Course of leading edges for turbomachine components

Details Course of leading edges for turbomachine components Course of leading edges for turbomachine components

2008-04-24

2011-11-01

Look, Edward (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Cantilever blade

C416SDIG004

Reexamination Certificate

active

08047802

ABSTRACT:
The course of the leading edges of turbomachine components, such as rotor blades and stator vanes is defined mathematically exactly and repeatedly as well as aerodynamically advantageously by the respective axial coordinate in the direction of the machine axis in relation to the blade height in percent, extending from the blade tip as per equation (1):axial⁢⁢coordinate⁢[%⁢⁢blade⁢⁢height]=15⁢⁢extension⁢[%⁢⁢blade⁢⁢height]⁢⁢tan⁢⁢sweeptip(1-ⅇ-5⁢(100⁢%-blade⁢⁢height⁢[%])extention⁢[%⁢⁢blade⁢⁢height])and extending from the blade hub as per equation (2):axial⁢⁢coordinate⁢[%⁢⁢blade⁢⁢height]=15⁢⁢extension⁢[%⁢⁢blade⁢⁢height]⁢⁢tan⁢⁢sweephub(1-ⅇ-5⁢⁢blade⁢⁢height⁢[%]extention⁢[%⁢⁢blade⁢⁢height])where sweeptipor sweephub, respectively, represents the sweep angle at the tip or at the hub, determined in accordance with the operating conditions, and the extension represents the height of the blade in percent, by which the sweep angle departs from 0° relative to the coordinate extending normal to the axial coordinate.

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German Search Report dated Oct. 24, 2008 from counterpart German patent application No. 102007020476.2.
European search report dated Oct. 19, 2010 for counterpart patent application.

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