Abstract: Combustion sections and sealing systems for fuel ignition assemblies of gas turbine engine combustion sections are provided. For example, a sealing system comprises a ferrule positioned on an outer surface of a ceramic matrix composite (CMC) combustor liner an aperture defined in the CMC liner; a sleeve positioned within an adapter of the fuel ignition assembly such that an inner end portion of the sleeve is in contact with the ferrule, the sleeve having an end wall that forms an inner boundary of a cavity defined by the sleeve; and a biasing member positioned within the cavity. The biasing member extends between a bushing and the end wall of the sleeve. The biasing member continuously urges the sleeve into contact with the ferrule to seal the aperture against fluid leakage therethrough. The exemplary sealing system may be part of a fuel ignition assembly of a gas turbine engine combustion section.

Abstract: Combustion sections and sealing systems for fuel ignition assemblies of gas turbine engine combustion sections are provided. For example, a sealing system comprises a ferrule positioned on an outer surface of a ceramic matrix composite (CMC) combustor liner an aperture defined in the CMC liner; a sleeve positioned within an adapter of the fuel ignition assembly such that an inner end portion of the sleeve is in contact with the ferrule, the sleeve having an end wall that forms an inner boundary of a cavity defined by the sleeve; and a biasing member positioned within the cavity. The biasing member extends between a bushing and the end wall of the sleeve. The biasing member continuously urges the sleeve into contact with the ferrule to seal the aperture against fluid leakage therethrough. The exemplary sealing system may be part of a fuel ignition assembly of a gas turbine engine combustion section.

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.

Abstract: A combustor assembly for a gas turbine engine includes a dome and a deflector positioned adjacent to the dome. One or both of the dome and the deflector define an opening, a component axis extending through the opening, and a radial direction relative to the component axis. The combustor assembly also includes a retainer having an outer member contacting the dome, the deflector or both. The outer member of the retainer defines at least in part a retainer cavity inward of the outer member along the radial direction. The dome, the deflector, or both define a plurality of cooling holes for providing a cooling airflow from the retainer cavity to the opening.

Abstract: Combustion sections and sealing systems for fuel ignition assemblies of gas turbine engine combustion sections are provided. For example, a sealing system comprises a ferrule positioned on an outer surface of a ceramic matrix composite (CMC) combustor liner an aperture defined in the CMC liner; a sleeve positioned within an adapter of the fuel ignition assembly such that an inner end portion of the sleeve is in contact with the ferrule, the sleeve having an end wall that forms an inner boundary of a cavity defined by the sleeve; and a biasing member positioned within the cavity. The biasing member extends between a bushing and the end wall of the sleeve. The biasing member continuously urges the sleeve into contact with the ferrule to seal the aperture against fluid leakage therethrough. The exemplary sealing system may be part of a fuel ignition assembly of a gas turbine engine combustion section.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

Abstract: Combustion sections and sealing systems for fuel ignition assemblies of gas turbine engine combustion sections are provided. For example, a sealing system comprises a ferrule positioned on an outer surface of a ceramic matrix composite (CMC) combustor liner an aperture defined in the CMC liner; a sleeve positioned within an adapter of the fuel ignition assembly such that an inner end portion of the sleeve is in contact with the ferrule, the sleeve having an end wall that forms an inner boundary of a cavity defined by the sleeve; and a biasing member positioned within the cavity. The biasing member extends between a bushing and the end wall of the sleeve. The biasing member continuously urges the sleeve into contact with the ferrule to seal the aperture against fluid leakage therethrough. The exemplary sealing system may be part of a fuel ignition assembly of a gas turbine engine combustion section.

Abstract: A combustor assembly for a gas turbine engine includes a dome and a deflector positioned adjacent to the dome. One or both of the dome and the deflector define an opening, a component axis extending through the opening, and a radial direction relative to the component axis. The combustor assembly also includes a retainer having an outer member contacting the dome, the deflector or both. The outer member of the retainer defines at least in part a retainer cavity inward of the outer member along the radial direction. The dome, the deflector, or both define a plurality of cooling holes for providing a cooling airflow from the retainer cavity to the opening.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. Additionally, a heat shield is provided. The heat shield includes an end also received within the slot defined by the annular dome. A mounting assembly attaches the forward end of the liner and the end of the heat shield to the annular dome, such that the forward end of the liner and the end of the heat shield are co-mounted within the slot defined by the annular dome.

Abstract: Various planting machines and planting methods are described. A planting method may include filling a seed pool with first-type seed, metering the first-type seed from the seed pool with a metering member, and then evacuating the first-type seed from the seed pool. The method may further include filling the seed pool with second-type seed, metering the second-type seed with the metering member, evacuating the second-type seed from the seed pool, and then refilling the seed pool with the first-type seed. First-type and second-type seed may be evacuated to separate temporary storage chambers, and the seed pool may be filled from the temporary storage chambers, as well as from bulk storage containers. A seed valve of a planting machine may include temporary seed storage chambers for different seed types. The seed valve may fill and evacuate a seed pool through rotation of various valve members and selective application of a vacuum.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. Additionally, a heat shield is provided. The heat shield includes an end also received within the slot defined by the annular dome. A mounting assembly attaches the forward end of the liner and the end of the heat shield to the annular dome, such that the forward end of the liner and the end of the heat shield are co-mounted within the slot defined by the annular dome.

Abstract: Various planting machines and planting methods are described. A planting method may include filling a seed pool with first-type seed, metering the first-type seed from the seed pool with a metering member, and then evacuating the first-type seed from the seed pool. The method may further include filling the seed pool with second-type seed, metering the second-type seed with the metering member, evacuating the second-type seed from the seed pool, and then refilling the seed pool with the first-type seed. First-type and second-type seed may be evacuated to separate temporary storage chambers, and the seed pool may be filled from the temporary storage chambers, as well as from bulk storage containers. A seed valve of a planting machine may include temporary seed storage chambers for different seed types. The seed valve may fill and evacuate a seed pool through rotation of various valve members and selective application of a vacuum.

Abstract: A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel. The method also includes forming a plurality of primary dilution holes in the first panel and forming a plurality of secondary dilution holes in the second panel, wherein the primary and secondary dilution holes are configured to discharge dilution air into the shell.

Abstract: A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel. The method also includes forming a plurality of primary dilution holes in the first panel and forming a plurality of secondary dilution holes in the second panel, wherein the primary and secondary dilution holes are configured to discharge dilution air into the shell.