Effects of hub endwall geometry and rotor leading edge shape on performance of supersonic axial impulse turbine. Part II: Method validation and final results.

Sebelev, Aleksandr; Smirnov, Maksim; Боровков, А. И.; Kuklina, Natalia; Rakov, Gennadiy

doi:10.29008/etc2019-165

Cited by 3 publications

(1 citation statement)

References 19 publications

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“…When calculating axial turbomachines, CFD methods are more successful, in particular, works [19] ̶ [21] present a positive experience of CFD calculations in relation to axial turbines. However, in case of axial compressors, the calculation results may not be completely correct.…”

Section: Introductionmentioning

confidence: 99%

Methodology and Experience of Primary Design of a Transonic Axial Compressor

Borovkov

Galerkin

Solovieva

et al. 2020

Wseas Transactions on Systems and Control

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The work presents the main provisions underlying the program for axial compressors calculation anddesign. The calculation of head losses and grids deflection capacity is based on the formulas of A. Komarov. Themodel contains empirical coefficients, values of which are selected during verification of the program based onthe tests results of multistage compressors and compressor stages. The main equations and algorithm for pressuresand velocities calculation under the radial equilibrium condition are presented. The use of computer programsbased on these models in the design of a 4-stage gas turbine engine compressor of moderate power with a totalpressure ratio of 3.2 and a given velocity is shown. For the first compressor stage, two variants with differentflow coefficients were compared. Variant #1 is designed with the classic recommendation to approach the samemechanical gas energy at the exit of the stage along the radius. Variant #2 is designed for a smaller flowcoefficient, but in order to ensure radial equilibrium, it was necessary to introduce a significant unevenness ofmechanical energy supply along the radius. Due to the lower kinetic energy, variant 2 has a 1.9% higher stageefficiency. Despite the fact that the loss coefficients of the blade devices are lower for variant #1. The questionremains as to how much the unavoidable mixing losses of variant #2 will reduce its efficiency in the process ofgas mechanical energy equalizing.

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Section: Introductionmentioning

confidence: 99%

Methodology and Experience of Primary Design of a Transonic Axial Compressor

Borovkov

Galerkin

Solovieva

et al. 2020

Wseas Transactions on Systems and Control

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Actualization of the ensuring the repeatability quality problem of a car generator set in conditions of large-volume production

Kozlovsky

Panyukov

Ermakov

et al. 2019

IOP Conf. Ser.: Mater. Sci. Eng.

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The causes of technological errors are quite numerous and varied, and they can be classified according to various criteria, for example, by the type of technological operations (errors in the machining operation of parts, winding and laying the windings into stator’s slots, etc.). The program performs an automated calculation of the characteristics of the generator when the input dimensional parameters of the core change within the limits of the tolerance field for each of them set by the technical specifications (TS). The algorithm of the program is based on the method of calculating a three-phase synchronous generator with a cranked rotor. To assess this effect, a system of interconnected computer programs and mathematical models has been built, with which it is possible to determine the weight of the influence of technological deviations in the manufacture of the generator on its performance and the characteristics of the electrical system as a whole. Reducing the variation of the generator reliability indicators can be achieved by phased assessment and timely adjustment of the quality level of design, production and ensuring their connection with the quality management system.

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Methodology and Experience in the Primary Designing a Transsonic Axial Compressor

et al. 2022

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The article considers the basic principles underlying the program for the calculation and designing gas turbine engine axial compressors. Calculation of pressure losses and deflection ability of the cascades is based on the formulas of A. Komarov. The model involves empirical coefficients, the values of which were selected during program verification based on the results of testing multistage compressors and compressor stages. The basic equations and the algorithm for calculating pressures and velocities are given under the condition of radial balance. The application of computer programs based on these models in designing a gas turbine engine four-stage compressor of moderate power with a total pressure ratio of 3.2 and a given speed is shown. For the first compressor stage, two options with different flow rates are compared. The first option was designed according to the classic recommendation to get close to the same mechanical energy of the gas at the exit of the stage along the radius. The second option was designed for a lower flow coefficient, but ensuring the radial balance, requires introducing a significant non-uniformity of mechanical energy supply along the radius. Due to the lower kinetic energy, the stage efficiency of the second variant is 1.9 % higher, despite the fact that the loss coefficients of the blade cascades are lower in the first variant. The question remains as to how much the inevitable mixing losses in the second variant will reduce its efficiency in the process of equalizing the mechanical energy of the gas

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Effects of hub endwall geometry and rotor leading edge shape on performance of supersonic axial impulse turbine. Part II: Method validation and final results.

Cited by 3 publications

References 19 publications

Methodology and Experience of Primary Design of a Transonic Axial Compressor

Methodology and Experience of Primary Design of a Transonic Axial Compressor

Actualization of the ensuring the repeatability quality problem of a car generator set in conditions of large-volume production

Methodology and Experience in the Primary Designing a Transsonic Axial Compressor

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