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Home Aerospace & Aeronautics A Novel Gas Turbine Blade Film Cooling Concept In Which The Film Naturally Oscillates

A Novel Gas Turbine Blade Film Cooling Concept In Which The Film Naturally Oscillates


The film cooling is the primary cooling technique employed in the gas turbine engineering to protect externally turbine blades operating at high gas temperatures (over 1,500K). At these flow conditions the coolant amount becomes so great, that associated pressure losses are comparable with achieved cooling effect or even exceed it. To reduce pressure losses the designers increase number of cooling rows (up to 5) leading to the wall temperature non-uniformity and surface cracks appearance. Currently employed film cooling configurations, including the shaped holes and complex angles are low effective, very sophisticated and expensive in production.

Recently, the novel idea of oscillating film cooling in which the film naturally oscillates was developed and tested in the Ukraine. The unsteady flow parameters and heat transfer downstream of one or two rows of spherical dimples under a range of boundary conditions have been studied to assess the merits and advantages of the suggested concept. The experimental studies have demonstrated the higher film cooling effectiveness, better flow mixing rate and lower spanwise wall temperature non-uniformity compared with traditional film cooling configuration. This idea is very tempting in terms of the better operational parameters of cooling system and might be effectively employed in the high performance gas turbines for the land, marine, and air applications.

Fig.1 Schematic view of vortex oscillations inside spherical
dimple and downstream of it..

Innovative Aspect and Main Advantages

As found, three-dimensional vortex structures generated inside spherical dimple fluctuate in the axial and angular directions, burst out of a dimple providing a wider surface coverage downstream of dimple row(s). These extraordinary flow features led to the innovative idea of the oscillating film cooling in which the coolant supplies into the vortex pole (figure). The main advantages of this concept compared with traditional film cooling are: (i) better surface coverage and lower spanwise wall temperature uniformity after row of dimples, (ii) higher heat transfer rate, (iii) lower coolant mass flow rate at the identical cooling efficiency. As expected, the number of cooling rows might also be reduced due to the higher film cooling effectiveness and better flow coverage.

Areas of Application

Aerospace and gas turbine engineering

Stage of Development

  • Development phase – laboratory tested.
  • Patented in Ukraine.
  • Chapters in two books and over 15 papers.

Contact Details

Organization: Institute for Engineering Thermophysics, National Academy of Science of Ukraine.
Contact person: Professor Artem A. Khalatov. Chlen-correspondent NANU, Head of the High Temperature Thermogasdynamics.
Address: 2A, Zhelyabova str., 03057, Kiev-57, Ukraine.
Tel: 044 456-9302.
Fax: 044 456-6091.
E-mail: This e-mail address is being protected from spambots. You need JavaScript enabled to view it


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