Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor
AssigneeUnited Technologies Corporation
InventorsLee E. Bouldin, Dennis M. Moura, Jonathan J. Eastwood, Monica Pacheco-Tougas
Life of this patent
Estimating the term…
Abstract
A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle α therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.
Claims13
A wall assembly within a gas turbine engine having an axial centerline, comprising:
- a support shell having a first side and a second side opposite the first side;
- a liner panel mounted to the support shell, the liner panel having a cold side facing the support shell and a hot side opposite the cold side;
- and
- an annular grommet mounted between the support shell and the liner panel, the annular grommet comprising a transverse structure comprising a wall, the wall having a first surface and a second surface opposite the first surface, the annular grommet further comprising at least one effusion passage, the at least one effusion passage including an inlet in the first surface of the wall, the annular grommet further comprising an outer portion, mounted between the second side of the support shell and the cold side of the liner panel, and an inner portion comprising the second surface of the wall;
- wherein the inner portion of the annular grommet has a grommet hot side and a grommet cold side opposite the grommet hot side and wherein the grommet hot side of the annular grommet and the hot side of the liner panel collectively form a first common surface and the grommet cold side of the annular grommet and the first side of the support shell collectively form a second common surface radially spaced from the second side of the support shell with respect to the axial centerline,
- wherein the second surface of the wall at least partially defines and interfaces with a dilution passage, and
- wherein the transverse structure further comprises a seal face configured to form a seal between the transverse structure and the second side of the support shell about a circumference of the dilution passage;
- wherein the support shell includes a radial surface extending between the first side of the support shell and the second side of the support shell and wherein the radial surface of the support shell abuts an outer radial surface of the annular grommet extending between the seal face and the grommet cold side of the annular grommet.
Dependencies are inferred from the claim text.