Abstract: A heat management system for a turbomachine may include a first heat exchanger configured and arranged to receive a first fluid stream from a first duct, a second heat exchanger configured and arranged to receive the first fluid stream after discharging from the first heat exchanger, and a hatch configured to provide fluid communication from a second duct to the first duct so as to introduce a second fluid stream from the second duct to the first duct. A method of cooling fluid streams may include directing a first fluid stream from a first duct across or through a first heat exchanger, directing the first fluid stream across or through a second heat exchanger after discharging from the first heat exchanger, and directing a second fluid stream from a second duct to the first duct, with the second fluid stream flowing through a hatch configured to provide fluid communication from the second duct to the first duct.

Abstract: A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

Abstract: An ejector is presented. The ejector includes a primary fluid inlet to receive a primary fluid. The ejector further includes a secondary fluid inlet to receive a secondary fluid. Furthermore, the ejector includes a nozzle fluidly coupled to the primary fluid inlet and the secondary fluid inlet. The nozzle includes a secondary pilot inlet to receive at least a portion of the secondary fluid from the secondary fluid inlet, and a nozzle outlet including a plurality of primary openings for discharging the primary fluid and a secondary opening for discharging the secondary fluid. A turbo-machine having the ejector is also presented.

Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.

Abstract: A heat exchanger includes a core defining a first passageway configured for a first fluid to flow through and a second passageway configured for a second fluid to flow through. The core includes a plurality of unit cells coupled together. Each unit cell of the plurality of unit cells includes a sidewall at least partly defining a first passageway portion, a second passageway portion, a plurality of first openings for the first fluid to flow through, and a plurality of second openings for the second fluid to flow through. Each unit cell of the plurality of unit cells is configured to enable the first fluid to combine and divide in the first passageway portion. Each unit cell is further configured to enable the second fluid to combine and divide in the second passageway portion.

Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.

Abstract: A heat exchanger includes a heat exchanger core, a header defining a header manifold, and a transition portion that provides fluid communication between the heat exchanger core and the header manifold. The transition portion includes a transition tube extending between the header and the heat exchanger core, a header junction where the transition tube joins the header, and a splitting junction that splits the transition tube into the plurality of heat exchange tubes. The header junction may define elliptical inlet apertures, a large filleted joint, and a junction thickness that is greater than a header wall thickness.

Abstract: An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.

Abstract: The present disclosure provides fluid eductors, systems that utilize fluid eductors, and methods of entraining a suction fluid flow using a fluid eductor. Exemplary fluid eductors include a concentric eductor space or a plurality of annular eductor spaces. Exemplary methods include ejecting a volume of motive fluid out of a concentric eductor space of a fluid eductor, accelerating a peripheral region of the suction fluid flow with the motive fluid ejecting out of the first annular eductor space, and accelerating a core region of the suction fluid flow with the motive fluid ejecting out of the second annular eductor space.

Abstract: A system for heat exchange and leak detection is generally provided, the system including a heat exchanger including a first wall defining a first passage containing a first fluid. A leak detection enclosure containing a leak detection medium is defined between the first wall and a second wall surrounding the first wall.

Abstract: A heat exchanger assembly for a gas turbine engine that includes an outer engine case. The heat exchanger assembly includes at least one cooling channel, the at least one cooling channel is configured to receive a flow of fluid to be cooled. At least one first coolant flow duct that is configured to receive a flow of a first coolant, wherein the at least one cooling channel is disposed between a first inlet and a first outlet. The heat exchanger assembly further include at least one second coolant flow duct that is configured to receive a flow of a second coolant, wherein the at least one cooling channel is disposed between a second inlet and a second outlet.

Abstract: A gas turbine engine assembly includes a turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order; a fuel delivery system operable with the combustion section of the turbomachine for providing fuel to the combustion section of the turbomachine; and an air cycle assembly including an air cycle machine and a heat exchanger, the air cycle machine in airflow communication with the compressor section of the turbomachine and the heat exchanger in airflow communication with the air cycle machine. The gas turbine engine assembly also includes a thermal transfer bus thermally coupling the heat exchanger of the air cycle assembly to the fuel delivery system for transferring heat from the air cycle machine to the fuel delivery system.

Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.

Abstract: A gas turbine engine includes an outer nacelle; a fan at least partially surrounded by the outer nacelle; and a turbomachine drivingly coupled to the fan and at least partially surrounded by the outer nacelle. The outer nacelle defines a bypass airflow passage with the turbomachine. The turbomachine includes a compressor section defining in part a core air flowpath. The turbomachine also includes a heat sink heat exchanger; and a thermal management duct assembly defining a thermal management duct flowpath extending between an inlet and an outlet and positioned between the core air flowpath and the bypass airflow passage along the radial direction, the outlet selectively in airflow communication with a core compartment of the turbomachine, and the heat sink heat exchanger positioned in thermal communication with the thermal management duct flowpath for transferring heat to an airflow through the thermal management duct flowpath during operation.

Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.

Abstract: A heat engine comprising a compressor providing a flow of compressed air from a core flowpath of the heat engine; a cooled cooling air (CCA) heat exchanger system to which the flow of compressed air is provided from the compressor; a coolant supply system providing a flow of coolant to the CCA heat exchanger in thermal communication with the flow of compressed air at the CCA heat exchanger, in which the coolant supply system and CCA heat exchanger together define a CCA circuit through which the compressed air flows in thermal communication with the coolant; and a hot section disposed downstream of the compressor section along the core flowpath through which combustion gases flow, in which the hot section defines a secondary flowpath through which the flow of compressed air from the CCA heat exchanger is provided.

Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.

Abstract: A cooling system for use with a turbine engine. The system includes a coolant reservoir configured to store cooling fluid therein, and a cooling device coupled in flow communication with the coolant reservoir, wherein the cooling device is configured to cool heated components of the turbine engine with the cooling fluid. The system further includes a first valve configured to control flow of the cooling fluid from the coolant reservoir towards the cooling device, and a controller coupled in communication with the first valve. The controller is configured to monitor an operational status of the turbine engine, and actuate the first valve into an open position after the turbine engine has been shut down such that the cooling fluid cools the heated components.

Abstract: A gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath. The gas turbine engine also includes a thermal management system including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section, the turbine section, or the exhaust section such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath.

Abstract: A gas turbine engine includes a combustion section and a compressor section, the compressor section including a high pressure compressor. The high pressure compressor includes an aft-most compressor stage and an upstream compressor stage, each of the aft-most compressor stage and the upstream compressor stage including a rotor disk. The gas turbine engine also includes a high pressure spool assembly, the high pressure spool assembly including a rotor disk, and an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage of the high pressure compressor to define in part a compressor cooling air passage outward of the airflow member along a radial direction.