The present study is conducted to investigate th local heat/mass transfer characteristics on the shroud with blad tip clearances. The relative motion between blade and shroud i neglected, and four-bladed linear cascade is used in this study, naphthalene sublimation method is employed to determine th detailed local heat/mass transfer coefficients on the surface o shroud. The tip clearance is changed from 0.66% to 2.85% of th blade chord length. The flow enters the gap between the blade ti and shroud at the pressure side due to the high pressur difference. Therefore, the heat/mass transfer characteristics o the shroud are changed significantly from those with endwall. A first, high heat/mass transfer occurs along the profile of blade a the pressure side due to the entrance effect and acceleration of th gap flow. Then, the heat/mass transfer coefficients on the shrou increase along the suction side of the blade because tip leakag vortices are generated and interact with the main flow. Th results show that the heat/mass transfer characteristics ar changed largely with the gap distance between the tip of turbin blade and the shroud.
|Number of pages||8|
|Journal||Annals of the New York Academy of Sciences|
|Publication status||Published - 2001 Jan 1|
All Science Journal Classification (ASJC) codes
- Biochemistry, Genetics and Molecular Biology(all)
- History and Philosophy of Science