Turbine blade for a turbomachine and method for reducing bow wave effects

摘要

A turbine blade (24, 110, 130) for a turbomachine, said turbine blade (24, 110, 130) comprising: a main body portion (27) including a base (30) and a blade portion (32), said base (30) a forward blade lumen portion (59) and a shaft cavity (80), the forward blade lumen portion (59) having a first land (60) extending outwardly to define a groove recess (62); a cooling channel (87) extending through the main body portion (27); and at least one flow path (97, 114, 134) having a first end (104) in fluid communication with the cooling channel (87) or stem cavity (80) and a second end (105) facing the groove recess (62). the at least one flow path (97, 114, 134) provides a jet of cooling gas to the groove recess (62) of the forward blade lumen region (59), the jet of cooling gas providing suction of the hot gas in the first blade void region (59) front blade cavity portion (59), wherein the at least one flow path (97) between the first end (104) and the second end (105) is oriented obliquely inclined to the axial direction and obliquely inclined to the radial direction in a plane defined by the axial direction and a radial direction and the jet of cooling gas exits obliquely inclined to the radial direction and to the axial direction at the second end (105).