Abstract
In this article, the effects of film cooling holes arrangement and groove depth on the heat transfer and film cooling performance of blade tip are investigated. For this numerical research, a high-pressure turbine blade with the squealer tip is applied, and the tip clearance is given to be 0.8 mm (1% of the blade span). Simultaneously, a typical tip cooling technology of film holes in the groove floor is used. The number of film holes is fixed at 10, and two kinds of holes arrangements are considered: (1) equidistance distribution and (2) dense distribution near the leading edge. Three groove depths are studied with the values of 1.5, 2.0, and 2.5 mm (1.875%, 2.5%, and 3.125% of the blade span, respectively). The results show that the area-averaged film cooling effectiveness is higher when the holes distribute densely near the leading edge, and the cooling effect of the groove depth with 2.0 mm is obviously high compared with the other two depths.
Highlights
With the development of modern gas turbine technology, the inlet temperature in front of the high-pressure turbine is rising
The way of film cooling is achieved by one or more jetstreams blowing out from film holes, and the stream close to the hole forms a thin layer of cooling film and protects the tip wall from the high-temperature gas
The results showed that the heat transfer distribution in the squealer tip is obviously different from the one with the flat tip
Summary
With the development of modern gas turbine technology, the inlet temperature in front of the high-pressure turbine is rising. The study of approach in tip cooling and flow is eager to be implemented. The way of film cooling is achieved by one or more jetstreams blowing out from film holes, and the stream close to the hole forms a thin layer of cooling film and protects the tip wall from the high-temperature gas. A solid summary can be found in the study of Bogard et al.[1] They pointed that film cooling performance is quantified by using the film effectiveness, heat transfer
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
