To increase the thermal efficiency of gas turbines, inlet temperature of gas is increased. This results in the requirement of cooling of gas turbine blades and vanes. Internal cooling of gas turbine blades and vanes is one of several options. Two-pass channels are provided with ribs to enhance heat transfer at the expense of an increased pressure drop. The space in the blade is limited and requires channels with small aspect ratios. Numerical simulations have been performed to investigate heat transfer, flow field and pressure loss in a two-pass channel equipped with 45 ribs with aspect ratio (Win/H) equal to 1:3 in the inlet pass and 1:1 in the outlet pass with both connected together with a 180 bend. The results are compared with a higher aspect ratio channel (Win/H = 1:2, inlet pass). In the ribbed channel, a decrease in pressure drop was observed with a decrease in the aspect ratio of the channel. The smaller aspect ratio channel not only allows using more cooling channels in the blade, but also results in more heat transfer enhancement. The divider-to-tip wall distance (Wel) has influence on the pressure drop, as well as on the heat transfer enhancement at the bend and outlet pass. Heat transfer decreases with decrease in aspect ratio of the inlet pass of the two-pass channel. With increase in divider-to-tip wall distance, heat transfer tries to attain a constant value.
|Original language||English (US)|
|Number of pages||16|
|Journal||Heat and Mass Transfer/Waerme- und Stoffuebertragung|
|State||Published - May 1 2013|
All Science Journal Classification (ASJC) codes
- Condensed Matter Physics
- Fluid Flow and Transfer Processes