| 摘要 |
<p>A gas turbine engine airfoil (54, 225, 88) extending from an airfoil base (56, 228,91) to an airfoil tip (58, 138, 86) at a free end (87) of the airfoil (54, 225, 88) and from a leading edge (LE) to a trailing edge (TE) of the airfoil (54, 225, 88) has at least one recess (92) extending into and circumferentially completely through the airfoil tip (58, 138, 86) and located inwardly of the leading and trailing edges (LE, TE). The recess (92) is located in an area (93) of the airfoil tip (58, 138, 86) subject to high tip vibratory stress and or rubs and may be a circular scallop (94) having a scallop radius (R) and a maximum depth (D) of a few mills in a range of about .005 - .01 inches as measured from a nominal tip edge (106) without the recess. The airfoil may be on a radial blade (200), a stator vane (204), or an impeller blade (84). An annular tip seal (144) may surround a plurality of such airfoils with an airfoil tip (142). A corresponding method of reducing vibratory stress at an airfoil tip is also disclosed.</p> |
