Abstract: A combustor for a turbine engine includes an outer liner having a row of circumferentially distributed outer combustion air holes and an inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners each include at least a major air hole having a first hole size, an intermediate air hole having a second hole size, and a minor air hole having a third hole size. The first, second, and third hole sizes are all different from each other.

Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

Abstract: A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.

Abstract: A method of combusting a catalyzed hydrocarbon fuel comprising providing a first fluid and a second fluid, at least one of said fluids comprising a mixture of a hydrocarbon fuel with an air stream, passing the first fluid into one or more catalytic tubes of a catalytic reactor, and passing the second fluid adjacent the catalytic tubes in a chamber of a catalytic reactor. A varying tube cross section to modify the flow of one of the fluids is provided for at least a portion of the tube. The flow of the first fluid leaving the catalytic tubes is mixed with the second fluid and combusted.

Abstract: A combustor assembly for a turbine engine includes an aft open end that communicates gas flow to a turbine assembly. The combustor assembly includes a liner assembly that terminates at a first fixed vane. A portion of the liner assembly extends an axial distance into the first fixed vane portion. An inner surface of the liner assembly corresponds with inner surfaces of the fixed vane portion to provide a smooth transition from the inner surfaces of the combustor assembly to the turbine assembly.

Abstract: A method of combusting a catalyzed hydrocarbon fuel comprising providing a first fluid and a second fluid, at least one of said fluids comprising a mixture of a hydrocarbon fuel with an air stream, passing the first fluid into one or more catalytic tubes of a catalytic reactor, and passing the second fluid adjacent the catalytic tubes in a chamber of a catalytic reactor. A varying tube cross section to modify the flow of one of the fluids is provided for at least a portion of the tube. The flow of the first fluid leaving the catalytic tubes is mixed with the second fluid and combusted.

Abstract: A catalyst conduit for a catalytic reactor of a turbine combustor, the conduit comprising a tube including an inlet and an outlet, and a wall with an interior surface and an exterior surface. The tube contains a variation in its cross sectional area along at least a portion of its length to change a property of a fluid flowing adjacent the wall of the tube. An oxidation catalyst is deposited on at least a portion of the tube.

Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

Abstract: A combustor liner assembly includes an outer shell made of a ceramic composite and an inner heat shell that is supported within the outer shell. The inner heat shield defines a surface that is exposed to combustion gases. The inner heat shield is made of material that is compatible with the ceramic matrix composite and that provides favorable thermal gradient capability for a combustion chamber.

Abstract: A combustor for a turbine engine includes an outer liner having a row of circumferentially distributed outer combustion air holes and an inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners each include at least a major air hole having a first hole size, an intermediate air hole having a second hole size, and a minor air hole having a third hole size. The first, second, and third hole sizes are all different from each other.

Abstract: A combustor assembly includes an inner and an outer liner defining a combustion chamber. The inner and outer liner includes a plurality of cooling holes that are spaced a specified distance apart. The cooling holes include a specified inclination angle and circumferential angle. A first group of cooling holes is spaced apart according to a uniform geometric pattern and density. A second group disposed between the first group and some structural feature within the liner assembly is disposed at a non-uniform pattern and a hole density equal to the density of the first group of cooling holes. The non-uniform cooling hole arrangement increases cooling flow effectiveness to accommodate local disturbances and thermal properties.

Abstract: A combustor assembly includes an inner and outer liner defining a combustion chamber. The inner and outer liners include a plurality of cooling holes spaced a specified distance apart. The cooling holes include first, second and third groups. The first group of cooling holes is the most densely spaced, followed by the second group and then the third group. The first group of cooling holes begin upstream of a leading edge of a large opening and terminates downstream of the leading edge. The increased density of cooling holes adjacent the large openings provide increased cooling airflow in areas where cooling may be affected by local disturbances in cooling airflow.

Abstract: A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. Bluff body fuel injectors are along the bulkhead.

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

Abstract: A combustor heat shield panel is secured relative to a combustor shell so as to hold the panel exterior surface spaced apart from and facing the shell interior surface over major area of the panel exterior surface. A gap is formed between the heat shield exterior surface and shell interior surface along at least a major portion of the perimeter of the heat shield.

Abstract: A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated cold side 32. A projection projects from an origin 36 at the shield portion to a terminus 38 remote from the shield portion. The terminus includes a protective coating 64 along at least a portion of its length.

Abstract: A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. In longitudinal section, a first portion of the combustor interior volume converges from fore to aft and a second portion, aft of the first portion converges from fore to aft more gradually than the first portion.

Abstract: A combustor for a gas turbine engine is provided which includes a plurality of liner segments and a support shell. The support shell includes an interior and an exterior surface, a plurality of mounting holes, and a plurality of impingement coolant holes extending through the support shell. Each liner segment includes a panel and a plurality of mounting studs. The panel includes a face surface and a back surface, and a plurality of normal or inclined coolant holes extending therethrough. The back surface of the panel has a surface profile for improving the heat transfer properties of a liner segment without substantial increase in pressure drop across the combustor.

Abstract: A method for casting a workpiece comprising the steps of applying a protective coating to a base core the base core comprising, a metal strip comprising a generally planar expanse, a plurality of tabs arranged in a pattern upon the metal strip each of the tabs comprising a base end, a terminus end, and a tab shaft extending from the base end to the terminus end wherein each of the tabs is angularly displaceable about each the base end of the tabs, injecting a molding substance about the tabs of the base core, encapsulating the base core in a shell, removing the molding substance, casting the base core, and removing the base core.