Leading edge impingement cooling system and turbine blade cooling system with adjacent wall impingement system

摘要

A turbine blade (10) usable in a turbine engine is disclosed. The turbine blade has an internal cooling system (14), the internal cooling system (14) is provided for improving the cooling of the leading edge (18) of the turbine blade (10) without leading edge film cooling showerhead row Of leading edge impingement passages (16). The internal cooling system (14) may comprise a leading edge cooling supply passage (20) formed from a leading edge wall (22), the leading edge wall (22) having a leading edge tip (24) , This leading edge tip (24) advances closer to the inner surface (26) of the leading edge (18) of the generally elongated hollow wing (28) than the other side of the leading edge cooling supply passageway (20) doing. The leading edge cooling supply passageway (20) may include a leading edge impingement orifice (30) that directs the cooling fluid to impinge on the inside surface (26) of the leading edge (18) of the wing (28). The internal cooling system (14) includes one or more adjacent wall ribs (92) with impingement orifices (90) in the leading edge cooling supply passage (20) to provide additional cooling of the adjacent walls, For example.