Raising requirements for aircraft engine efficiency and fuel consumption level combined with strong restrictions to engine weight and geometrical dimension pose serious challenges for engineers who are working under the new generation of engine development. These tasks require brand new flow path design approaches. The usage of a counter-rotating turbine is one of the possible ways to successfully match all these requirements. Modern aerodynamic design computational and optimization methodologies allow to fulfil this task in the shortest period of time with the highest gain in turbine performances. A counter-rotating turbine means that blade rows are joined to two shafts with opposite rotation direction and different rotation speeds. Vanes elimination in a counter-rotating turbine helps to solve three important tasks of turbine improvement: • Increasing turbine efficiency by eliminating vanes and correspondingly losses in vanes; • Decreasing turbine blading weight; • Decreasing turbine axial length; These improvements are impossible without such fundamental design changes. In the current paper the steps of counter-rotating turbine aerodynamic design, optimization, and offdesign performances estimation are described. The comparison of traditional and counter rotating turbines integral and detailed thermodynamic performances are presented.
A new technique for multi-parameter optimization of gas turbines flow paths considering a variable mode for their operation is presented. It allows the estimation of the influence of flow path optimization on performance parameters of gas-turbine units, such as power, efficiency, and fuel consumption. An algorithm for turbine flow path multi-criteria optimization that takes into account the gas-turbine unit operation mode is shown. Approaches to speed up the optimization process are described. Using this technique GT-750-6M low pressure turbine flow path optimization based on real working loads during one year is carried out and the results are analyzed. Due to optimization the unit efficiency was improved at all operating modes. The total fuel economy for considered period makes 50.831 t.
The new method and algorithm of three-dimensional turbine guide blade rim optimization were proposed using CFDcalculations, guide blade deformation and reasonable computation time consuming optimization approach.Verification of three-dimensional CFD-calculations results are presented by comparison with experimental data. The reasonableness of the isolated guide blade rim optimization of a turbine stage is justified. Two methods of the complex tangential lean implementation are compared. The parametric model is developed allowing conservation of the mass flow rate through the blade passage during optimization process. Both a bowing method and computational grids construction are realized in specialized program TOpGrid. The gained grids has been written in format CGNS (CFD General Notation System). The optimization approach is grounded on a combination of the DOE theory and Monte-Carlo method. The algorithm of optimization of guide blade rim is described. The examination of aerodynamic optimization efficiency with the developed algorithm of a guide blade rim at different a/l (a-throat of the channel, l-height of a blade) was carried out . The analysis of the results of the computation and physical explanation of reasons of a turbine blade passage efficiency rise is given. NOMENCLATURE AND GLOSSARY1 1 1
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