Dehns

A method of manufacture is provided during which a first material layer (62A) is disposed with a second material layer (64) to provide a multi-layered preform (60). The first material layer (62A) lengthwise and widthwise overlaps the second material layer (64). The first material layer (62A) is configured from or otherwise includes a titanium material. The second material layer (64) is configured from or otherwise includes an aluminum material. The multi-layered preform (60) is clamped between a first die (66) and a second die (68). The first die (66) and the second die (68) each lengthwise and widthwise overlap the multi-layered preform (60). The multi-layered preform (60) clamped between the first die (66) and the second die (68) is sintered and bonded to provide a bipolar plate (36; 38) for a fuel cell (28). The titanium material in the first material layer (62A) of the bipolar plate (36; 38) is bonded to the aluminum material in the second material layer (64) of the bipolar plate (36; 38) during the sintering of the multi-layered preform (60).

A liquid desiccant (LD)-based dehumidification system (601) is provided for heating, ventilation, air conditioning and refrigeration (HVAC&R) systems. The LD-based dehumidification system (601) includes a tank (610) containing LD (611), a contact media device (620) including media (621) for disposition in a flow of air to be dehumidified and a sump (622) disposed below the media (621) to receive LD (611) drained from the media (621), a pump and valve system (630) to pump the LD (611) from the tank (610) to the contact media device (620) to wet the media (621) and from the sump (622) to the tank (610), a heat exchanger (640) through which LD (611), which is pumped from the sump (622) to the tank (610), flows, a sensing system (650) to sense one or more conditions of the LD (611) and a controller (780) to control the pump and valve system (630) in accordance with a system status and the one or more conditions of the LD (611).

An additive manufacturing apparatus (100) includes a chamber (110), a controller (140) including processing circuitry and a memory (144), the controller (140) operable to determine an expected life of an additive manufactured part (130), by receiving an initial part design and initial additive manufacturing parameters and 1) utilizing a machine learning model trained on historic images to estimate grain structure based upon the initial part design and initial additive manufacturing parameters, 2) manufacturing a part (130) by additive manufacturing based upon the initial part design and initial additive manufacturing parameters, and monitoring for the location of likely defects during the manufacturing based upon sensed information during the manufacturing, 3) inferring potential defects' associated shapes, sizes, and morphologies, combining 2) and 3) to reach a defect map, superimposing the defect map on the grain structure and determining an expected life of the part (130) based upon the superimposed defect map and grain structure. A method is also disclosed.

An additive manufacturing machine (100) forms a part (130) utilizing additive manufacturing and with a plurality of layers. A controller (140) includes processing circuitry and a memory (144), and is operable for receiving design information about a proposed part (130) to be manufactured utilizing additive manufacturing, and also receives proposed process parameters for the additive manufacturing machine (100). The controller (140) is operable to predict a temperature at each of a plurality of layers that will be found in the proposed part (130), and identify a temperature history for a plurality of the layers including identifying the time to solidify for at least one of the plurality of layers, and determine a derivative of a change in temperature of the at least one of the plurality of layers over time and predicting grain structure utilizing the derivative. The controller (140) is operable to determine an expected life based upon the predicted grain structure. A method is also disclosed.

A method for improvement of T6 probes accuracy based on swirl angle includes predicting a swirl angle of a gas turbine engine (102a, 102b) based on a power of the gas turbine engine (102a, 102b) and a delta value. The method includes determining an error value of an exhaust temperature (T6) of the gas turbine engine (102a, 102b) based on the predicted swirl angle and a correlation function (400) of swirl angle to error. Also, the method includes compensating a measured value of the T6 based on the error value.

A ceramic matrix composite (CMC) component (200) for a turbine engine includes a base (210) having a radial outer surface (212) and a radial inner surface inward surface (215). The base includes a plurality of ceramic fiber plies and a ceramic matrix. A forward flange structure (220) and an aft flange structure (230) each extend from the radial outer surface of the base. A splash plate (270) is positioned between the forward flange structure and the aft flange structure to direct cooling air flowing from a forward end of the base to an aft end of the base towards the radial outer surface of the base. The splash plate has a first end proximate the forward flange structure, a second end proximate the aft flange structure, and an inner surface facing the radial outer surface of the base and including a curved surface region (275) that curves towards the outer radial surface of the base. The CMC component is a blade outer air seal (BOAS). A BOAS assembly includes a plurality of the BOAS segments arranged to form an annular shaped structure. A method of assembling the CMC component includes: providing the CMC component and providing the splash plater plate. The turbine engine includes a fan section (22), a compressor section (24), a combustion chamber (56), and a turbine section (28). The turbine section includes at least one rotor and one or more turbine blade(s) extending radially outwardly from the at least one rotor; the blade outer air seal assembly positioned between the one or more turbine blade(s); and an outer casing (36).

