IGTC-10 / ASME-83-GTJ-16 IMPINGEMENT COOLING OF TURBINE AIRFOILS BY MULTIPLE TWO-DIMENSIONAL JETS(Session A-3 Heat Transfer III (Internal Surface))

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概要

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• For internal cooling of turbine vanes by convection type-impingement of compressor bleed air, a frequently used arrangement is a multitude of round holes through which cooling air is impacted on the inner surface of a turbine blade. High heat transfer rates at the impingement points are utilized to remove the heat load imparted by external high-temperature gas streams. The localized, high heat transfer rates are accompanied by a rapid decay as the jet spreads away from its center of impact. Furthermore, in the regions between neighboring jets, heat transfer rates are less susceptible to rational correlation of the performance data. It appears that some of the drawbacks can be alleviated by using a series of two-dimensional or line jets impinging onto the inner surface of a blade, resulting in a line of impingement. In this investigation, the jet spacing, jet height and jet Reynolds number were varied within limits of practical interest commensurate with turbine cooling application. All jets were of equal width. Two series of experiments wer run: one with equal flow for the jets, and the other with increasing flow rates for jets on either side of the symmetry line. A principal feature of the two-dimensional multi-jet configuration is that the heat transfer coefficient shows a less steep decay distribution than a single axis-symmetry jet. Furthermore, by varying the flow rates among the line jets, the surface heat transfer distribution can be modified to a certain extent. Correlations of the average heat transfer coefficients over the region facing the jets are given in this paper.

• 公益社団法人日本ガスタービン学会の論文

著者

• Han L.s.

  Mechanical Engineering Ohio State University

• Kayansayan N.

  Mechanical Engineering Dept., Ege University

• Dantzer C.W.

  General Motors Corporation

• Kayansayan N.

  Mechanical Engineering Dept. Ege University

関連論文

• IGTC-3 / ASME-83-GTJ-9 THE ENDWALL INFLUENCE ON HEAT TRANSFER FROM A SINGLE CYLINDER : THE HORSESHOE VORTEX EFFECT(Session A-1 Heat Transfer I (External Surface))
• IGTC-10 / ASME-83-GTJ-16 IMPINGEMENT COOLING OF TURBINE AIRFOILS BY MULTIPLE TWO-DIMENSIONAL JETS
• IGTC-10 / ASME-83-GTJ-16 IMPINGEMENT COOLING OF TURBINE AIRFOILS BY MULTIPLE TWO-DIMENSIONAL JETS(Session A-3 Heat Transfer III (Internal Surface))

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