| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a gas passage shape for reducing pressure loss caused by a secondary flow of the inlet guide vane of a turbine of an axial flow type gas turbine engine. <P>SOLUTION: An inner peripheral wall Ch of a gas passage of the turbine of the axial flow type gas turbine engine includes upstream inner peripheral recessed parts Cc1, Cc3 and downstream inner peripheral protrusions Cv1, Cv3, and an outer circumferential wall Ct of the gas passage includes upstream outer circumferential protrusion parts Cv2, Cv4 and downstream outer circumferential recessed parts Cc2, Cc4. By this configuration, a pressure difference in the radial direction of the inlet guide vane V is reduced or partially inverted, and the pressure loss can be reduced by suppressing the secondary flow toward inside in the radial direction. Also, a maximum load point where the pressure difference between the positive pressure face and the negative pressure face of the inlet guide vane V is maximum is shifted to a rear edge TE side, and the secondary flow from the positive pressure face to the negative pressure face of the inlet guide vane V adjacent to the circumferential direction is suppressed, to thereby uniformize the flow of gas flowing into the rear stage turbine. <P>COPYRIGHT: (C)2012,JPO&INPIT |
