , and solve the conduction heat transfer at each time step with a commercial CFD code. Using the method above, the transient temperature fields of the first stage segment ring of a gas turbine during a cold state start-load-stop process is calculated. The whole process shows that the transient temperature calculation method is easy to use with the computational cost bearable.