US 11,732,590 B2
Transition section for accommodating mismatch between other sections of a cooling aperture in a turbine engine component
Brian Craig, Palm Beach Gardens, FL (US); James M. Koonankeil, Marlborough, CT (US); Brian T. Hazel, Avon, CT (US); Paul E. Denney, Northborough, MA (US); and Dominic J. Mongillo, West Hartford, CT (US)
Assigned to Raytheon Technologies Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Aug. 13, 2021, as Appl. No. 17/401,927.
Prior Publication US 2023/0050204 A1, Feb. 16, 2023
Int. Cl. F01D 5/18 (2006.01); F01D 25/12 (2006.01)
CPC F01D 5/186 (2013.01) [F01D 25/12 (2013.01); F05D 2220/32 (2013.01); F05D 2260/202 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An apparatus for a turbine engine, comprising:
a turbine engine component including a sidewall and a cooling aperture;
the cooling aperture including an inlet, an outlet, a meter section, a diffuser section and a transition section, the transition section between and fluidly coupled with the meter section and the diffuser section, and the cooling aperture extending through the sidewall from the inlet to the outlet;
the meter section at the inlet;
the diffuser section at the outlet; and
the transition section configured to accommodate lateral misalignment between the meter section and the diffuser section, wherein a groove having an annular shoulder is formed at a first interface between the meter section and the transition section.