Abstract: A process for separating a Cs or C6 alkanediol from a crude product stream comprising the Cs or C6 alkanediol, light contaminants and heavy contaminants comprising one or more of: a C 10 or C 12 linear ester, or a C 10 or C 12 cyclic acetal or ketal is disclosed. The process comprises feeding the crude product stream to a separation system comprising a first distillation zone, to which the crude product stream is fed and from which the heavy contaminants are removed in a heavies stream taken as a bottom stream, and a second distillation zone, in which the Cs or C6 alkanediol is separated from a reaction product, comprising one or more of: a Cs or C6 cyclic ester, or a Cs or C6 aldehyde, formed in the first distillation zone and from which the Cs or C6 alkanediol is withdrawn in a refined product stream.

Abstract: An assembly for an aircraft propulsion system includes a propulsor rotor and a guide vane structure. The guide vane structure includes a plurality of guide vanes. The guide vane structure is disposed axially next to the propulsor rotor. The guide vanes include a first guide vane. The first guide vane includes a camber line, a leading edge, a trailing edge, an inner end, an outer end, at least one leading edge section and a trailing edge section. The first guide vane extends longitudinally along the camber line from the leading edge to the trailing edge. The leading edge section forms a respective portion of the leading edge and is arranged radially along the trailing edge section between the inner end and the outer end. The trailing edge section forms the trailing edge. The leading edge section is configured to translate longitudinally along the camber line.

Abstract: A system including a engine having a low spool and a high spool, a first hybrid electric motor connected to the low spool and a second hybrid electric motor connected to the high spool. An auto-throttle controls an amount of power provided to the engine responsive to at least one aircraft parameter. A power splitting algorithm implemented between the auto-throttle and at least one of the first and second hybrid electric motors determines a power split dividing the total engine power into the power produced by burning fuel and electrical power provided to the at least one of the first and second hybrid electric motors responsive to control signals from the auto-throttle.

Abstract: An engine system of an aircraft includes an energy storage system, a gas turbine engine, and a controller. The gas turbine engine includes a low spool, a high spool, a low-spool generator operably coupled to the low spool, and a high-spool electric motor operably coupled to the high spool. The controller is configured to detect a braking condition of the aircraft, transfer power from the low-spool generator to the energy storage system based on the storage capacity state of the energy storage system, and transfer power to the high spool through the high-spool electric motor to support combustion in the gas turbine engine while a rotational speed of the low spool is reduced responsive to the low-spool generator extracting energy from the low spool.

Abstract: A laser hole drilling system includes a laser source that generates a laser beam along an optical axis; a spherical lens along the optical axis downstream of the laser source; and a control system in communication with the spherical lens and the laser source, the control system operable to locate the spherical lens with respect to the laser source to produce a light distribution in polar coordinates of a real portion of the Fourier Transform to generate an asymmetric teardrop shaped energy distribution at a focal plane.

Abstract: An apparatus is provided for an aircraft propulsion system. This apparatus includes an airfoil and an electric heater. The airfoil includes a fiber-reinforced composite and an exterior surface. The fiber-reinforced composite includes a plurality of fibers embedded within a matrix. The electric heater includes an electric heating element. The electric heater is configured to melt and/or prevent ice accumulation on the exterior surface. The electric heating element is integrated with the fibers and embedded within the matrix.

Abstract: An open rotor gas turbine engine includes a gearbox and a fan blade system coupled to the gearbox. The fan blade system includes a hub and a plurality of fan blades affixed to the hub. At least one of the fan blades includes a blade body and a break line formed within the blade body at a location that divides the blade body into sections having parametrically defined masses. The break line has less rigidity than surrounding portions of the blade body that surround the break line. The blade body of at least one fan blade is configured to break into the sections when subjected to an excessive stress.

Abstract: An aircraft propulsion system includes at least one bearing system that includes a bearing member that supports rotation of the engine shaft. The bearing member is disposed within a bearing chamber and receives lubricant. An air seal controls a leakage flow into the bearing chamber and a breather air collection system cleans air exhausted from the bearing chamber. The breather air collection system including a deoiler for removing entrained lubricant from the air.

Abstract: A gas turbine engine with split variable fan exit guide vanes including a fan duct supporting a circumferential pattern of split variable fan exit guide vanes, the split variable fan exit guide vanes comprising an upper section and a lower section, the upper section and the lower section each being adjustable about an axis extending along a span of each of the split variable fan exit guide vanes; an upper actuator in operative communication with the upper section, the upper actuator configured to independently adjust an incidence angle of the upper section responsive to predetermined gas turbine operating conditions; and a lower actuator in operative communication with the lower section, the lower actuator configured to independently adjust an incidence angle of the lower section responsive to the predetermined gas turbine operating conditions.

