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Effects of the multicavity tip coolant injection on the blade tip and the over tip casing aerothermal performance in a high-pressure turbine cascade

Du, Kun (author)
Lund University,Lunds universitet,Värmeöverföring,Institutionen för energivetenskaper,Institutioner vid LTH,Lunds Tekniska Högskola,Heat Transfer,Department of Energy Sciences,Departments at LTH,Faculty of Engineering, LTH,Northwestern Polytechnic University
Li, Huarong (author)
Northwestern Polytechnic University
Meng, Xianlong (author)
Northwestern Polytechnic University
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Chen, Qihao (author)
Northwestern Polytechnic University
Liu, Cunliang (author)
Northwestern Polytechnic University
Sundén, Bengt (author)
Lund University,Lunds universitet,LTH profilområde: Nanovetenskap och halvledarteknologi,LTH profilområden,Lunds Tekniska Högskola,LTH Profile Area: Nanoscience and Semiconductor Technology,LTH Profile areas,Faculty of Engineering, LTH,Northwestern Polytechnic University
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 (creator_code:org_t)
2022-08-03
2023
English.
In: Numerical Heat Transfer; Part A: Applications. - : Informa UK Limited. - 1040-7782 .- 1521-0634. ; 84:4, s. 340-354
  • Journal article (peer-reviewed)
Abstract Subject headings
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  • In high performance gas turbine engines, the over tip leakage flow driven by the lateral pressure gradient is inevitably induced inside the blade tip gap in the high-pressure stage turbine due to the freestanding airfoil design methodology. To obtain an increasing level of thermal efficiency, the turbine inlet temperature is gradually increased in terms of the Brayton cycle. Hence, the blade tip and the over tip casing are subjected to high thermal load. In real turbine blade, cavity tips are widely used to decrease the over tip leakage flow and the thermal load on the blade tip and over tip casing. In the present study, the numerical simulations were conducted to investigate the effects of the multicavity coolant injection on the blade tip and the over tip casing aerothermal performance. Three-dimensional (3-D) Reynolds-averaged Navier–Stokes (RANS) equations and standard (Formula presented.) turbulence model were solved together in the simulations. The results indicate the ribs inside the tip cavity alter the distribution of film cooling efficiency by changing flow structure within the tip gap. Most of the coolant is limited in each little cavity owing to the blockage of ribs. Here, the swirling action of each cavity vortex results in the coolant providing a wider film cooling coverage. Therefore, the increase in film cooling effectiveness on the blade tip surface is more efficient than that of over-tip casing. The blade with four tip cavities film cooling (4CFC) obtains the largest area-averaged film cooling effectiveness, which is augmented by 14.3% in comparison with the case with a single tip cavity film cooling (1CFC).

Subject headings

TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Energiteknik (hsv//swe)
ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Energy Engineering (hsv//eng)

Keyword

Coolant
film cooling effectiveness
multicavity tip
numerical simulations

Publication and Content Type

art (subject category)
ref (subject category)

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By the author/editor
Du, Kun
Li, Huarong
Meng, Xianlong
Chen, Qihao
Liu, Cunliang
Sundén, Bengt
About the subject
ENGINEERING AND TECHNOLOGY
ENGINEERING AND ...
and Mechanical Engin ...
and Energy Engineeri ...
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Numerical Heat T ...
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Lund University

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