An energy supply system includes an electrolysis system to perform electrolysis on a first source of water, and break the water into hydrogen and oxygen components. The hydrogen and oxygen components are supplied to a power generation system. The power generation system includes a combustor receiving the hydrogen and oxygen components and is operable to combust the hydrogen and oxygen components. The combustor also receives a source of steam. Products of combustion downstream of the combustor pass over a top turbine rotor, driving the top turbine rotor to rotate. A first generator generates electricity from the rotation of the top turbine rotor.
Baffles (126) for installation within airfoils include a baffle body (1004, 704, 804) defining a feed cavity (420) and extending between inner and outer diameter (316) ends. A forward standoff shelf (812) is formed along an exterior surface of the baffle (126, 302) and defined by a depression, bend, or channel in a material of the baffle body (1004, 704, 804) extending between the inner and outer diameter (316) ends. The forward standoff shelf (812) is configured to engage with a forward rail (502) of the airfoil body (402, 702, 704, 802), and an aft standoff shelf (814) is formed along an exterior surface of the baffle body (1004, 704, 804) and configured to engage with an aft rail (504) of the airfoil body (402, 702, 704, 802). A surface of the baffle body (1004, 704, 804) between the forward standoff shelf (812) and the aft standoff shelf (814) defines a side channel surface extending in a radial direction along the baffle body (1004, 704, 804) between the outer diameter end (430, 506, 706, 914) and the inner diameter end (432, 508, 708, 916).
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix; a topcoat; and a porous interlayer disposed between the topcoat and the bond coat. The porous interlayer has a porosity that is greater than a porosity of the topcoat. A slurry composition for applying an interlayer to an article and method of applying a top coat to an article are also disclosed.
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix. At least about 10 % of the gettering particles are in a crystalline phase. The article also includes a top coat. An article is also disclosed.
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
C04B 35/14 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silica
C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C04B 41/50 - Coating or impregnating with inorganic materials
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix; and a topcoat including a constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS). An article and a method applying a calciummagnesium- alumino-silicate (CMAS)-resistant topcoat are also disclosed.
A gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gaspath side and an internal side that borders a cooling air cavity. The external combustion gaspath side has an associated combustion gas flow direction there along. An array of cooling holes extends through the silicon-containing ceramic wall and connects the internal side with the external combustion gaspath side. The cooling holes are oriented to discharge cooling air to the external gaspath side in a direction counter to the combustion gas flow direction.
A redox flow battery includes a cell that has first and second electrodes and an ion-exchange layer there between, first and second circulation loops that are fluidly connected with, respectively, the first and second electrodes, first and second electrolyte storage tanks in, respectively, the first and second circulation loops, first and second electrolytes contained in, respectively, the first and second circulation loops, and a Raman spectrometer on at least one of the first or second circulation loops for determining a state-of-charge of at least one of the first or second electrolytes. The Raman spectrometer includes a laser source that is rated to emit a laser of a wavelength of 694 nanometers to 1444 nanometers.
Aircraft engines and methods of operation include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section. A core condenser is arranged downstream of the turbine section of the core assembly along the core flow path, the core condenser being configured to condense water from the core flow path. A refrigeration system is operably coupled to the core condenser and configured to direct a cold stream flow path into thermal interaction with the core flow path at the core condenser and configured to control a delta temperature at which heat exchange occurs between the core flow path and the cold stream flow path.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F02C 7/16 - Cooling of plants characterised by cooling medium
F02C 7/224 - Heating fuel before feeding to the burner
F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422 defining a plenum 424. An airfoil 402 extends radially inward from the platform on a side opposite the forward and aft rails and includes a leading edge cavity 412 that is open at the platform. A platform feed structure 426 is arranged on the platform about the leading edge cavity 412 and in the plenum 424 and defines a fluid path through the forward rail 420 and into the leading edge cavity 412. A cover plate 726 is arranged on a top surface of the platform feed structure 426 and configured to fluidly separate the plenum of the platform from the leading edge cavity and define a turning plenum. The cover plate 726 defines a turning contour surface that is shaped to turn an airflow from an axial flow direction to a radial flow direction.
