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.

公开(公告)号：US20240410283A1

公开(公告)日：2024-12-12

申请号：US18208689

申请日：2023-06-12

Applicant: Raytheon Technologies Corporation

Inventor： Dana K. Bondarevsky ,  Dominic J. Mongillo, JR. ,  Christopher Paul Perron ,  Yuta Yoshimura ,  David D. Chapdelaine

IPC: F01D5/18

Abstract: An airfoil for a gas turbine engine includes a first wall disposed in an interior cavity, the first wall extending in the spanwise direction from a base region to a tip wall and adjoining a pressure side wall and a suction side wall to form a first cooling channel; a second wall disposed in the interior cavity and extending in a chordwise direction from the first wall toward a trailing edge, the second wall adjoining the pressure side wall and the suction side wall to form a second cooling channel; a first hole through the first wall, the first hole connecting the first cooling channel to the second cooling channel; and a second hole though the second wall connecting the second cooling channel to a third cooling channel.