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发明授权
CN107091122B 具有冷却的涡轮发动机翼型件 有权

具有冷却的涡轮发动机翼型件
摘要：
本发明涉及具有冷却的涡轮发动机翼型件。具体而言，一种用于冷却燃气涡轮发动机(10)的翼型件(78)的设备和方法包括用于翼型件(78)的径向外端的末梢(80)，翼型件(78)具有在翼型件(78)的内部(96)内限定冷却回路(110)的内部肋(108)。肋(108)可以是全长度(120)的，在翼型件(78)的根部(82)与末梢(80)之间延伸。可在全长度肋(120)中在末梢(80)附近形成间隙(122)，以形成用于全长度肋(120)的热应力减小结构(122)。
摘要（英）：

An apparatus and method of cooling an airfoil (78) for a gas turbine engine (10) includes a tip (80) for the radially outer end of the airfoil (78) with internal ribs (108) defining cooling circuits (110) within an interior (96) of the airfoil (78). The ribs (108) can be full-length (120), extending between a root (82) and tip (80) of the airfoil (78). A gap (122) can be formed in the full-length ribs (120) near the tip (80) to form a thermal stress reduction structure (122) for the full-length rib (120).

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