Performance of primary holes in presence of dilution and cooling holes in a reverse-flow combustor model

Experimental investigations on discharge coefficient of row of primary holes of a reverse-flow gas turbine combustor have been carried out using a plane annulus model. The studies have been carried out in a wide range of Reynolds number (0.1 x 10(4) to 1.65 x 10(4)) on the individual row of primary holes as well as in combination with the other rows of liner holes. It observed that presence of other rows of liner holes significantly affect static pressure distribution at the primary holes. Static pressure at all the four rows of liner holes, when operating together, increased up to a magnitude till R-e = 1.35 x 10(4) and decreased thereafter with further increase in R-e. The values of discharge coefficient of row of primary holes. when operating alone remained in the range of 0.74-0.69. These magnitudes reduced in the presence of individual row of dilution (by approximate to18%) and cooling holes (by approximate to6%) while they improved to the extent of approximate to0.77 to 0.72 (K = 1510 to 1750) when all the four rows operating together