A ceramic matrix composite (CMC) component (200) for a turbine engine (20) includes at least one cooling cavity (260) having a cooling cavity opening (262) and defined by side walls (264) and a cavity bottom wall (266), and a cover plate (270) covering the cooling cavity opening (262). The cover plate has one or more cooling air inlets (275, 285) to permit cooling air to flow from a region above the cover plate into the cooling cavity. The cover plate further has one or more walls (280) extending downward from an inner surface of the cover plate to the cavity bottom wall thereby dividing the cooling cavity into a plurality of cooling channels or cooling subcavities (290, 292, 295), and/or creating a circuitous cooling pathway within the cooling cavity (260).The CMC component is a blade outer air seal (BOAS) segment. A BOAS assembly comprising a plurality of the BOAS segments arranged to form an annular shaped structure.A method of controlling cooling air flow within a CMC component for a turbine engine includes providing the CMC component; and covering the cooling cavity opening of the cooling cavity with the cover plate.The turbine engine includes a fan section (22), a compressor section (24), a combustion chamber (26), and a turbine section (28), the turbine section (28) including at least one rotor and one or more turbine blade(s) extending radially outwardly from the at least one rotor; and the blade outer air seal assembly positioned between the one or more turbine blade(s) and an outer casing to the engine.

A multi-mode blade tip timing sensor (100; 200) includes a housing (201), a sensing coil (205) provided within the housing (201) and a powered exciter coil (207). The multi-mode blade tip timing sensor (100; 200) can operate in a first, sensing mode, and a second, de-icing mode. When operating in the first, sensing mode, a first current is provided to the powered exciter coil (207) to create a magnetic field such that a movement of one or more moving metallic fan blades (109) through the magnetic field creates a signal in the sensing coil (205). When operating in the second, de-icing mode, a second current is provided to the powered exciter coil (207) to induce an eddy current in a tip of the one or more moving metallic turbine fan blades (109), wherein the eddy current raises a temperature of the one or more moving metallic turbine fan blades (109) above an icing temperature.

A ceramic matrix composite (CMC) component (400) for a turbine engine (20) includes a base (410) having a radial outer surface (412) and a radial inner surface (415), a cooling cavity (460) within the base that extends from the radial outer surface (412) of the base into an interior region of the base, the cooling cavity having a cooling cavity opening (462) at the outer radial surface of the base and being defined by cavity side walls ( 464) and a cavity bottom wall (466), and a cover plate (200) covering the cooling cavity opening of the cooling cavity. The cover plate comprises an edge region (210) around the perimeter of the cover plate which is in contact with the base and a central recessed region (220) which extends into the cooling cavity. The central recessed region is defined by side walls (230) and a bottom wall (240) wherein each side wall of the central recessed region is spaced from a corresponding cavity side wall (464) and the bottom wall of the central recessed region is spaced from the cavity bottom wall. The central recessed region has a plurality of cooling air inlets (250) to permit cooling air to flow from a region above the cover plate into the cooling cavity. The CMC component is a blade outer air seal (BOAS) segment. A BOAS assembly comprising a plurality of the BOAS segments arranged to form an annular shaped structure. A method of controlling cooling air flow within a CMC component for a turbine engine includes providing the CMC component; and covering the cooling cavity opening of the cooling cavity with the cover plate. The turbine engine includes a fan section (22), a compressor section (24), a combustion chamber (26), and a turbine section (28), the turbine section (28) including at least one rotor and one or more turbine blade(s) extending radially outwardly from the at least one rotor; and the blade outer air seal assembly positioned between the one or more turbine blade(s) and an outer casing to the engine.

A home energy management system (HEMS) includes a power supply configured to provide alternating current (AC) power, at least one load electrically connected to the power supply, and a modular multi-level (MMC) converter configured to receive power from the power supply and to supply a regulated converter output to the at least one load. The MMC includes one or more converter branches and a filter. The converter branch is in signal communication with the power supply and includes a plurality of bridge cells. Each bridge cell includes a plurality of power switches and a battery. The filter is electrically connected between the at least one load and the at least one converter branch. The filter is configured to reduce harmonic distortion and highfrequency noise in the converter output.