Conditions along the boundaries of bladed zones within the flow tracts of turbines

Lurie, Konstantin A.; Fedorov, A. V.; Климович, В. И.

doi:10.1002/fld.1650020307

Cited by 3 publications

(2 citation statements)

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“…In that case, there are an additional n S ¡ 1 parameters to optimize. If the enthalpy drop of every stage is known, the same procedure [equations (3) to (8)] should be performed for every stage in order to nd the corresponding set of nine ow parameters.…”

Section: Design Optimizationmentioning

confidence: 99%

“…This technique gives the optimum geometry of the row at mean diameter and is widely used for preliminary turbomachinery design. There were also early attempts at optimizing multistage axial compressor meridional planes [7] and a highly analytical approach at optimizing inlet and exit boundary conditions for each blade row in an axial turbine [8]. Massardo et al [9] used a throughow code to optimize the spanwise distribution of an axial compressor blade geometry.…”

Section: Introductionmentioning

confidence: 99%

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Optimization of multistage turbines using a through-flow code

Petrović

Dulikravich

Martin

2001

Proceedings of the Institution of Mechanical Engineers, Part A:

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Fast and accurate flow calculation and performance prediction of multistage axial flow turbines at design and off-design conditions were performed using a compressible steady state inviscid through-flow code with high fidelity loss and mixing models. The code is based on a stream function model and a finite element solution procedure. A new design system has been developed which optimizes hub and shroud geometry and inlet and exit flow field parameters for each blade row of a multistage axial flow turbine. Optimization was performed using a hybrid constrained optimization code that switches among the modules automatically in order to avoid local minima and to accelerate design convergence rate. By automatically varying a relatively small number of geometric variables per turbine stage it is possible to find an optimal radial distribution of flow parameters at the inlet and outlet of every blade row. Thus, an optimized meridional flow path can be found that is defined by the optimized shape of the hub and shroud while keeping blade shapes intact. The multistage design optimization system has been demonstrated using an actual two-stage axial gas turbine as an example. The comparison of computed performance of an already very high efficiency initial design and its optimized design demonstrates more than 1 per cent improvement in the turbine efficiency at design and significant off-design conditions. The entire design optimization process is feasible on a typical single-processor computer workstation or a personal computer.

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Section: Design Optimizationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%