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422, wherein the interior platform surface, the forward rail, and the aft rail define a plenum 424, an airfoil 402 extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity 412 and a baffle 416 installed within the leading edge cavity, and a platform feed structure 426 arranged on the platform 404 in the plenum 424 and defining a fluid path through the forward rail 420 and into the baffle 416 of the leading edge cavity 412.
Aircraft propulsion systems and aircraft are described. The aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and an expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the expander, prior to being injected into the burner for combustion.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/224 - Heating fuel before feeding to the burner
An apparatus has: a first member (120); a shaft (40; 50) rotatable relative to the first member about an axis; and a seal system (100). The seal system has a seal carrier (150) having: an axially-extending wall (156) having an inner diameter (ID) surface (160); and a radially-extending wall (154) having a first surface (158). A seal (102) is carried by the first member and has: an outer diameter (OD) surface (206); and a seal face (106). A seat (104) is carried by the shaft and has a seat face (108) in sliding sealing engagement with the seal face. One or more springs (132) bias the seal carrier relative to the first member so as to bias the seal face against the seat face. A key (240; 280; 300; 338) spans an interface between the seal carrier and the seal.
A method for producing a ceramic matrix composite component is disclosed. The method includes providing a plurality of first ceramic fiber plies including a plurality of interconnected tows and a plurality of first pores positioned between adjacent tows. The method includes applying a plurality of first ceramic particles within the plurality of first pores. Next, the method includes applying a plurality of second ceramic fiber plies onto an outer surface of the plurality of first ceramic fiber plies. The second ceramic fiber plies include a plurality of interconnected tows and a plurality of second pores positioned between adjacent tows. The method then includes applying a plurality of second ceramic particles within the plurality of second pores. Further, the plurality of second ceramic particles are larger than the plurality of first ceramic particles. Lastly, the method includes densifying the ceramic matrix composite preform to form the ceramic matrix composite component.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
Disclosed herein is a composite co-fiber comprising a plurality of ceramic tows; one or more sacrificial yarns; where the sacrificial yarns are operative to undergo dissolution, decomposition or melting upon being subjected to an elevated temperature; and wherein the sacrificial yarns leave open spaces in the co-fiber upon being subjected to decomposition, dissolution or melting.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C04B 38/06 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof by burning-out added substances
C22C 49/02 - Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
C22C 49/14 - Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
16.
POLYMER YARNS FOR FABRIC STABILITY AND UNIFORMITY, PLIES MANUFACTURED THEREFROM AND ARTICLES COMPRISING THE SAME
Disclosed herein is a composite ply comprising fill and warp tows; or optional axial and bias tows; wherein one or more of the fill tows and/or the warp tows or wherein one or more of the optional axial and/or bias tows comprise a polymer yarn while the remaining portion of the fill tows and/or the warp tows or the remaining portion of the bias and/or optional axial tows comprise the polymer yarn; and wherein the polymer yarn is melted to bond to the fill or warp tows to prevent removal from the ply.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
C04B 35/01 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides
C04B 35/515 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides
17.
SACRIFICAL YARN FILAMENT FOR USE IN CERAMIC MATRIX COMPOSITES AND METHODS OF MANUFACTURE THEREOF
Disclosed herein is a composite tow comprising a plurality of ceramic filaments; one or more sacrificial yam filaments; where the sacrificial yarn filaments are operative to undergo decomposition or melting upon being subjected to an elevated temperature; and wherein the sacrificial yarn filaments leave open spaces in the tow upon being subjected to decomposition, dissolution or melting; where the filaments have an average filament diameter of 5 to 15 micrometers.
