A Quick Method for Full Flange-to-flange Industrial Gas Turbine Analysis Based on Through-flow Modelling

Abstract

In this paper flow field calculations for an entire two shaft industrial gas turbine will be described. This method is based on individual through flow codes for axial compressors and air-cooled expansion turbines developed by the authors which are automatically coupled using simple combustion and secondary flow models connecting compressor and turbine flow paths. With this approach the complete quasi 3-D flow field from compressor inlet to turbine exit can be solved simultaneously (flange-to-flange). Details are explained in this paper. The through-flow computation for the analysis of cooled axial multistage turbines is fed by air from the compressor bleeds which are part of the through flow model of the compressor. The through-flow methods are based on a stream function approach and a finite element solution procedure. They include high-fidelity loss and deviation models with improved correlations. Advanced radial mixing and endwall boundary layer models are applied to simulate 3-D flow effects. For air-cooled turbine analysis, various types of cooling air injection were encompassed: film cooling, trailing edge injection and disc/endwall coolant flow. Compressor and turbine flow path computations were extensively validated individually and published by the authors. Predicted gas turbine operating points of MAN's MGT-gas turbine will be compared with results of the 3-D Navier-Stokes solver TBLOCK which was run for both compressor and turbines individually using the boundary conditions derived from the present analysis. The focus is on the comparison of mean data and radial distributions at inlet and outlet stations as well as planes between individual stages and blade rows. They will be compared with measured data at MAN's gas turbine test rig which were obtained in the turn of a prototype telemetry test campaign. It will be demonstrated that the new method presented is an essential and quick tool for overall gas turbine design and matching of the gas turbine components. NOMENCLATURE

A Performance Simulation Methodology for a Whole Turboshaft Engine Based on Throughflow Modelling

“…Stewart [15] adopted a method to solve the axisymmetric Euler equations for integrated throughflow simulation of the E3 engine and nacelle. Petrovic et al [16][17][18] employed the finite element method to solve the throughflow governing equations based on the stream function approach. They combined a series of empirical models to construct the whole engine throughflow simulation model.…”