| 摘要 |
<P>PROBLEM TO BE SOLVED: To reduce a pressure loss caused by a secondary flow of an inlet guide vane of a turbine of an axis-type gas turbine engine. <P>SOLUTION: A plurality of inlet guide vanes V are radially disposed in an annular gas duct sectioned between an inner peripheral wall Ch and an outer peripheral wall Ct of a turbine. The inner peripheral wall Ch of the gas duct includes upstream inner peripheral concavities Cc1 and Cc3 and downstream inner peripheral convexities Cv1 and Cv3. The outer peripheral wall Ct of the gas duct includes upstream outer peripheral convexities Cv2 and Cv4 and downstream outer peripheral concavities Cc2 and Cc4. Thus, a difference in pressure in a radial direction of the inlet guide vane V is reduced, or the pressure is partially inverted, so that a secondary flow going radially inward is suppressed to reduce the pressure loss. In addition, the maximum load position where the pressure difference between a pressure surface and a suction surface of the inlet guide vane V is the maximum is shifted toward a rear edge TE, so that a circumferential secondary flow going from the pressure surface toward the suction surface of the circumferentially adjacent inlet guide vane V is suppressed to equalize the gas flow flowing into a subsequent turbine. <P>COPYRIGHT: (C)2012,JPO&INPIT |