Disclosed herein is a ceramic matrix composite comprising a preform comprising a plurality of plies; a ceramic matrix encompassing the plies and distributed through the plies; and thermally conducting particles distributed through the ceramic matrix. Disclosed herein is a method comprising distributing thermally conducting particles between plies in a preform; infiltrating chemical vapors of a ceramic precursor into the plies; and reacting the ceramic precursor to form a matrix.
B05D 3/10 - Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by other chemical means
B23B 7/02 - Automatic or semi-automatic machines for turning of stock
19.
METHOD FOR MACHINING CERAMIC WORKPIECE WITH COMPOSITE VIBRATION
A method for machining a ceramic workpiece includes providing a sonotrode that has a transducer and a horn arranged along an axis, and the horn has helical slots and terminates at a tip, bringing the tip into proximity of the ceramic workpiece and providing an abrasive media to a work zone around the tip, using the transducer to produce ultrasonic vibration that axially propagates down the horn and causes axial vibration at the tip, and the helical slots convert a portion of the axial vibration to torsional vibration at the tip, and the axial vibration and the torsional vibration causing the abrasive media to abrade the ceramic workpiece in the work zone and thereby remove a localized portion of the ceramic workpiece.
B06B 3/04 - Processes or apparatus specially adapted for transmitting mechanical vibrations of infrasonic, sonic or ultrasonic frequency involving focusing or reflecting
In a redox flow battery (RFB), the base solvent of the electrolytes tends to migrate across the barrier layer from one electrode toward the other. This can result in a volume and concentration imbalance between the electrolytes that is detrimental to battery efficiency and capacity. Compatible electrolytes can be mixed to rebalance the system, but for incompatible electrolytes mixing is not a viable option. To this end, the RFB herein includes a separator that recovers base solvent from the vapor phase of one of the electrolytes and returns the recovered base solvent to the other electrolyte to thereby reverse the imbalance.
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
22.
HYDROGEN POWERED GEARED TURBOFAN ENGINE WITH REDUCED SIZE CORE ENGINE
A turbine engine system includes an aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply line configured to supply hydrogen fuel from the at least one hydrogen fuel tank into the burner for combustion. The turbine engine system has a bypass ratio between 5 to 20.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/16 - Cooling of plants characterised by cooling medium
A preform comprising a first sub-laminate comprising a plurality of layers and a second sub-laminate comprising a plurality of layers. The first sub-laminate comprises a first unit cell comprising a first volume fraction of tows, where the first volume fraction of tows comprise first tows having a first tow spacing between successive first tows. The second sub-laminate comprises a second unit cell comprising a second volume fraction of tows, where the second volume fraction of tows comprise second tows having a second tow spacing between successive second tows. The first volume fraction of tows in the first unit cell is equal to the second volume fraction of tows in the second unit cell. The second tow spacing is less than the first tow spacing.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 19/06 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica next to a fibrous or filamentary layer
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
A ceramic matrix composite laminate comprises a ceramic matrix that encapsulates a plurality of layers. Each layer comprises fibers. Each layer comprises a plurality of fill fibers and a plurality of warp fibers or a plurality of bias fibers. The outermost layer contains a different concentration of fibers per unit volume than a layer located near an interior of the ceramic matrix composite laminate. A gradient in the number of fibers exists between the outermost layer and the layer located at the interior of the ceramic matrix composite laminate, or a combination thereof. A combined ceramic matrix composite comprises a plurality of composite laminates; wherein each laminate has a different fiber concentration gradient from another laminate that it is in contact with.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 19/06 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica next to a fibrous or filamentary layer
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
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.
A method of applying a coating to a substrate includes forming a slurry by mixing elemental precursors of gettering particles, diffusive particles, matrix material, and a carrier fluid; applying the slurry to a substrate; and sintering the slurry to form a composite material. The sintering causes the elemental precursors to react with one another to form gettering particles. An article is also disclosed.
