公开(公告)号：US12012866B1

公开(公告)日：2024-06-18

申请号：US18208684

申请日：2023-06-12

Applicant: Raytheon Technologies Corporation

Inventor： Dana K. Bondarevsky ,  Christopher Corcoran ,  Bryan P. Dube ,  Yuta Yoshimura ,  David D. Chapdelaine ,  Christopher Paul Perron

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F05D2260/20

Abstract: An airfoil for a gas turbine engine is configured to extend in a radial direction relative to an engine axis from an inner diameter to an outer diameter. The airfoil comprises a body having a base disposed at the inner diameter, a tip disposed at the outer diameter, a leading edge, a trailing edge, and pressure and suction side walls extending between the leading edge and the trailing edge and between the base and the tip. The body defines an interior cavity. A first wall is disposed in the interior cavity, extends radially, and adjoins the pressure side wall and the suction side wall to form a first cooling channel. A first hole through the first wall connects the first cooling channel to a second cooling channel. The first hole has a profile that tapers inward toward the base.