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

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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

Engineer of the Theory of Engine for Flying Vehicle Department

Russian Federation

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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