Optimal design of impinging jets in an impingement/effusion cooling system

Constructal design for gas-turbine blade based on minimization of maximum thermal resistance

“…A C C E P T E D ACCEPTED MANUSCRIPT 9 In Ref. [11], it is assumed that the minimization of MTD is approximately the same as minimizing the length 0 L (shown in Fig.…”

“…Sciubba [8] developed an analytical method to estimate the cooling characteristic of a GTB, and the result showed that the method was a simple and physics-based one compared with the numerical method adopted in Ref. [9].…”

“…Therefore, the cooling problems of the gas-turbine blade (GTB) should be specially paid attention, and many scholars have shown great interests in these problems [1][2][3][4][5][6][7][8][9].…”

Conjugate heat transfer analysis of leading edge and downstream mist–air film cooling on turbine vane

“…The energy efficiency of a gas turbine is improved by increasing the turbine inlet temperature [1]. The inlet temperature of turbine engines has been steadily increasing with the development of new engine.…”

An Enhanced Flow-Thermo-Structural Modeling and Validation for the Integrated Analysis of a Film Cooling Nozzle Guide Vane

“…Moritz et al [19] studied film cooling holes at the leading edge of NGV by thermal-fluid coupling calculations. Kim et al [20] and Nowak et al [21] optimized the hole-structure to some extent and reduced the maximum temperature load with regard to the influences of porosity, passage, jet angle, and arrangement on film cooling effectiveness. In fact, however, the maximum temperature is not the sole factor of determining NGV service life.…”