Abstract: Methods of cleaning flow path components of power systems, and sump purge kits used in the same or related methods are disclosed. A method of cleaning may include removing a casing of the turbine system to expose a rotor of the turbine system, a plurality of flow path components coupled to the rotor and/or the casing, and a sump system in communication with the rotor. The method may also include pressurizing the sump system in communication with the rotor, and sealing a plurality of openings formed in the rotor. Additionally, the method may include exposing the rotor and the plurality of flow path components to steam to dry hydrocarbons formed on a surface of the rotor and a surface of the plurality of flow path components, and blasting the rotor and the plurality of flow path components with solid carbon dioxide (CO2) to dislodge the dried hydrocarbons.

Abstract: The elastomeric money or wallet band is a fastening structure. The elastomeric money or wallet band comprises an elastic band and one or more negotiable instruments. The elastomeric money or wallet band is configured for use with the one or more negotiable instruments. The elastomeric money or wallet band binds the one or more negotiable instruments together.

Abstract: A method for removing ink and/or a foreign material different from ink from the surface of an article, wherein at least a part of the surface of the article comprises a polymer, the method includes: i) providing an ink imprinted article and/or an article having a surface covered at least partly by a foreign material different from ink; ii) contacting the article provided in step i) with an acid having a pKa in the range from ?10 to 7 having a minimum concentration of 1 wt.-% for solving the ink and/or the foreign material different from ink or their degradation products in the acid; iii) separating the acid and the therein dissolved ink- and/or foreign material different from ink or their degradation products from the article to obtain a deinked article and/or an article with a surface free from foreign material.

Abstract: Methods of cleaning flow path components of power systems, and sump purge kits used in the same or related methods are disclosed. A method of cleaning may include removing a casing of the turbine system to expose a rotor of the turbine system, a plurality of flow path components coupled to the rotor and/or the casing, and a sump system in communication with the rotor. The method may also include pressurizing the sump system in communication with the rotor, and sealing a plurality of openings formed in the rotor. Additionally, the method may include exposing the rotor and the plurality of flow path components to steam to dry hydrocarbons formed on a surface of the rotor and a surface of the plurality of flow path components, and blasting the rotor and the plurality of flow path components with solid carbon dioxide (CO2) to dislodge the dried hydrocarbons.

Abstract: A method may include cold spraying a masking material on selected locations of a component to form a masking layer, wherein the masking material comprises a metal or alloy; additively manufacturing an additively manufactured portion of the component at locations at which the masking layer is not present; and removing the masking layer from the component. The masking layer may be configured to protect portions of the component by covering or otherwise providing a physical barrier that reduces or prevents material from adhering to unwanted portions of the component during a subsequent manufacturing and/or repair technique. Additionally, the masking layer may be reflective to infrared radiation and/or intimately contact the component and function as a heat sink or thermally conductive layer to transfer heat from the component.

Abstract: In some examples, systems and techniques for repairing or otherwise forming a blade of a bladed disk. In one example, a method including positioning a shield member around a perimeter of a partial blade extending from a rotor disk of a bladed disk, the shield member being positioned adjacent to a build surface of the partial blade; and depositing, with the shield member around the perimeter of the partial blade, a material on the build surface using an additive manufacturing technique to form a repaired portion on the build surface of the partial blade.

Abstract: A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.

Abstract: The present disclosure provides, at least in part, methods and compositions for in vivo fusosome delivery. In some embodiments, the fusosome comprises a combination of elements that promote specificity for target cells, e.g., one or more of a re-targeted fusogen, a positive target cell-specific regulatory element, and a non-target cell-specific regulatory element. In some embodiments, the fusosome comprises one or more modifications that decrease an immune response against the fusosome.

Abstract: Methods and systems for speech signal processing an interactive speech are described. Digitized audio data comprising a user query from a user is received over a network in association with a user identifier. A protocol associated with the user identifier is accessed. A personalized interaction model associated with the user identifier is accessed. A response is generated using the personalized interaction model and the protocol. The response is audibly reproduced by a voice assistance device.

Abstract: This disclosure provides, e.g., cytobiologic compositions and methods of use thereof. The cytobiologics can be used, e.g., to deliver a protein or nucleic acid to a target cell.

Abstract: Methods and systems for speech signal processing an interactive speech are described. Digitized audio data comprising a user query from a user is received over a network in association with a user identifier. A protocol associated with the user identifier is accessed. A personalized interaction model associated with the user identifier is accessed. A response is generated using the personalized interaction model and the protocol. The response is audibly reproduced by a voice assistance device.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

Abstract: Methods and systems for speech signal processing an interactive speech are described. Digitized audio data comprising a user query from a user is received over a network in association with a user identifier. A protocol associated with the user identifier is accessed. A personalized interaction model associated with the user identifier is accessed. A response is generated using the personalized interaction model and the protocol. The response is audibly reproduced by a voice assistance device.

Abstract: Methods of cleaning flow path components of power systems, and sump purge kits used in the same or related methods are disclosed. A method of cleaning may include removing a casing of the turbine system to expose a rotor of the turbine system, a plurality of flow path components coupled to the rotor and/or the casing, and a sump system in communication with the rotor. The method may also include pressurizing the sump system in communication with the rotor, and sealing a plurality of openings formed in the rotor. Additionally, the method may include exposing the rotor and the plurality of flow path components to steam to dry hydrocarbons formed on a surface of the rotor and a surface of the plurality of flow path components, and blasting the rotor and the plurality of flow path components with solid carbon dioxide (CO2) to dislodge the dried hydrocarbons.

Abstract: An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.

Abstract: An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: A receptacle device which detects when mail has been delivered to the receptacle using a pressure sensor, IR beam, and/or a magnetic sensor. The receptacle device is connected to a wireless or wired network and is configured to communicate with a smart home system at the delivery point. The receptacle detects mail delivery and communicates this information via a network bridge to the smart home device of the recipient. The network bridge also gathers information from an informed delivery system which includes information regarding and images of mailpieces being delivered for a given day. The network bridge sends images of mailpieces which were delivered and additional mailpiece information to the recipient on the smart home system. For parcel, the network bridge can receive information regarding parcels to be delivered and can provide delivery estimates and visual tracking on a map.