A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.

A combustor may comprise a combustion chamber encapsulated by a combustor casing, wherein the combustor casing comprises a casing forward portion, a casing radially inward portion, a casing radially outward portion, and a casing aft portion. The casing radially inward portion may comprise a dirt collector system comprising a hot panel adjacent to the combustion chamber; a cold shell panel coupled to the hot panel such that the hot panel is between the combustion chamber and the cold shell panel; and a dirt collector panel coupled to the cold shell panel such that the cold shell panel is between the hot panel and the dirt collector panel. The cold shell panel and the dirt collector panel at least partially define a dirt collecting space.

A combustion chamber assembly for an engine with at least one tile component, on the cold side of which facing away from a combustion space, a positioning aid with at least two positioning elements, wherein a defined position relative to the combustion chamber component is predefined for the tile component via the contact of the at least two positioning elements on at least one contact face of the combustion chamber component in two spatial axes.

A heat engine including a wall assembly is generally provided. The wall assembly includes a plurality of radial walls coupled together via a connecting member. The radial wall defines a flow opening therethrough. A flow cavity is defined between the plurality of radial walls and the connecting member.

An assembly is provided for a gas turbine engine. This assembly includes a combustor wall, a case and an inlet. The combustor wall is configured with a quench aperture. The case is displaced from the combustor wall such that a plenum is formed by and extends between the combustor wall and the case. The case includes a case wall, a deflector and a conduit. The deflector projects out from the case wall into the plenum towards the combustor wall. The deflector is arranged upstream of the quench aperture. The inlet to the conduit is arranged next to and downstream of the deflector.

Methods and systems for characterizing holes in a combustor liner of a gas turbine engine, and associated repair methods are provided. One method comprises receiving first measured data of the combustor liner in an uncoated state. The method includes determining a first location and a first orientation of a first hole and a first location and a first orientation of a second hole in the combustor liner using the first measured data. The method includes receiving second measured data of the combustor liner in a coated state where the second hole is at least partially obstructed by a coating and the first hole is substantially unobstructed by the coating. The method includes inferring a second location of the second hole of the combustor liner in the coated state using a known spacing between the first location of the first hole and the first location of the second hole. The characterization of the holes may be used to re-drill the obstructed second hole.

A trapped vortex combustor for use in a gas turbine engine includes an outer vortex chamber wall and a dome attached to, or formed integrally with, the outer vortex chamber wall. The dome, the outer vortex chamber wall, or both define at least in part an outer trapped vortex chamber and a channel. The channel extends along the circumferential direction at a forward end of the outer vortex chamber wall, the channel configured to receive an airflow through or around the outer vortex chamber wall, the dome, or both and provide such airflow as a continuous annular airflow to the inner surface of the outer vortex chamber wall. The dome further defines a fuel nozzle opening, with all openings in the dome outward of the fuel nozzle opening along the radial direction, excepting any effusion cooling holes having a diameter less than about 0.035 inches, being in airflow communication with the channel.

Systems and methods are provided for cleaning one or more cooling passages associated with a combustion chamber of a gas turbine engine. The gas turbine engine has a compressor section upstream from the combustion section. The method includes receiving a pressurized fluid from a source and directing the pressurized fluid through an inlet of a chamber such that a portion of a plurality of particles within the chamber is entrained within the pressurized fluid. The method includes injecting the pressurized fluid with the entrained portion of the plurality of particles downstream from the compressor section through an end wall of a diffuser and deswirl system upstream from a combustor plenum of the combustion section to clean the one or more cooling passages associated with the combustion chamber.

An annular dome assembly for a combustor. The annular dome assembly includes an annular dome including one or more dome panels defining the annular dome. A first dome panel includes a dome upstream surface and a dome downstream surface opposite the dome upstream surface. One or more dome arms extend from the dome upstream surface. One or more apertures extend from the dome upstream surface to the dome downstream surface. The annular dome assembly also includes a deflector assembly including one or more deflector panels defining the deflector assembly. A first deflector panel includes a deflector upstream surface and a deflector downstream surface opposite the deflector upstream surface. One or more deflector arms extend from the deflector upstream surface. Each of the one or more deflector arms are mounted within a respective aperture of the annular dome.

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.