Abstract: A fuel nozzle assembly includes a premix chamber, an air flow divider extending radially and axially within the premix chamber between an inner wall and an outer wall and a plurality of guide vanes disposed within the premix chamber. One or more of the guide vanes includes a fuel port in fluid communication with the flow divider. The fuel nozzle assembly further includes a premix plate that extends radially between the inner and outer walls and circumferentially between first and second side walls downstream from the fuel ports. The premix plate includes an upstream side axially spaced from a downstream side and a plurality of passages that provide for fluid flow from the premix chamber through the premix plate.

Abstract: A combustor dome heat shield has a heat shield panel adapted to be mounted to a combustor dome with a back face of the heat shield panel in spaced-apart facing relationship with an inner surface of the combustor dome to define an air gap between the heat shield panel and the combustor dome. Rails extend from the back face of the heat shield panel across the air gap. An anti-rotation notch is defined in at least one of the rails for receiving an anti-rotation tab of an adjacent element, such as a fuel nozzle floating collar. The rails include notch cavity rails extending on either side of the anti-rotation notch. The notch cavity rails define a notch cavity for capturing coolant air leaking through the anti-rotation notch.

Abstract: A thrust reverser of an aircraft comprises a blocker door and a variable area fan nozzle (VAFN) panel configured to conceal the blocker door from a duct associated with a bypass fan flow when the VAFN panel is in a closed position.

Abstract: Methods and apparatus to vary reverse thrust of turbofans are disclosed. An example cascade apparatus disclosed herein includes a fixed frame having a plurality of fixed vanes coupled to the frame, where each of the fixed vanes defines a plurality of slots. A plurality of movable vanes intersects the fixed vanes to form a reverse thrust flow path and slidably coupled to the fixed vanes via the slots. The movable vanes slide relative to the fixed vanes between a first position to provide a first reverse thrust and a second position to provide a second reverse thrust different from the first reverse thrust.

Abstract: A turbomachine includes a compressor having an inter-stage gap between adjacent rows of rotor blades and stator vanes. A combustor is connected to the compressor, and a turbine is connected to the combustor. An intercooler is operatively connected to the compressor, and includes a first plurality of heat pipes that extend into the inter-stage gap. The first plurality of heat pipes are operatively connected to a first manifold, and the heat pipes and the first manifold are configured to transfer heat from the compressed airflow from the compressor to heat exchangers. A cooling system is operatively connected to the turbine, and includes a second plurality of heat pipes located in the turbine nozzles. The second plurality of heat pipes are operatively connected to a second manifold, and the heat pipes and the second manifold are configured to transfer heat from the turbine nozzles to the heat exchangers.