Session: 37-05 Whole Engine, Through-flow and Mean-line

Paper Number: 82229

82229 - New Method for Cycle Performance Prediction Based on Detailed Compressor and Gas Turbine Flow Calculations 

Gas turbines have made significant progress in the last period. The efficiency of the compressor and turbine was improved based on achievements of aerodynamics, i.e., on the introduction of numerical flow simulation. The introduction of the massive cooling and thermal barrier coating enables a considerable increase in the turbine inlet temperature. These developments lead to a significant increase in the gas turbine thermal efficiency. However, most of the existing tools for predicting the cycle performances are based on 0D compressor and turbine maps for efficiency and pressure ratio as a function of the mass flow. Such tools are not able to simulate all new trends in gas turbines in the best way. The new method proposed here is based on detailed flow calculation in the compressor and the gas turbine. Earlier developed throughflow tools for 2D compressor/turbine flow simulation and performance prediction were applied for this purpose. The processes in the compressor and the turbine are connected by calculation of the processes in the combustion chamber and in the cooling air system. The turbine inlet temperature is determined in an iterative procedure. The method enables accurate prediction performances at every operating point. Air cooling bleeds in the compressor, and its injections in the turbine blades could be simulated in an exact way. Also, adjustments of IGV and stator vanes and their influence on compressor behavior could be accurately taken into regard at every operating point. Finally, calculation of the combustion and the flow in the compressor and the turbine allows a simulation with correct gas composition and humidity of the air. The method is demonstrated in a case of an industrial gas turbine. The numerical results were compared with experimental results showing a very good agreement. The procedure is quick and robust, enabling optimization of the different solutions during the design phase.

Presenting Author: Milan Petrovic University of Belgrade

Presenting Author Biography: Milan Petrovic received his Dipl. Ing. degree from the University of Belgrade and Ph.D. from the University of Hanover, Germany, in 1995. He is professor of Thermal Turbomachinery and head of the Laboratory of Thermal Turbomachinery at the University of Belgrade.

Authors:

Milan Petrovic University of Belgrade
Alexander Wiedermann MAN Energy Solutions SE
Milan B Banjac University of Belgrade - Fac of Mech Eng
Srdjan Milic University of Belgrade - Fac of Mech Eng
Djordje Petkovic University of Belgrade - Fac of Mech Eng
Teodora Madzar University of Belgrade - Fac of Mech Eng