Abstract: An assembly is provided that includes a slider seal having a washer and a tubular puck. The washer includes an inner washer surface and an outer washer surface. The inner washer surface extends around an axis of the slider seal and has a non-circular cross-sectional geometry. The inner washer surface forms a washer bore axially through the washer. The outer washer surface extends around the axis and has a cross-sectional geometry with a shape that is different than a shape of the non-circular cross-sectional geometry. The tubular puck projects axially through the washer bore and includes an outer puck surface. The outer puck surface extends around the axis. The outer puck surface is sealingly engaged with and configured to slide axially along the inner washer surface.

Abstract: An assembly is provided that includes a slider seal having a washer and a tubular puck. The washer includes an inner washer surface and an outer washer surface. The inner washer surface extends around an axis of the slider seal and has a non-circular cross-sectional geometry. The inner washer surface forms a washer bore axially through the washer. The outer washer surface extends around the axis and has a cross-sectional geometry with a shape that is different than a shape of the non-circular cross-sectional geometry. The tubular puck projects axially through the washer bore and includes an outer puck surface. The outer puck surface extends around the axis. The outer puck surface is sealingly engaged with and configured to slide axially along the inner washer surface.

Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.

Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.

Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.

Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.

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 combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.

Abstract: A cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter.

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 cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter.

Abstract: Aspects of the disclosure are directed to a liner of an aircraft. The liner comprises a panel including at least one dilution hole, a rail coupled to the panel, and at least one effusion cooling hole located between a wall of the at least one dilution hole and a side of the rail. The liner may be associated with a combustion engine of the aircraft.

Abstract: A fuel injection system for a gas turbine engine can be used to ensure successful transition in all conditions, while avoiding the possibility of steady state, or increasing power mode, operations with an insufficiently filled secondary fuel line. This may be accomplished by altering a pressure in a secondary fuel line. The present disclosure allows for the elimination of individual fuel injector valves, which may reduce the total complexity and number of parts of the fuel injection system.

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 cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter.

Abstract: Disclosed are exemplary apparatus and methods for removing a fluid from an article. A guide tube is extended into the article so that a tube first end resides in a region proximate the fluid. The guide tube is a rigid, semi-rigid or flexible member, allowing the tube to circumvent obstructions in the article. A wick, made of an absorbent material, is inserted into the tube until a wick first end is proximate the tube first end and is in contact with the fluid. Capillary action draws the fluid into the wick first end, where it is transferred to an opposite, wick second end that is disposed in a collection vessel. The vessel may contain an absorbent material to speed the removal process and simplify the disposal of the fluid. After removal, the fluid may be disposed of in an environmentally conscious manner.

Abstract: A fuel nozzle designed to reduce pollutant emissions and minimize the buildup of coke in the secondary fuel passage of a dual orifice fuel nozzle for the combustor of a gas turbine engine sizes the orifices and passages of the air and fuel so as to increase the pressure in the secondary passage during its inoperative mode and when the primary fuel passage is in the operative mode and having the air and fuel issuing from both the primary and secondary orifices swirl in the same direction.

Abstract: Coke hereinbefore known to form in the secondary passage of a dual orifice fuel nozzle for the combustor of a turbine type power plant is prevented from forming by imposing increased air pressure in the secondary passage during its inoperative mode and when the primary fuel passage is in the operative mode, without relying on purging or requiring an external air source.