Abstract: The present invention contemplates an apparatus for forming a combustion mixture in a gas turbine engine. In one form, the apparatus includes a diffuser having at least two flowpath structures spaced apart to define a flowpath for directing fluid flow. At least one of the flowpath structures includes a flowpath surface and a plurality of edges disposed along a trailing end portion of the flowpath surface. The edges extend perpendicularly from the flowpath surface and are arranged generally parallel to the fluid flow to define a plurality of corners. A fluid vortex is generated as the fluid flow rolls over each of the corners. A spray ring is disposed along a trailing edge of one of the flowpath structures and is integrally attached to the diffuser. The spray ring includes a plurality of fuel delivery apertures adapted to spray fuel into respective ones of the fluid vortices to form the combustion mixture.

Abstract: A cast heat exchanger, having an inlet and an outlet and defining an internal passage therebetween, includes a wall structure disposed within the internal passage that defines a series of interconnected chambers through which a cooling medium flows in a serpentine path. The outer surface of the heat exchanger is covered with pin fins that transfer heat away from the hot working medium flowing over the pin fins and into the cooling medium within the chambers of the heat exchanger.

Abstract: The present invention contemplate a seal assembly for reducing the passage of fluid between a combustor liner and a turbine vane segment in a gas turbine engine. In one embodiment, the turbine vane segment has a lip portion defining a sealing surface. A seal element having first and second seal portion is coupled to the turbine vane segment by a support element. The support element urges the first seal portion into engagement with an aft edge of the combustor liner and positions the second seal portion adjacent the sealing surface of the turbine vane segment, while allowing relative movement between the second seal portion and the sealing surface in a direction substantially parallel to the sealing surface.

Abstract: A combustor apparatus for a gas turbine engine includes a combustor liner support having an annular dome panel and a plurality of load transfer members extending axially therefrom. The dome panel maintains inner and outer combustor liners in spaced relation to define a combustion chamber. The load transfer members extend into a diffuser flowpath defined by inner and outer flowpath structures which are interconnected by a plurality of struts. Each of the load transfer members surrounds at least a portion of a corresponding strut to shield the strut from fluid flowing through the diffuser flowpath.

Abstract: A high temperature capable flange is disclosed where the use of bolts is minimized or eliminated. The flange is intended for use in a gas turbine engine extending generally along a central axis. The loads between a hanger and an inner case, a hanger and a seal, or between all three are transmitted through pin arrangements that are substantially radially located. The hanger, inner case and seal all include generally ring shaped portions that are at least partially overlapping. The ring shaped portions of the components may have a variety of radially overlapping cavities for receiving the pins in different arrangements.