Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, first thermal bus and heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, or each first electric machine, and the first heat exchanger. Waste heat energy transfers to the first heat transfer fluid. The first heat exchanger configures to transfer waste heat energy from the first heat transfer fluid to a dissipation medium. During steady-state operation of the first gas turbine engine, the first heat transfer fluid entering the first heat exchanger has a temperature of TFLUID(° C.), and a temperature of an inlet air flow entering the first gas turbine engine has a temperature TAIR(° C.) and a ratio B is in a range of between 5.0-18.0.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, and a first heat exchanger. Waste heat energy generated by at least one first gas turbine engine, and first electric machine, transfers to the first heat transfer fluid. The first heat exchanger directs a first proportion of the first heat transfer fluid through a first heat dissipation portion wherein a first proportion of the waste heat energy transfers to a first dissipation medium dependent on the first dissipation medium temperature and mass flow rate. The first heat exchanger directs a second proportion of the first heat transfer fluid through a second heat dissipation portion wherein the second proportion of waste heat energy transfers to a second dissipation medium dependent on the second dissipation medium temperature and mass flow rate.

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat is exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, a first thermal bus, and a first heat exchanger. The first thermal bus includes a first heat transfer fluid in a closed loop flow sequence, between the first gas turbine engine, the or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to first heat transfer fluid. When airspeed of aircraft is less than Mn0.6, the first heat exchanger transfers the waste heat energy from the first heat transfer fluid to a first dissipation medium. When the airspeed of the aircraft is greater than Mn0.6, the first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a second dissipation medium.

Abstract: A thermal management system for an aircraft includes a first gas turbine engine, first thermal bus, first heat exchanger, one or more first ancillary systems, vapour compression system, one or more second ancillary systems and second heat exchanger. A waste heat energy generated by a first gas turbine engine, and a first ancillary system, transfers to the first heat transfer fluid. A waste heat energy generated by a second ancillary system transfers to a second heat transfer fluid, and the second heat exchanger transfers the waste heat energy from the second heat transfer fluid to the first heat transfer fluid. The waste heat energy generated by a second ancillary system transfers to the first heat transfer fluid, and the first heat exchanger transfers the waste heat energy to a dissipation medium. The waste heat energy transferred to the second heat transfer fluid ranges from 20 kW to 300 kW.

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, a first heat exchanger, and one or more first ancillary systems. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the or each first electric machine, the first gas turbine engine, the first heat exchanger, and the or each first ancillary system. Waste heat energy generated by at least one of the first gas turbine engine, the or each first electric machine, and the or each first ancillary system, is transferred to the first heat transfer fluid. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

Abstract: A thermal management system for an aircraft includes a first thermal bus including one or more first heat sources, a heat sink, a vapour compression system, and one or more second heat sources. The vapour compression system includes a compressor, a condenser, a receiver, a first side of a recuperator, an expansion valve, an evaporator, a second side of the recuperator, and the compressor. A first heat flow (Q1) of waste heat energy generated by the first heat sources is transferred via the first heat transfer fluid to the heat sink. A second heat flow (Q2) of waste heat energy generated by the second heat source(s) being transferred via the evaporator to a refrigerant. A third heat flow (Q3) of heat energy in the refrigerant is transferred via the condenser to the first heat transfer fluid. The controller is configured to ensure that: 1.1*Q2<Q3<3.0*Q2.

Abstract: A flame simulating assembly is provided with a reflected flickering light that includes only one light source. Light from the light source passes through a rotating flicker element onto one or more reflectors, or mirrors, that reflect light up onto a simulated fuel bed and the some of the light is reflected off of the flicker elements towards a flame screen to create a simulated flame. The dipping flicker elements creates a fluttering light effect due to the flicker elements “intermittently dipping” into the light path. This fluctuating light is reflected onto the logs and ember bed in front and creates a dancing effect, which simulates glowing embers.

Abstract: A method for authenticating a wearable device is disclosed. The method includes: receiving, from a tokenization service provider (TSP), a signal representing a first code derived by the TSP from decrypting a security token previously provisioned in the computing device, wherein the security token was received at a terminal from the computing device and transmitted to the TSP; obtaining, based on the received signal representing the first code, a device identifier of the computing device and an identifier of an account; querying a device database to verify that the computing device is associated with a first status; verifying that the account is enabled for an operation initiated using the computing device; and transmitting an authorization message to the terminal, the authorization message authorizing the operation.

Abstract: A button for a drug delivery device with a reduced operating loudness includes a plate-like button body forming a touch surface, wherein the plate-like button body is coupled by an axial supporting member to a noise-generating interface of the drug delivery device and movable into a longitudinal direction of the drug delivery device, wherein the plate-like button body includes a material composite with at least one first component consisting of a first material and at least one second component consisting of a second material different from the first material, wherein the at least one first component and the at least one second component are coupled via at least one coupling plane that is at least sectionwise slanted or perpendicular to the longitudinal direction. Further, the disclosure describes a button assembly for a drug delivery device which is shock resistant.

