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Fundamentally Studies on the Double-ducker Cooling Structures of Impingment with Film Outflow in Rotating State

Author: WangXiaoPing
Tutor: MaoJunZuo
School: Nanjing University of Aeronautics and Astronautics
Course: Aerospace Propulsion Theory and Engineering
Keywords: Impact Gas film Bilayer Turbine blades Rotation
CLC: V231.1
Type: Master's thesis
Year: 2007
Downloads: 84
Quote: 0
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Abstract


In this paper, \First under static conditions, the double layer structure is limited within a small space impinging jet produced cyclone pilot study of the heating effect of the impact orifice as well as the effect on the overall heat exchanger, and by changing the impact of the bilayer structure pitch ratio ( impact spacing and the impact hole diameter ratio H / D), the impact of the jet Re number of parameters, a set of parameters that change the impact of the heat transfer enhancement effect of the cyclone, a detailed analysis of the strengthening of the impact of the cyclone in the confined space change thermal characteristics and variation. The experimental results show that, with the impact of the Reynolds number Re is increased, impact orifice flux density and the ratio of the total heat flux density q 2 / Q1 rendering decreasing trend. When the impact spacing ratio H / D increases, q / q1 change is not monotonous, trends appear first increases and then decreases. The scope of heat transfer enhancement in the test conditions, the impact of the cyclone the impact orifice is substantially impact the region of the holes 4.5 ~ 6D, q 2 / Q1 variation range of 9% to 20%. Subsequently, analyzed and summarized under stationary conditions, the impact of the cyclone on the basis of the contribution of double-layer structure within the heat exchanger, in rotation conditions, to carry out the the rotation conditions under different turbulence models applicability validation comparison; then double impact modeling / composite cooling structure of the gas film, in rotation under the conditions of the numerical calculations for the composite cooling structure, discussed by a large number of calculations under different rotating number and impact spacing and the impact hole inclination and hair than the structure of the flow field within the confined space of two-tier structure and change thermal characteristics studied. The study results show that the rotation impinging jet deflection and gas film flow acceleration, resulting in the double segment different areas of the wall temperature distribution and cooling efficiency with speed variation. Vertical impact with impact spacing increases cooling efficiency decreased tilt shock (30 °) cooling efficiency with the impact of the change is not monotonic spacing. Cooling efficiency vertical impact with the blowing ratio increases the cooling effect of the rise, while the tilt shock (30 °) with blowing ratio change is not monotonic. Studies have shown that small spacing within the confined space, impinging jet will be deflected to form a cyclone and a direct impact on the overall effect of heat transfer, the impinging jet deflection at the same time by the direction of rotation, speed, double wall geometry parameters, and hair than and other parameters together, showing the complex interaction of law.

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Engine theory > Thermodynamics, heat transfer
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