| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a gas passage shape for reducing pressure loss caused by secondary flow of an inlet guide vane of a turbine of an axial flow gas turbine engine. <P>SOLUTION: An inner circumference wall Ch of a gas passage is provided with inner circumference concave parts Cc1, Cc3 at an upstream side and inner circumference convex parts Cv1, Cv3 at a downstream side, and an outer circumference wall Ct of the gas passage is provided with outer circumference convex parts Cv2, Cv4 at an upstream side and outer circumference concave parts Cc2, Cc4 at a downstream side. Consequently, differential pressure in a radial direction of an inlet guide vane V is reduced or partially reversed, and pressure loss can be reduced by inhibiting secondary flow toward a radial direction inside. The maximum load position where differential pressure at a positive pressure surface and a negative pressure surface of the inlet guide vane V is maximized is shifted to a rear edge TE side, circumferential secondary flow toward the negative pressure surface from the positive pressure surface of the inlet guide vane V adjacent in the circumferential direction is inhibited, and flow of gas flowing in a rear stage turbine can be equalized. <P>COPYRIGHT: (C)2009,JPO&INPIT</p> |
