US 12,228,076 B2
Stud film cooling for double wall combustors
Timothy S Snyder, Glastonbury, CT (US); Roger O. Coffey, Glastonbury, CT (US); Lourdes M. Tafur Bermudez, Isabela, PR (US); Ryan Kimball Lundgreen, Provo, UT (US); and Dibesh D. Joshi, South Windsor, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jul. 20, 2023, as Appl. No. 18/356,109.
Prior Publication US 2025/0027449 A1, Jan. 23, 2025
Int. Cl. F02C 7/18 (2006.01); F23R 3/00 (2006.01)
CPC F02C 7/18 (2013.01) [F23R 3/002 (2013.01); F05D 2240/35 (2013.01); F05D 2260/232 (2013.01)] 20 Claims
OG exemplary drawing
 
16. A gas turbine engine, comprising:
a fan section,
a compressor section adjacent the fan section, and
a combustor section adjacent the compressor section, the combustor section including:
a combustion chamber,
an outer shell disposed around the combustion chamber, and
an inner shell disposed around the combustion chamber and between the combustion chamber and the outer shell, the inner shell including:
a top side facing the outer shell,
a bottom side facing the combustion chamber,
a stud coupled to the top side of the inner shell and extending toward the outer shell, the stud configured to secure the outer shell to the inner shell,
a first plurality of cooling holes disposed adjacent a first side of the stud and extending through the inner shell in a first direction that is rotated about 1° to about 45° counter-clockwise from an axial direction, and
a second plurality of cooling holes disposed adjacent a second side of the stud and extending through the inner shell in a second direction that is rotated about 1° to about 45° clockwise from the axial direction, wherein each of the first plurality of cooling holes and the second plurality of cooling holes has a pentagonal-shaped cross section.