Abstract: A method of verifying that a user is authorized to access a secured area via an entry point includes receiving at a first computer and from a user device associated with the user, check-in request information that includes: a membership number associated with the user and a travel event; and a lounge location. The method also includes generating a time stamp for the receipt of the check-in request; verifying that the membership number is a valid membership number; and verifying that the time stamp is within a predetermined window of time. The method also includes sending, in response to the verification, instructions from the first computer to a second computer positioned near the entry point to display a window that includes user information associated with the user.

Abstract: In one embodiment, a method includes identifying at a first powered device in communication with power sourcing equipment, a second powered device in communication with the first powered device, wherein the first powered device is receiving high voltage pulse power from the power sourcing equipment, notifying the power sourcing equipment of the second powered device at the first powered device, and performing a low voltage power initialization at the first powered device with the second powered device before passing the high voltage pulse power to the second powered device.

Abstract: As disclosed herein, a preservation system for perishable products in a display case comprises a control valve for connection to a water supply. A pressure regulator is connected to the control valve for reducing water pressure. A plurality of piezoelectric transducer nebulizers are operatively mounted to the display case in spaced apart relation to one another and are fluidically connected in series with an output of the pressure regulator to emit a dry fog. A control system comprises a controller for controlling a duty cycle of a pulse signal to vibrate the piezoelectric transducers in the plurality of nebulizers, and a timer for alternately generating an on and an off signal to periodically control the valve to supply water to the pressure regulator and to enable the controller whereby the nebulizers emit the dry fog to maintain desired relative humidity level throughout the display case.

Abstract: A method, computer system, and a computer program product for storing a write data in a storage system that operates using a log-structured filing system is provided. The present invention may include compressing a write data. The present invention may also include identifying a region of a storage system based on a first size of the compressed write data. The present invention may further include the storage system operating using a log-structured filing system. The present invention may also include a different region of the storage system having a different compression ratio. The present invention may further include writing the compressed write data in the identified region of the storage system.

Abstract: A firearm recoil mechanism is provided that includes a front spring plate integrally coupled with a Bolt Carrier Group. The front spring plate is slidably coupled with first and Second Guide Rods, where the first and Second Guide Rods extend through apertures in the front spring plate, first and second Recoil Springs engaging with the front spring plate, where the first Recoil Spring is disposed around the first Guide Rod, and where second Recoil Spring is disposed around the Second Guide Rod. A piston integrally coupled with the front spring plate and the Bolt Carrier Group. The piston and the front spring plate move with the Bolt Carrier Group in opposing directions while the first and Second Guide Rods remain stationary to coil and recoil the first Recoil Spring and second Recoil Spring on the first and Second Guide Rods, respectively.

Abstract: The present invention relates to a polymeric Mannich base useful as an epoxy curative and/or accelerator, which has an improved safety profile due to the avoidance of the use of phenol in its preparation.

Abstract: A panel television support and mounting kit allows the consumer to employ any of the three modes of support, namely stand mount, elevated console mount and wall mount. The elevated console mount incorporates a vertical spine to elevate the panel television above the console and an offset arm to support the television over an upper shelf of the console. A mounting structure is provided that can be attached to the spine or to a wall. Pivoting and tilting is accommodated by the mounting structure.

Abstract: The invention relates to a Mannich base useful as an epoxy curative agent. In particular, the present invention is directed to a Mannich base derived from furfuryl alcohol, or a homopolymer or co-polymer thereof, an epoxy resin curative composition comprising the Mannich base, a cured epoxy resin obtainable using the composition, processes for preparing the Mannich base and uses thereof.

Abstract: The present technology relates to improved device and methods of use of insulator-based dielectrophoresis. This device provides a multi-length scale element that provides enhanced resolution and separation. The device provides improved particle streamlines, trapping efficiency, and induces laterally similar environments. Also provided are methods of using the device.

Abstract: Benzodiazepine derivatives of formula (Ie) wherein one R1 and R2 is a benzodiazepinyl-containing group of formula (II) in which R8 is H or halo; the other of R1 and R2 is a group Z selected from H, C3-C6 cycloalkyl, halo, —NHR9, benzyl, phenyl, 4- to 10-membered heterocyclyl and 4- to 10-membered heteroaryl, wherein phenyl, heterocyclyl and heteroaryl are unsubstituted or substituted by one or two substituents selected from 4- to 10-membered heterocyclyl which is unsubstituted or substituted by OR, and from C1-C6 alkyl, C1-C6 hydroxyalkyl, C1-C6 haloalkyl, C3-C6 cycloalkyl, halo, —OR, —(CH2)mOR, —NR2, —(CH2)mNR2, —NHR?, —SOmNR2, —SOmR, —SR, nitro, —CO2R, —CN, —CONR2, —NHCOR, —CH2NR10R11 and —NR10R11, in which each R is independently H or C1-C6 alkyl, R? is C3-C6 cycloalkyl and m is 1 or 2; R9 is selected from phenyl and 4- to 10-membered heteroaryl wherein phenyl and heteroaryl are unsubstituted or substituted by halo; R10 and R11 are each independently H or C1-C6 alkyl; or R10 and R11 form, together with the