Browsing by Author "Liu, Yao-Hsien"
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Item Effect of rib spacing on heat transfer and friction in a rotating two-pass rectangular (AR=1:2) channel(Texas A&M University, 2006-10-30) Liu, Yao-HsienThe research focuses on testing the heat transfer enhancement in a channel for different spacing of the rib turbulators. Those ribs are put on the surface in the two pass rectangular channel with an aspect ratio of AR=1:2. The cross section of the rib is 1.59 x 1.59 mm. Those ribs are put on the leading and trailing walls of the channel with the angle of flow attack to the mainstream of 45????. The rotating speed is fixed at 550-RPM with the channel orientation at ????=90????. Air is used as the coolant through the cooling passage with the coolant-to-wall density ratio ( ???? ???? ?????? ) maintained around 0.115 in the first pass and 0.08 in the second pass. The Reynolds numbers are controlled at 5000, 10000, 25000, and 40000. The rib spacing-to-height ratios (P/e) are 3, 5, 7.5, and 10. The heat transfer coefficient and friction factor are measured to determine the effect of the different rib distributions. Stationary cases and rotational cases are examined and compared. The result shows that the highest thermal performance is P/e=5 for the stationary case and P/e=7.5 for the rotating case.Item Heat transfer in leading and trailing edge cooling channels of the gas turbine blade under high rotation numbers(2009-05-15) Liu, Yao-HsienThe gas turbine blade/vane internal cooling is achieved by circulating the compressed air through the cooling passages inside the turbine blade. Leading edge and trailing edge of the turbine blade are two critical regions which need to be properly cooled. Leading edge region receives extremely hot mainstream flow and high heat transfer enhancement is required. Trailing edge region usually has narrow shaped geometry and applicable cooling techniques are restricted. Heat transfer will be investigated in the leading edge and trailing edge cooling channels at high rotation numbers close to the engine condition. Heat transfer and pressure drop has been investigated in an equilateral triangular channel (Dh=1.83cm) to simulate the cooling channel near the leading edge of the gas turbine blade. Three different rib configurations (45?, inverted 45?, and 90?) were tested at four different Reynolds numbers (10000-40000), each with five different rotational speeds (0-400 rpm). By varying the Reynolds numbers (10000-40000) and the rotational speeds (0-400 rpm), the rotation number and buoyancy parameter reached in this study were 0-0.58 and 0-2.3, respectively. 45? angled ribs show the highest thermal performance at stationary condition. 90? ribs have the highest thermal performance at the highest rotation number of 0.58. Heat transfer coefficients are also experimentally measured in a wedge-shaped cooling channel (Dh =2.22cm, Ac=7.62cm2) to model an internal cooling passage near the trailing edge of a gas turbine blade where the coolant discharges through the slot to the mainstream flow. Tapered ribs are put on the leading and trailing surfaces with an angle of attack of 45?. The ribs are parallel with staggered arrangement on opposite walls. The inlet Reynolds number of the coolant varies from 10,000 to 40,000 and the rotational speeds varies from 0 to 500 rpm. The inlet rotation number is from 0 - 1.0. The local rotation number and buoyancy parameter are determined by the rotational speeds and the local Reynolds number at each region. Results show that heat transfer is high near the regions where strong slot ejection exists. Both the rotation number and buoyancy parameter have been correlated to predict the rotational heat transfer enhancement.