C23C 16/22 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the deposition of inorganic material, other than metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A redox flow battery includes a redox flow cell and a supply and storage system external of the redox flow cell. The supply and storage system includes first and second electrolytes for circulation through the redox flow cell. The first electrolyte is a liquid electrolyte having electrochemically active manganese species with multiple, reversible oxidation states in the redox flow cell. The electrochemically active manganese species may undergo reactions that cause precipitation of manganese oxide solids. The first electrolyte includes an inhibitor that limits the self-discharge reactions. The inhibitor includes an oxoanion compound.
A method for configuring a fixture for use in machining of sequential parts via a machine tool, for a planned machining movement of the machining element, uses a model of the part and fixture. Respective reaction forces at the plurality of part contact references are computed. Responsive to computation of a negative reaction force at a said part contact reference, a modification is made to a machining parameter.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)
In a method for forming an abradable material (36), the abradable material has at least 20% by volume rutile titania (44) and hBN (46). The method includes: blending a first titania powder having an oxygen debit of at least 5.0% with a second titania powder having an oxygen debit, if any, of less than 1.0%. The blend is thermal sprayed. The sprayed blend is then oxidized.
C04B 35/46 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on titanium oxides or titanates
C04B 35/20 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in magnesium oxide
C04B 35/22 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in calcium oxide
C04B 35/462 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on titanium oxides or titanates based on titanates
C04B 35/583 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on boron nitride
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
Disclosed is a heat exchanger having: an inlet manifold configured to receive a cooling fluid; a reservoir; first and second condenser arms connected between and that respectively fluidly couple the inlet manifold to the reservoir, so that fluid received at the inlet manifold travels from the inlet manifold into the reservoir; and an outlet pump having a pump inlet port coupled to the reservoir and having a pump outlet port, wherein the inlet manifold, the reservoir, the first and second condensers, in combination, form a continuous shape.
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
31.
HEADER GUIDING FLUID FLOW TO AND FROM COOLING CHANNELS IN A HIGH DENSITY MOTOR
A header for an electric machine that include a stator core and one or more windings that include coolant passages formed therein. The header includes an inlet to receive a coolant, an outlet though which the coolant exits the header, an inlet plenum fluidly connected to the inlet, and an outlet plenum fluidly separated from the inlet plenum and fluidly connected to the outlet. The inlet and outlet plenums each have a varying cross section that varies from a top of the header as compared to a bottom of the header.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
A stator includes a stator hub, a plurality of stator teeth extending from stator hub that define a stator slot and at least one winding disposed in the stator slot, the winding including a cooling passage formed therein through. The cooling passage is connected to an inlet plenum and an outlet plenum. The stator can also include coil separators that include cooling passages.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
Electric motors and stators thereof are described. The stators of the electric motors include a first header, a second header fluidly connected to the first header, a plurality of windings fluidly connected to the first header and the second header to receive a cooling fluid passing from the first header to the second header along one or more flow channels, and one or more phase-change material elements arranged to thermally interact with at least one of the first header, the second header, the one or more flow channels, and the plurality of windings.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 9/20 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil wherein the cooling medium vaporises within the machine casing
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
A method for maintaining a redox flow includes draining a first battery electrolyte solution from a redox flow battery cell, the cell including a separator layer arranged between a first electrode and a second electrode, a first circulation loop configured to provide the first battery electrolyte solution to the first electrode and a second circulation loop configured to provide a second battery electrolyte solution to the second electrode; and flowing a non-battery electrolyte solution through the first electrode. The non-battery electrolyte removes at least a portion of the solid precipitates from at least one of the first electrode and the separator layer. The method also includes draining the non-battery electrolyte solution from the cell and returning the first battery electrolyte solution to the cell. A method for a redox flow battery and a redox flow battery are also disclosed.
A method for a redox flow battery includes using a cell of a redox flow battery to store electrical energy and discharge the stored electrical energy. The using includes circulating a first electrolyte solution through a first circulation loop in fluid connection with the first electrode of the cell; circulating a second electrolyte solution through a second circulation loop in fluid connection with the second electrode of the cell; and at least one of a first element from the first electrolyte solution in the first electrode permeates through the separator layer and precipitates as a first solid product in the second electrode and a second element from the second electrolyte solution permeates through the separator layer and precipitates a second solid product in the first electrode. The method also includes removing at least a portion of the first solid product or the second solid product from the first electrode and the second electrode, respectively.
C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A coated substrate has a substrate and a coating system having one or more ceramic layers. At least a first layer of one of the one or more ceramic layers is a columnar layer having as-deposited columns and intercolumn gaps. The intercolumn gaps have a mean width at least one of: at least 4.0 micrometers; and at least 1.5% of a thickness of said first layer.
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C04B 35/50 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare earth compounds
C22C 19/03 - Alloys based on nickel or cobalt based on nickel
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.
A heat exchanger plate provides heat transfer between a first flow along a first flowpath and a second flow along a second flowpath. The heat exchanger plate has a substrate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal portion having a plurality of inlet ports along the first flowpath and a plurality of outlet ports along the first flowpath; and a plurality of passageways along the first flowpath. Each passageway extends between a respective associated said inlet port of the plate and a respective associated said outlet port of the plate.
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28F 3/00 - Plate-like or laminated elements; Assemblies of plate-like or laminated elements
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/12 - Elements constructed in the shape of a hollow panel, e.g. with channels
An alloy that may include nickel, aluminum from 4.8 wt.% to 5.15 wt.%;cobalt from 18 wt.% to 19 wt.%, chromium from 11.9 wt.% to 12.9 wt.%, molybdenum from 2.8 wt.% to 3.6 wt.%, and niobium from 0.05 wt.% to 0.1 wt.%. The alloy may further include tungsten from 0.05 wt.% to 0.1 wt.%. The alloy may further include tantalum from 0.05 wt.% to 0.1 wt.%.
A heat exchanger for providing thermal energy transfer between a first flow along a first flowpath and a second flow along a second flowpath has a plate bank having a plurality of plates, each plate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. An inlet manifold has at least one inlet port and at least one outlet port. An outlet manifold has at least one outlet port and at least one inlet port. The first flowpath passes from the at least one inlet port of the inlet manifold, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet manifold.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/08 - Elements constructed for building-up into stacks, e.g. capable of being taken apart for cleaning
B21D 53/04 - Making other particular articles heat exchangers, e.g. radiators, condensers of sheet metal
F28F 1/26 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending transversely the means being integral with the element
F28F 9/26 - Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators
F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
A turbine engine has: a first member (22) having a surface bearing an abradable coating, the abradable coating (36) being at least 90% by weight ceramic; and a second member (24) having a surface bearing an abrasive coating. The abrasive coating (56) has a metallic matrix (64) and a ceramic oxide abrasive (66) held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
B01J 21/06 - Silicon, titanium, zirconium or hafnium; Oxides or hydroxides thereof
C04B 35/20 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in magnesium oxide
C04B 35/5831 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on boron nitride based on cubic boron nitride
A turbine engine includes a duct defining an annular passage, at least two heat exchangers arranged within the annular passage and spaced circumferentially apart, a passage between the at least two heat exchangers, and a forward flow control device operable for controlling airflow through the passages.
A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.
A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.
A method of manufacturing a component includes forming an inner wrap about a mandrel. The inner wrap has first and second walls joined by a base portion and an outer wall. A rod is arranged at each of the first and second walls. An outer wrap is formed about the inner wrap and the rods to form a body. Features are formed in the first and second walls.
An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the face sheet. The face sheet has elongated slots that extend along respective slot centerlines in the plane of the face sheet. The slot centerlines are sloped at oblique angles to the central axis.
An airfoil for a gas turbine engine includes an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets.
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
F04D 29/26 - Rotors specially adapted for elastic fluids
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
patents
