Improving the high pressure compressor efficiency by optimizing the stator blades angles

Abstract


The optimization of multistage compressor of gas turbine engine is considered. Optimization was performed by changing the guide vanes angles of three stages. As a result the increasing of compressor efficiency by 0.3% was achieved on one of the main modes of operation.


About the authors

G. M. Popov

Samara State Aerospace University

Author for correspondence.
Email: grishatty@mail.ru

Russian Federation

Engineer of the Theory of Engine for Flying Vehicle Department

References

  1. Optimization of the gas turbine engine parts using methods of numerical simulation [Текст] / I.N. Egorov, M.L. Kuzmenko, Yu.N. Shmotin [et al.] // ASME paper GT2007-28205.
  2. Дмитриева, И.Б. Автоматизация создания объёмной модели пера лопатки в ANSYS TurboGrid на базе традиционного представления его геометрии [Текст] / И.Б. Дмитриева, Л.С. Шаблий // Вестн. СГАУ. – Самара, 2011. – №3 (27). - Ч. 3. – С. 106-111.

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