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Home     Ukrainian Institutes Department of High Temperature Thermogasdynamics

Department of High Temperature Thermogasdynamics, Institute of Engineering Thermophysics

Staff of Department of High Temperature Thermogasdynamics

The Department of High Temperature Thermogasdynamics (DHTTGD) of the National Academy of Sciences has vast experience in the aerospace engineering field. DHTTGD has worked for many years with the leading gas turbine and space companies.

Primary scientific directions

  • novel cooling technologies for high performance gas turbines
  • flow separation control in gas turbines, centrifugal compressors and flight control
  • heat transfer studies in components of aerospace systems

Distinctive competencies

Novel oscillating film cooling technique

Development of heat resistance alloys has lagged behind designers requirements. Since modern gas turbines operate at gas turbine levels above the blade melting point, both internal and external cooling systems are employed in the blades to meet product life span. Film cooling is the primary technique employed in various applications to protect objects externally in the flow path while operating at high gas temperatures.

However, in some cases, the coolant amount becomes so great that associated pressure losses due to providing the cooling flow are excessive. To reduce losses, designers increase the number of cooling arrays which leads to significant wall temperature non-uniformity, thermal stresses, surface cracks, and damage. Modern production technologies, such as shaped cooling holes with compound angles, give opportunities for increasing the coolant flow without large increases in pressure loss penalties. However, they are complex and expensive.

Recently, the unique vortex structures generated in a deep spherical dimple at relatively high Reynolds number flow were documented. This led to the innovative concept of using dimples to create a naturally oscillating film cooling pattern, as patented in the Ukraine. The aim of the proposed collaboration is to evaluate the primary merits and benefits of this innovative film cooling concept where the film naturally oscillates.

Innovative internal cyclone cooling for gas turbine blades

Despite the progress in the design of cooling systems, adequate internal blade cooling remains a serious engineering problem. The cyclone cooling concept is based on the creation of swirl flow in a blade cooling passage. The results of experimental studies have demonstrated the high ability of a cyclone cooling concept to enhance heat transfer in the cooling passage. In some cases this extends the limit of the internal blade cooling system, and the production of a blade with internal cyclone cooling is much simpler and more cost effective. The aim of the proposed collaboration is to evaluate the merits and benefits of the cyclone cooling scheme in terms of the real blade design.

Passive flow separation control

The suction side of the gas turbine and compressor blade often suffers from boundary layer separation while operating at off-design or close to off-design conditions. The separation zone reduces the blade (aerodynamic profile) efficiency and leads to a reduction of turbine or compressor power. To improve the turbine or compressor efficiency both active and passive flow separation control techniques are being considered. The aim of the proposed collaboration is to assess the effect of span-wise dimple configurations on the efficiency of the flow separation control using the actual gas turbine or compressor blades and various space system elements.

The oscillating film cooling concept: Top - the angular fluctuations of jets bursting out of dimples Bottom - compressed vortex inside a deep spherical dimple
The oscillating film cooling concept:
Top - the angular fluctuations of jets bursting out of dimples
Bottom - compressed vortex inside a deep spherical dimple

Passive flow separation control using the surface dimple technology. Flow separation over gas turbine blade.
Passive flow separation control using the
surface dimple technology. Flow
separation over gas turbine blade.

Passive flow separation control using the surface dimple technology. “Suppression” of the flow separation by means of dimple row.
Passive flow separation control using the surface
dimple technology. “Suppression” of the flow separation
by means of dimple row.

Passive flow separation control using the surface dimple technology. Flow field inside the two-dimensional groove.
Passive flow separation control using the surface
dimple technology. Flow field inside the two-dimensional
groove.

Partnering opportunities

The DHTTGD has close scientific and industrial links with Cardiff University (UK), University of Oxford (UK), University of Cambridge (UK), Rolls-Royce (UK), Solar Turbines Inc. (USA), General Electric (USA), US Air Force Academy, Stuttgart University (Germany) and others.

Over the last ten years the DHTTGD was involved in several international projects and research programs in the aerospace engineering field. This includes the programs carried out jointly with the Cardiff University (UK), University of Utah (USA), US Air Force Academy (USA) and Russian aerospace companies.

The DHTTGD is looking for international collaboration to establish experimental and CFD studies of the innovative cooling systems, flow separation and flight control and heat transfer studies in components of aerospace engineering.

Contact Details

Artem Khalatov, Professor, Head of DHTTGD
Address: 2A Zhelyabova str., 03057, Kyiv-57, UKRAINE
Tel. (of.): 38 (044) 456-9302
E-mail: This e-mail address is being protected from spambots. You need JavaScript enabled to view it

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