Abstract: A gas turbine engine with variable fan exit guide vanes including a fan duct supporting a circumferential pattern of variable fan exit guide vanes, the variable fan exit guide vanes being adjustable about an axis extending along a span of each of the variable fan exit guide vanes; and an actuator in operative communication with the variable fan exit guide vanes, the actuator configured to independently adjust an incidence angle of each of the variable fan exit guide vanes responsive to predetermined gas turbine operating conditions.

Abstract: A hybrid propulsion update system includes a controller in signal communication with a replaceable battery. The controller includes a tuning parameters storage unit configured to store at least one tuning parameter corresponding to the replaceable battery. The controller is configured to execute at least one optimization algorithm that utilizes the tuning parameters to control operation of the hybrid electric aircraft according to a first performance. The tuning parameters storage unit is configured to receive at least one updated tuning parameter from a controller updating device. The controller executes the at least one optimization algorithm that utilizes the at least one updated tuning parameter such that the hybrid electric aircraft operates according to a second performance that improves upon the first performance.

Abstract: An open rotor gas turbine engine includes a gearbox and a fan blade system coupled to the gearbox. The fan blade system includes a hub and a plurality of fan blades affixed to the hub. At least one of the fan blades includes a blade body and a break line formed within the blade body at a location that divides the blade body into sections having parametrically defined masses. The break line has less rigidity than surrounding portions of the blade body that surround the break line. The blade body of at least one fan blade is configured to break into the sections when subjected to an excessive stress.

Abstract: Methods and systems for monitoring operation of hybrid electric engines of aircraft. The methods include monitoring a motor condition of an electrical power system associated with an engine condition using a motor sensor, wherein the electrical power system comprises an electric machine operably coupled to at least one shaft of an engine core, wherein the electric machine is configured to at least one of add power to the at least one shaft and extract power from the at least one shaft, receiving motor data from the motor sensor at a motor controller, wherein the motor controller is configured to control operation of, at least, the electric machine, analyzing the motor data to determine the presence of a fault in the engine core, and, when a fault is detected, performing a fault response action.

Abstract: A system including a engine having a low spool and a high spool, a first hybrid electric motor connected to the low spool and a second hybrid electric motor connected to the high spool. An auto-throttle controls an amount of power provided to the engine responsive to at least one aircraft parameter. A power splitting algorithm implemented between the auto-throttle and at least one of the first and second hybrid electric motors determines a power split dividing the total engine power into the power produced by burning fuel and electrical power provided to the at least one of the first and second hybrid electric motors responsive to control signals from the auto-throttle.

Abstract: A hybrid propulsion update system includes a controller in signal communication with a replaceable battery. The controller includes a tuning parameters storage unit configured to store at least one tuning parameter corresponding to the replaceable battery. The controller is configured to execute at least one optimization algorithm that utilizes the tuning parameters to control operation of the hybrid electric aircraft according to a first performance. The tuning parameters storage unit is configured to receive at least one updated tuning parameter from a controller updating device. The controller executes the at least one optimization algorithm that utilizes the at least one updated tuning parameter such that the hybrid electric aircraft operates according to a second performance that improves upon the first performance.

Abstract: An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.

Abstract: A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool, a high speed spool, and a combustor; a lubrication circuit comprising a bearing compartment, a supply pump, and a scavenger pump; an electric motor configured to augment rotational power of the low speed spool or the high speed spool; and a controller operable to: control the electric motor based upon a pressure differential between an interior of the bearing compartment and an exterior of the bearing compartment and to drive rotation of the low speed spool and/or the high speed spool via the electric motor responsive to a thrust command while fuel flow to the combustor is inhibited.

Abstract: A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.

Abstract: Methods and systems for monitoring operation of hybrid electric engines of aircraft. The methods include monitoring a motor condition of an electrical power system associated with an engine condition using a motor sensor, wherein the electrical power system comprises an electric machine operably coupled to at least one shaft of an engine core, wherein the electric machine is configured to at least one of add power to the at least one shaft and extract power from the at least one shaft, receiving motor data from the motor sensor at a motor controller, wherein the motor controller is configured to control operation of, at least, the electric machine, analyzing the motor data to determine the presence of a fault in the engine core, and, when a fault is detected, performing a fault response action.

Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a plurality of upstream airfoils, a plurality of downstream airfoils, a sensor, an actuator and a controller. The upstream airfoils include a first upstream airfoil. The downstream airfoils are arranged downstream of and adjacent the upstream airfoils. The downstream airfoils include a first downstream airfoil. The sensor is arranged with the first upstream airfoil. The sensor is configured to provide sensor data indicative of a parameter for the first upstream airfoil. The actuator is coupled to the first downstream airfoil. The controller is configured to signal the actuator to move the first downstream airfoil based on the sensor data.