Formation of film cooling on the turbine blade back and pressure side in the case of using V-shaped dimples

Abstract

Alongside the development of methods of intensifying convective heat transfer inside the blade, development of methods of local improvement of the efficiency of film cooling of the blade’s surface is still of immediate interest. The film is formed on the blade surface in conditions of high-camber shape and low initial velocity of the gas flow in the vicinity of the leading edge with its subsequent abrupt acceleration. The paper presents some data on the peculiarities of film formation on the back and pressure side of the blade in the vicinity of the leading edge. Experimental temperature distribution over the adiabatic wall was obtained with the use of a FLIR-E 64501 thermal imager. It was found that the conditions for the film formation on the blade back are more favorable than those on the pressure side. It manifests itself in the fact that optimal blowing parameters on the blade back are considerably lower than those on the pressure side. The use of V-shaped dimples located on the wall immediately behind the holes for blowing was suggested as a measure for local improvement of film cooling efficiency. The efficiencies of film cooling in the formation of a curtain, without the use and with the use of V-shaped dimples behind the holes for blowing were compared. Local improvement of efficiency and uniformity of film cooling distribution with the use of V-shaped dimples behind the holes for blowing was observed.

About the authors

V. V. Lebedev

Soloviev Rybinsk State Aviation Technical University

Author for correspondence.
Email: lebedevvlad2000@mail.ru

Candidate of Science (Engineering), Associate Professor,
Associate Professor of the Department of
Aircraft Engines

Russian Federation

O. V. Lebedev

Soloviev Rybinsk State Aviation Technical University

Email: lebedevov2000@mail.ru

Postgraduate Student of the Department of Aircraft Engines

Russian Federation

A. E. Remizov

Soloviev Rybinsk State Aviation Technical University

Email: ad@rsatu.ru

Doctor of Science (Engineering), Professor,
Head of the Department of Aircraft Engines

Russian Federation

References

  1. Sendyurev S.I., Tikhonov A.S., Khairulin V.T., Samokhvalov N.Yu. Modern cooling vane’s systems of high-loaded gas turbines. PNRPU Aerospace Engineering Bulletin. 2015. № 42. P. 34-46. doi: 10.15593/2224-9982/2015.42.03 (In Russ.)
  2. Sgarzi O., Leboeu F. Analysis of vortices in three-dimensional jets introduced in a cross-flow boundary-layer. Proceedings of the ASME Turbo Expo. 1997. V. 1. doi: 10.1115/97-GT-517
  3. Nesterenko V.G., Matushkin A.A. Design methods of modern air-jet engines turbine rotor blades film cooling system improvement. Trudy MAI. 2010. No. 39. Available at:http://trudymai.ru/published.php?ID=14813 (In Russ.)
  4. Jordan C.N., Wright L.M. Heat transfer enhancement in a rectangular (AR=3:1) channel with v-shaped dimples. Proceedings of ASME Turbo Expo. 2011. V. 5. doi: 10.1115/gt2011-46128
  5. Remizov A.E., Lebedev V.V., Lebedev O.V. Enhancement of local efficiency and film cooling allocation uniformity at V-shape recesses employment. Vestnik of P.A. Solovyov Rybinsk State Aviation Technical University. 2018. No. 1 (44). P. 26-31. (In Russ.)

Statistics

Views

Abstract: 550

PDF (Russian): 298

Dimensions

PlumX

Refbacks

  • There are currently no refbacks.

Copyright (c) 2020 VESTNIK of Samara University. Aerospace and Mechanical Engineering

License URL: https://journals.ssau.ru/index.php/vestnik/about/editorialPolicies#custom-2

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies