110results about How to "Minimizes gradient" patented technology

Apparatus for permanent placement across an ostium of a left atrial appendage in a patient, which includes a filtering membrane configured to extend across the ostium of the left atrial appendage. The filtering membrane has a permeable structure which allows blood to flow through but substantially inhibits thrombus from passing therethrough. The apparatus also includes a support structure comprising a plurality of fingers which are radially outwardly expandable with respect to a longitudinal axis to permanently engage the interior wall of the left atrial appendage, wherein the filtering membrane is attached to the support structure extending across the ostium of the left atrial appendage.

A method, apparatus and assembly related to solid oxide fuel cell interconnects is disclosed. In its broadest embodiment, the invention contemplates a multi-layered ceramic interconnect having integrated flow fields and electrical connections. The method of making this interconnect includes judicious selection of materials, formation of appropriate apertures for the flow fields and electrical connectors, and the joining of the layers through a firing and / or sealing process.

A turbine airfoil usable in a turbine engine and having at least one cooling system. The cooling system may be positioned in an outer wall of the turbine airfoil, and the airfoil may include a hot gas receiving cavity positioned in a mid-chord region of the airfoil. The hot gas receiving cavity may have an opening in a tip of the airfoil to enable hot gases to circulate into the hot gas receiving cavity. In at least one embodiment, the cooling system in the outer wall and the hot gas receiving cavity may include a plurality of ribs. Cooling fluids may be passed through the cooling system in the outer wall, and hot combustion gases may be passed into the hot gas receiving cavity to moderate the temperature of the inner portions of the outer wall to reduce the temperature gradient in the outer wall.

A two-stage high pressure turbine comprises a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Apparatus for permanent placement across an ostium of a left atrial appendage in a patient, which includes a filtering membrane configured to extend across the ostium of the left atrial appendage. The filtering membrane has a permeable structure which allows blood to flow through but substantially inhibits thrombus from passing therethrough. The apparatus also includes a support structure attached to the filtering membrane which retains the filtering membrane in position across the ostium of the left atrial appendage by permanently engaging a portion of the interior wall of the left atrial appendage. The support structure may be radially expandable from a first configuration to a second configuration which engages the ostium or the interior wall of the left atrial appendage. The filtering membrane may define an opening therethrough that is configured to expand from a first size which inhibits the passage of thrombus therethrough to a second size which allows an interventional device, e.g., an expansion balloon, to pass therethrough, and wherein the opening is resiliently biased towards the first size.

An integrated air foil and ammonia injection grid provides a plurality of air foils across a flue conveying flue gas. Each air foil has a leading curved edge and a tapered, pointed, trailing end. At least one injection pipe is positioned inside each air foil, and has at least one nozzle for injecting ammonia into the flue gas flowing across the air foils. Preferably, plural injection tubes are provided and positioned one behind the other in each air foil, and each injection tube in a given air foil has a length different than a length of the other injection tubes in the same air foil. A longest injection tube in a given air foil is located furthest downstream and proximate the tapered trailing edge and a shortest injection tube in the same air foil is located furthest upstream, remaining injection tubes in the same air foil being progressively shorter the further upstream any injection tube is located. Apertures may be provided on opposed lateral sides of the air foils for introducing a gas flow into the flue gas passing across the air foils. Ammonia flow to each injection pipe may be individually controlled.

A two-stage high pressure turbine includes a first stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

The present invention relates generally to tuning the flow of cooling air across converter and inverter heat sinks in a motor drive system. More specifically, present techniques relate to motor drive duct systems having parallel cooling air duct channels dedicated to providing cooling air for a converter heat sink and an inverter heat sink, respectively. In particular, a first duct channel through an inverter duct and a converter duct is dedicated to providing cooling air to the converter heat sink without cooling the inverter heat sink, whereas a second duct channel through the inverter duct and the converter duct is dedicated to providing cooling air to the inverter heat sink without cooling the converter heat sink.

A turbine engine component, such as a turbine blade, has an airfoil portion having a pressure side wall and a suction side wall, a first cooling circuit embedded within the pressure side wall, which first cooling circuit has at least two passageways embedded within the pressure side wall, a second cooling circuit embedded within the suction side wall, which second cooling circuit has at least two passageways embedded within the suction side wall, at least one cooling fluid supply cavity located between the pressure and suction side walls, each cooling fluid supply cavity having at least one projecting portion extending between adjacent ones of the embedded passageways in the first cooling circuit or adjacent ones of the embedded passageways in the second cooling circuit, and each projecting portion communicating with at least one film cooling hole. A method for forming the turbine blade component is also described.

A method of subsurface exploration includes generating a representation of a portional volume of the Earth from a seismic measurement of a physical parameter. The method includes providing observed seismic dataset having three distinct nonzero data values derived from three distinct nonzero seismic measured values of said portional volume of the Earth, generating a predicted seismic dataset having three distinct nonzero data values, generating a nontrivial convolutional filter including three nonzero filter coefficients, generating a convolved observed dataset by convolving the convolutional filter with said observed seismic dataset, generating primary objective functions to measure the similarity between said convolved observed dataset and said predicted dataset, maximizing and / or minimizing said primary objective functions by modifying at least one filter coefficient of the convolutional filter, generating predetermined reference filters having at least three reference coefficients generating secondary objective functions to measure the similarity between filter coefficients for the nontrivial filter and reference coefficients for the predetermined reference filters, and minimizing and / or maximizing said secondary objective functions by modifying a model coefficient of a subsurface model of a portion of the Earth to produce an updated subsurface model of a portion of the Earth.

A thermal mass flow controller or mass flow meter having a novel sensor housing that reduces heat conduction from the housing mounting plate or base to the sensor itself. The housing also greatly minimizes the thermal gradient that can result from the uneven application of heat to the housing base. This reduction is accomplished in part by the use of one or more thermal isolation slots to isolate the upper portion of the housing (which holds the sensor) from the lower portion of the housing. Heat transfer to the sensor housing is also minimized by raising the middle portion of the bottom of the housing so that thermal contact is made between the base and the housing only at the two ends of the housing.

A tympanic thermometer includes a thermally conductive nozzle extending from a distal end of the thermometer. A base of a sensor can is thermally connected to the nozzle to define a path of conductive heat transfer from the nozzle to the base of the can thereby minimizing a thermal gradient between proximal and distal ends of the sensor can when temperature is measured in the ear.

The present invention provides a method for conveniently manufacturing a solid oxide fuel cell (SOFC) at a cost that is less than five-hundred dollars per kilowatt of electricity. The method comprises forming an electrode layer and depositing an electrolyte material on the surface of the electrode. The formed structure is an electrode-electrolyte bi-layer. A second electrode is deposited onto this bi-layer to form a multilayer fuel cell structure comprising an electrolyte positioned between two electrodes. This multilayer structure is then heated and fired in a single thermal cycle to remove any binder materials and sinter, respectively, the fuel cell. This thermal cycle can be performed in a furnace having one or more chambers. The chamber(s) preferably contains a variable or multiple frequency microwave source for heating the cell and removing binder materials in the electrolyte and electrode structures. The chamber(s) also preferably include a convection and / or radiation source for sintering the fuel cell. In addition, the method of the invention harmonizes and minimizes the deviation among the thermophysical properties of the electrolyte and electrode structures. This harmonization reduces and minimizes the temperature gradient within the cell such that the structure can be uniformly heated and fired during the thermal cycle. The multilayer structure is also unlikely to distort and fracture by minimizing the temperature gradient in the cell. An SOFC can also be manufactured by the present method in an order of magnitude less time than standard processes.

A compact fiber packaging system for fiber lasers is provided that comprises a series of spools nested inside one another for efficient volume utilization. The spools comprise an inner spool nested inside at least one outer spool to form a module. Generally, the fiber lasers are wrapped around the inner spool, and then around successive outer spools as required to form the module. Furthermore, the modules may be stacked to form a fiber assembly. The compact fiber packaging system further comprises devices and methods for minimizing thermal gradients between fibers and for removing Waste heat from the system. Additionally, the available volume is further utilized by disposing equipment and materials for operation of the fibers inside a hollow center defined by the inner spool, between the nested spools, and adjacent the nested spools.

The invention relates to a single crystal boron doped CVD diamond that has a toughness of at least about 22 MPa m1 / 2. The invention further relates to a method of manufacturing single crystal boron doped CVD diamond. The growth rate of the diamond can be from about 20-100 μm / h.