| 摘要 |
A pulse detonation system for a gas turbine includes a rotatable cylindrical member (42) having a forward surface (44), an aft surface (46), and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages (52) are disposed therethrough. Each detonation passage (52) further includes: a leading portion (54) positioned adjacent the forward surface (44) of the cylindrical member (42), with the leading portion (54) having a centerline (67) therethrough oriented at a designated angle (60) to an axis (77) extending substantially parallel to the longitudinal centerline axis within a specified plane; a trailing portion (56) positioned adjacent the aft surface (46) of the cylindrical member (42), with the trailing portion (56) having a centerline (69) therethrough oriented at a designated angle (68) to the axis (77) within the specified plane; and, a middle portion (58) connecting the leading and trailing portions (54,56), with the middle portion (58) having a centerline (71) therethrough with a substantially constantly changing slope in the specified plane. A shaft is rotatably connected to the cylindrical member (42) and a stator is configured in spaced arrangement with the forward surface (44) of the cylindrical member (42) and a portion of the shaft. The stator further includes at least one group of ports formed therein alignable with the leading portions (54) of the detonation passages (52) as the cylindrical member (42) rotates. |
