Abstract: A system includes a recirculation line, a mainline flow meter operable to measure a flowrate of fluid flowing through the recirculation line, a mixing chamber, an inlet line coupled between the recirculation line and the mixing chamber, at least one chemical injection port coupled to the inlet line, a dedicated feed pump operably associated with each chemical injection port, and an outlet line coupled between the mixing chamber and the recirculation line. The mixing chamber includes a plurality of mixing zones, a mixing blade assembly that includes at least one blade within each mixing zone, and a motor coupled to the mixing blade assembly and operable to rotate the mixing blade assembly. Each of the dedicated feed pumps is coupled to a separate chemical supply and is operable to pump a chemical to the corresponding chemical injection port for injection into the inlet line.

Abstract: A thermal relief device (1) is described comprising a housing (2) having an inlet (3) and an outlet (4) connected by a relief channel (5). Such a thermal relief device should have a simple construction. To this end a microporous structure (10) is arranged between inlet (3) and outlet (4).

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 turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

Abstract: A method is described for producing a pneumococcal capsular polysaccharide protein conjugate in which one or more activated pneumococcal polysaccharides of particular pneumococcal serotypes and carrier protein are separately lyophilized, the separately lyophilized polysaccharides and carrier protein are separately reconstituted in an organic solvent, and the reconstituted polysaccharide and carrier protein are then combined together by Tee-mixing and conjugated together to produce polysaccharide carrier protein conjugates. A plurality of conjugates, each comprising polysaccharides of a particular serotype, may be used to produce multivalent pneumococcal immunogenic compositions having a combination of conjugates for use in vaccines.

Abstract: The present invention relates to Polysaccharide Size-Reduction Monitoring Methods useful for the non-invasive, and accurate monitoring of the progress of a polysaccharide size-reduction process.

Abstract: An assembly for use in a bearing compartment having an axis includes a bearing outer race configured to be located in the bearing compartment. The assembly further includes at least one annular spring positioned in the bearing outer race and being asymmetric in at least one of the axial direction or the circumferential direction relative to the axis to reduce the likelihood of amplification of vibration experienced by the at least one annular spring.

Abstract: A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

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: 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 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: A ground-based cryogenic cooling system includes a means for cooling an airflow and producing chilled air responsive to a power supply. A liquid air condensate pump system is operable to condense the chilled air into liquid air and urge the liquid air through a feeder line. A cryogenic cartridge includes a coupling interface configured to detachably establish fluid communication with the feeder line and a cryogenic liquid reservoir configured to store the liquid air under pressure. The cryogenic cartridge can be coupled to a cryogenic liquid distribution system on an aircraft. The liquid air can be selectively released from the cryogenic cartridge through the cryogenic liquid distribution system for an aircraft use.

Abstract: An assembly for use in a bearing compartment having an axis includes a bearing outer race configured to be located in the bearing compartment. The assembly further includes at least one annular spring positioned in the bearing outer race and being asymmetric in at least one of the axial direction or the circumferential direction relative to the axis to reduce the likelihood of amplification of vibration experienced by the at least one annular spring.

Abstract: A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

Abstract: A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

Abstract: A propulsion system includes an electric fan propulsion motor with a plurality of propulsion motor windings. The propulsion system also includes a means for controlling a flow rate of a working fluid through a cryogenic working fluid flow control assembly to the propulsion motor windings. The propulsion system further includes a controller operable to control supplying a pre-cooling flow of the working fluid from a cryogenic liquid reservoir through the cryogenic working fluid flow control assembly to the propulsion motor windings.

Abstract: A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

Abstract: The present invention provides immunogenic compositions having one or more polysaccharide-protein conjugates in which polysaccharides obtained from bacterial capsules are conjugated to diphtheria toxin fragment B (DTFB) or a variant thereof. The immunogenic compositions may be multivalent pneumococcal polysaccharide conjugate compositions in which polysaccharides from one or more Steptococcus pneumoniae serotypes are conjugated to diphtheria toxin fragment B (DTFB) and, optionally, additional polysaccharides from one or more different Steptococcus pneumoniae serotypes are conjugated to one or more other carrier proteins.

Abstract: The invention is related to multivalent immunogenic compositions comprising more than one S. pneumoniae polysaccharide protein conjugates, wherein each of the conjugates comprises a polysaccharide from an S. pneumoniae serotype conjugated to a carrier protein, wherein the serotypes of S. pneumoniae are as defined herein. In some embodiments, at least one of the polysaccharide protein conjugates is formed by a conjugation reaction comprising an aprotic solvent. In further embodiments, each of the polysaccharide protein conjugates is formed by a conjugation reaction comprising an aprotic solvent. Also provided are methods for inducing a protective immune response in a human patient comprising administering the multivalent immunogenic compositions of the invention to the patient. The multivalent immunogenic compositions are useful for providing protection against S. pneumoniae infection and diseases caused by S. pneumoniae.

Abstract: The present invention provides immunogenic compositions having one or more polysaccharide-protein conjugates in which one or more polysaccharides from Streptococcus pneumoniae bacterial capsules are conjugated to a carrier protein in an aprotic solvent such as dimethylsulfoxide (DMSO). The present invention also provides methods for providing an enhanced immune response to a pneumococcal polysaccharide protein conjugate vaccine comprising administering to a human subject an immunogenic composition comprising polysaccharide-protein conjugates prepared in DMSO conditions.