A method for large-scale, real-time simultaneous additive and subtractive manufacturing is described. The apparatus used in the method includes a build unit and a machining mechanism that are attached to a positioning mechanism, a rotating platform, and a rotary encoder attached to the rotating platform. The method involves rotating the build platform; determining the rotational speed; growing the object and the build wall through repetitive cycles of moving the build unit(s) over and substantially parallel to multiple build areas within the build platform to deposit a layer of powder at each build area, leveling the powder, and irradiating the powder to form a fused additive layer at each build area; machining the object being manufactured; and cutting and removing the build wall. The irradiation parameters are calibrated based on the determined rotational speed.

In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.

Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.

A staged fuel injector comprises a pilot inner air swirler arranged along a centre axis of the injector, a pilot fuel swirler arranged radially outboard of the pilot inner air swirler, a main inner air swirler arranged radially outboard of the pilot fuel swirler and a main fuel swirler arranged radially outboard of the pilot fuel swirler. A fuel feed arm is arranged in fluid communication with the pilot fuel swirler and the main fuel swirler for delivering fuel to the pilot fuel swirler and the main fuel swirler and a heat protective casing enclosing the fuel feed arm, the pilot fuel swirler and the main fuel swirler.

There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions. The gas turbine combustor includes: a cylindrical combustion chamber that burns combustion air and fuel to thereby produce combustion gas; an outer casing disposed concentrically on an outside of the combustion chamber; an end cover disposed at an upstream side end portion of the outer casing; an annular passage formed by an outer peripheral surface of the combustion chamber and an inner peripheral surface of the outer casing, the annular passage allowing the combustion air to flow therethrough; and a passage formed inside a combustion chamber wall between the outer peripheral surface and an inner peripheral surface of the combustion chamber, the passage having a U-shape turned sideways and having ends disposed on an upstream side in a transverse cross-sectional view, in which the passage includes a first passage that extends in parallel with an axial direction of the combustion chamber and has a supply hole on a first end side thereof, the supply hole communicating with an outside of the combustion chamber wall, and a second passage that has a second end side communicating with a second end side of the first passage and has a jet hole on a first end side thereof, the jet hole communicating with an inside of the combustion chamber wall.

A combustor assembly for a gas turbine engine includes a liner and a combustor dome. The combustor dome and liner together at least in part define a combustion chamber. The combustor dome includes a transition portion and a forward wall. The transition portion extends from the forward wall towards the liner. Additionally the transition portion may define an angle relative to the forward wall and/or may define a radius of curvature between the forward wall of the combustor dome and a flat of the transition portion of the combustor dome for increasing an aerodynamic efficiency of the combustor dome.

A fuel supply system includes a first component configured to direct a fuel flow to a combustor of an engine system. The first component includes a first inner surface and a first outer surface. The fuel supply system also includes an outer coating disposed on the first outer surface of the first component. The outer coating is configured to thermally insulate a first interior of the first component to reduce non-catalytic coke formation in the first interior. Additionally, the fuel supply system includes an inner coating disposed on the first inner surface of the first component. The inner coating is configured to reduce the fuel flow from contacting a base material of the first inner surface of the first component to reduce catalytic coke formation in the first interior.

A method of manufacturing a component includes forming an inner wrap about a mandrel. The inner wrap has first and second walls joined by a base portion and an outer wall. A rod is arranged at each of the first and second walls. An outer wrap is formed about the inner wrap and the rods to form a body. Features are formed in the first and second walls.

A fuel injector comprises a swirler and the swirler comprises a plurality of vanes, a first member and a second member. The second member is arranged coaxially around the first member and the vanes extend radially between the first and second members. The vanes have leading edges and the second member has an upstream end. The leading edges of the vanes extend with radial and axial components from the first member to the upstream end of the second member and the radially outer ends of the leading edges of the vanes form arches with the upstream end of the second member. The arrangement of the swirler enables the fuel injector to be built by direct laser deposition.

A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole.