抄録
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.
