Abstract: A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.

Abstract: A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine.

Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.

Abstract: A gas turbine engine includes a static structure which includes a first fluid passage and a rotatable shaft. A bearing assembly supports the rotatable shaft relative to the static structure. The bearing assembly includes an outer race with a damper passage that extends between the static structure and the outer race. A second fluid passage extends from the damper passage to a seal.

Abstract: A gas turbine engine includes a first spool, a second spool, a primary combustor, and a diffuser. The first spool includes a first compressor rotationally driven by a first turbine via a first shaft. The second spool includes a second compressor driven by a second turbine via a second shaft. The first compressor, the diffuser, and the primary combustor are arranged in series to provide a compressed airflow discharged from the first compressor to the primary combustor via the diffuser, which includes walls that diverge towards the primary combustor. The second compressor is fluidly coupled to the diffuser to receive at least a portion of the compressed airflow from the diffuser. The second turbine is fluidly coupled to the diffuser to discharge an expanded airflow to the diffuser.

Abstract: A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine.

Abstract: A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine.

Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.

Abstract: A cooling system for a component of a gas turbine engine includes a first airflow passage configured to direct a first airflow to a mixing chamber and a second airflow passage to configured direct a second airflow to the mixing chamber, the second airflow having a higher temperature than the first airflow, and a cooling airflow passage to direct a cooling airflow from the mixing chamber to the component, the cooling airflow comprising the first airflow and the second airflow. The airflow passages are configured and sized to allow an amount of cooling airflow for unrestricted engine operation. When the first airflow passage is disabled, the second airflow passage and cooling airflow passage are configured and sized to allow an amount of cooling airflow which is adequate to permit continued safe engine operation restricted to within only a portion of its normal parameters and operating envelope.

Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least one heat exchanger configured to incrementally generate cooling air for at least one of an aft compressor stage and a foremost turbine stage relative to fluid flow through the turbine section.

Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least one heat exchanger configured to incrementally generate cooling air for at least one of an aft compressor stage and a foremost turbine stage relative to fluid flow through the turbine section.

Abstract: A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine.

Abstract: A gas turbine engine comprises a fan rotor driven by a fan drive turbine, the fan drive turbine also rotating with one of a ring gear, an intermediate gear carrier, and a sun gear. A first compressor is driven by another of the ring gear, the intermediate gear carrier, and the sun gear. A second turbine rotates with the third of the ring gear, the intermediate gear carrier, and the sun gear.

Abstract: A system for maintaining a position of a bearing compartment in a gas turbine during disassembly of a low-pressure turbine of the gas turbine engine includes a forward annular shaft defining an engine centerline axis. The system includes a ring radially inward from and engaged with an inner diameter surface of the forward annular shaft. An aft annular shaft is radially inward from the forward annular shaft and aft of the ring. The ring is connected to a forward end of the aft annular shaft for common rotation therewith. The ring retains the aft annular shaft during disassembly. The system includes a stack nut axially held between an aft facing shoulder of the forward annular stub shaft and a forward facing surface of the ring to retain the stack nut during disassembly.

Abstract: An example method of decontaminating a fuel reactant stream for a fuel cell flows the fuel reactant stream through a fluidized ammonia dissolving media, while simultaneously flowing water through the fluidized ammonia dissolving media to separate contaminants from the fuel reactant stream into a separated contaminant and water stream. The separated contaminant and water stream from the fluidized bed is accumulated within an accumulator, circulated through a water-control loop, and decontaminated by flowing the stream through an ion exchange bed secured in fluid communication with the water-control loop. A decontaminated water stream from the ion exchange bed is circulated back through the ammonia dissolving media. A temperature of the fuel reactant stream is controlled upstream of the fuel reactant stream entering the separator scrubber to produce a predetermined temperature of the fuel reactant stream passing through the separator scrubber.

Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.

Abstract: A gas turbine engine includes a core engine section which includes a compressor section and a core turbine section. The core engine is configured to rotate about a core axis. A drive turbine is configured to rotate about a drive turbine axis. A bypass passage connects an intake to the gas turbine engine directly with an exhaust of the drive turbine.

Abstract: A gas turbine engine has a main compressor section. A turbine section has a variable vane positioned upstream of a rotor blade, and the variable vane is provided with an actuator operable to control an orientation of the variable vane. A tap line taps air from the compressor section, and passes the tapped air through a cooling compressor. The cooling compressor is a fixed flow compressor. Air downstream of the cooling compressor is delivered into the turbine section.

Abstract: A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine.

Abstract: A thermal priority fuel cell power plant includes a cell stack assembly for generating an electrical power output. The cell stack assembly includes an anode, a cathode, and a waste heat recovery loop. The waste heat recovery loop is configured to remove waste heat generated from the electrochemical reaction and is thermally coupled to the cell stack assembly for managing the waste heat of the cell stack assembly and for supplying thermal power to a thermal load demand. The waste heat recovery loop includes a heat exchanger in heat exchange relationship with the coolant outlet conduit and the thermal load demand. A controller is operatively associated with the cell stack assembly and the waste heat recovery loop. The controller controls the operation of the cell stack assembly by adjusting a fuel cell power plant parameter responsive to the thermal load demand.