Abstract: A system includes a turbine with an expansion section configured to expand an exhaust flow in a downstream direction, such that the expansion section includes a plurality of stages and a diffuser section coupled downstream of the expansion section. The diffuser section receives the exhaust flow along an exhaust path and an energizing flow along a wall, and the diffuser section includes the wall comprising an inner surface, so the wall is disposed about the exhaust path, and an energizing port disposed in the wall at or downstream of a last stage of the plurality of stages of the expansion section. The energizing port is configured to direct the energizing flow along the inner surface of the wall to energize a boundary layer along the wall, and a first pressure of the energizing flow is greater than a second pressure of the exhaust flow at the energizing port.

Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.

Abstract: A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.

Abstract: A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system.

Abstract: The present application provides a modular enclosure for use with an equipment platform and a turbo-machine. The modular enclosure may include a first number of walls attached to a number of legs of the equipment platform and a second number of walls attached to the legs of the equipment platform. The first number of walls may include a number of pivotable panels. The second number of walls may include an access aperture therein. The equipment platform may provide a roof for the modular enclosure.

Abstract: The present application provides a modular enclosure for use with an equipment platform and a turbo-machine. The modular enclosure may include a first number of walls attached to a number of legs of the equipment platform and a second number of walls attached to the legs of the equipment platform. The first number of walls may include a number of pivotable panels. The second number of walls may include an access aperture therein. The equipment platform may provide a roof for the modular enclosure.

Abstract: An air intake includes a conduit, an inlet, an inlet duct, an outlet duct, an outlet, and a fan. The inlet is configured to removably couple with the fan and to direct the second airflow in a first direction. The inlet duct is coupled to the inlet and directs the second airflow in a second direction around the conduit and a third direction into a turbomachine enclosure. The outlet duct receives the second airflow from a fourth direction substantially opposite to the third direction and directs the second airflow in the second direction. The outlet is configured to removably couple with the fan and to direct the second airflow in a fifth direction. The fan within the air intake is removably coupled to the inlet or to the outlet and is configured to positively or negatively pressurize the turbomachine enclosure with the second airflow based on the fan disposition.

Abstract: A system includes a gas turbine engine and a multipurpose gas turbine engine support frame couple to the gas turbine engine. The multipurpose gas turbine support frame is configured to support the gas turbine engine during both operation and transport of the gas turbine engine.