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TURBINE AIRFOIL COOLING SYSTEM WITH LEADING EDGE IMPINGEMENT COOLING SYSTEM AND NEARWALL IMPINGEMENT SYSTEM
专利权人:
Siemens Energy, Inc.
发明人:
MARSH, Jan H.,MATTHEWS, Ralph W.
申请号:
EP20140827579
公开号:
EP3158169(A1)
申请日:
2014.06.17
申请国别(地区):
欧洲专利局
年份:
2017
代理人:
摘要:
A turbine airfoil (10) usable in a turbine engine and having an internal cooling system (14) with a leading edge impingement channel (16) for enhanced cooling of the leading edge (18) of the turbine airfoil (10) without a leading edge film cooling showerhead array is disclosed. The internal cooling system (14) may include an leading edge cooling supply channel (20) formed from a leading edge wall (22) having a leading edge tip (24) that is advanced closer to an inner surface (26) of the leading edge (18) of the generally elongated, hollow airfoil (28) than other aspects of the leading edge cooling supply channel (20). The leading edge cooling supply channel (20) may include leading edge impingement orifices (30) for directing cooling fluids to impinge on the inner surface (26) of the leading edge (18) of the airfoil (28). The internal cooling system (14) may also include one or more nearwall ribs (92) with impingement orifices (90) in the leading edge cooling supply channel (20) for providing additional cooli
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