Abstract: A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage. A combustor for a turbine engine includes an outer liner panel with a multiple of outer dilution passages. The multiple of outer dilution passages includes a repeating pattern of a first major outer air passage, a first minor outer air passage, a second major outer air passage, and a second minor outer air passage.

Abstract: Combustor panels for use in gas turbine engine combustors having a panel body having a peripheral rail around a periphery of the panel body, a first boss formed on the panel body and surrounding a first aperture that passes through the panel body, and a first webbing that extends from the peripheral rail toward the first boss. A first annular channel is formed between the first webbing and the first boss and surrounds the first boss and a first web pocket is formed within the first webbing between the peripheral rail and the first boss and defines a local extension of the first annular channel extending from the first boss to the peripheral rail.

Abstract: The present invention relates to novel peptides, compositions and methods for the prevention and/or treatment of pathological conditions and diseases associated with NADPH oxidase 1 (Nox1) activity, and/or increased reactive oxygen species (ROS) production. The novel peptides are thus particularly useful for treating and/or preventing cancer, atherosclerosis, angiogenesis, and aging.

Abstract: Combustor panels for use in gas turbine engine combustors having a panel body having a peripheral rail around a periphery of the panel body, a first boss formed on the panel body and surrounding a first aperture that passes through the panel body, and a first webbing that extends from the peripheral rail toward the first boss. A first annular channel is formed between the first webbing and the first boss and surrounds the first boss and a first web pocket is formed within the first webbing between the peripheral rail and the first boss and defines a local extension of the first annular channel extending from the first boss to the peripheral rail.

Abstract: A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell.

Abstract: The present invention relates to novel peptides, compositions and methods for the prevention and/or treatment of pathological conditions and diseases associated with NADPH oxidase 1 (Nox1) activity, and/or increased reactive oxygen species (ROS) production. The novel peptides are thus particularly useful for treating and/or preventing cancer, atherosclerosis, angiogenesis, and aging.

Abstract: The present invention relates to novel peptides, compositions and methods for the prevention and/or treatment of pathological conditions and diseases associated with NADPH oxidase 1 (Nox1) activity, and/or increased reactive oxygen species (ROS) production. The novel peptides are thus particularly useful for treating and/or preventing cancer, atherosclerosis, angiogenesis, and aging.

Abstract: The present disclosure relates to combustor configurations and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. The plurality of panels include a first panel having a leading and trailing edge, and a second panel having a leading edge and trailing edge, wherein a trailing edge of the first panel extends beyond the leading edge of the second panel and wherein the second panel is mounted to the support structure aft of the first panel.

Abstract: A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage. A combustor for a turbine engine includes an outer liner panel with a multiple of outer dilution passages. The multiple of outer dilution passages includes a repeating pattern of a first major outer air passage, a first minor outer air passage, a second major outer air passage, and a second minor outer air passage.

Abstract: The present invention relates to novel peptides, compositions and methods for the prevention and/or treatment of pathological conditions and diseases associated with NADPH oxidase 1 (Nox1) activity, and/or increased reactive oxygen species (ROS) production. The novel peptides are thus particularly useful for treating and/or preventing cancer, atherosclerosis, angiogenesis, and aging.

Abstract: A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell.

Abstract: A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which is located adjacent to the stator vane arrangement. The combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures. The combustor wall end includes a plurality of circumferentially extending film cooled regions. At least one of the film cooled regions is circumferentially aligned with one of the stator vanes and includes a cooling aperture.

Abstract: A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which is located adjacent to the stator vane arrangement. The combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures. The combustor wall end includes a plurality of circumferentially extending film cooled regions. At least one of the film cooled regions is circumferentially aligned with one of the stator vanes and includes a cooling aperture.