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Non-axisymmetric airfoil platform shaping

Tue, 26 May 2015 08:00:00 EDT

Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.



Rotor, a steam turbine and a method for producing a rotor

Tue, 26 May 2015 08:00:00 EDT

A rotor, a steam turbine having a rotor, and a method of producing a rotor are disclosed. The rotor disclosed includes a shaft high pressure section. The high pressure section includes a first high pressure section, a second high pressure section, the second high pressure section being joined to the first pressure section, and a third high pressure section, the third high pressure section being joined to the second high pressure section. At least a portion of the second high pressure section is formed of a high-chromium alloy steel comprising 0.1-1.2 wt % of Mn, up to 1.5 wt % of Ni, 8.0-15.0 wt % of Cr, up to 4.0 wt % of Co, 0.5-3.0 wt % of Mo, 0.05-1.0 wt % of V, 0.02-0.5 wt % of Nb, 0.005-0.15 wt % of N, up to 0.04 wt % of B, up to 3.0 wt % of W, and balance Fe and incidental impurities.



Integrated case and stator

Tue, 26 May 2015 08:00:00 EDT

A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.



Blower housing

Tue, 26 May 2015 08:00:00 EDT

A blower housing has a discharge direction, an axis of rotation, a polar axis that intersects the axis of rotation and is substantially perpendicular to the discharge direction, and an angular sweep of increasing fluid flow area. The fluid flow area, A, increases with increasing angular magnitude, Φ, as a function comprising at least a functional component that is at least one of (1) equal to, (2) substantially mathematically reducible to, and (3) substantially mathematically analogous to the equation, A⁡(Φ)=Aco+R(1-1-[(ri)⁢(Φ)R]2), where Aco is a minimum fluid flow area, R is a radius of a first circle, and ri is a radius of a second circle that is smaller than the first circle.



Impeller and centrifugal fan using the same

Tue, 26 May 2015 08:00:00 EDT

An impeller includes: a main plate; a shroud; and a plurality of blades provided between the main plate and the shroud and arranged circumferentially; wherein the impeller is configured to rotated about a rotation axis; wherein the plurality of blades include a pressure surface and a negative pressure surface; and the pressure surface has a shape, in which at least three types of circular arcs are connected, as viewed from a rotation axial direction. A centrifugal fan includes the above-described impeller; and three or more pillars, wherein an interval between one adjacent pillars of the three or more pillars is different from an interval between the other adjacent pillars of the three or more pillars.



Centrifugal fan

Tue, 26 May 2015 08:00:00 EDT

A centrifugal fan is provided. The centrifugal fan is configured such that an impeller having plural blades disposed between a disk-shaped main plate and an annular shroud along a circumferential direction is accommodated 5 in a casing, and that an air suctioned from a suction opening is discharged outward in a radial direction of the impeller by a centrifugal force due to a rotation of the impeller, and thereby discharging the air from the casing. The casing includes an upper plate, a lower plate, and plural supporting struts interposed between the upper plate and the lower plate, and 10 lateral sides of the casing have only the supporting struts to form a discharge opening.



Centrifugal fan

Tue, 26 May 2015 08:00:00 EDT

A centrifugal fan is provided. The centrifugal fan is configured such that an impeller having a plurality of blades along a circumferential direction and disposed between a disk-shaped main plate and an annular shroud is housed in a casing configured by an upper casing and a lower casing, and that an air suctioned from a suction opening is discharged outward in a radial direction of the impeller by a centrifugal force due to a rotation of the impeller. The shroud has a curved surface formed from an outer edge portion toward a center thereof. The shroud has a plurality of protrusions which are formed on the surface of the shroud such that a gap is formed between each of the protrusion portions and the upper casing.



Kinetic energy atom-powered engine

Tue, 26 May 2015 08:00:00 EDT

A device for converting the kinetic energy of molecules into useful work includes an actuator configured to move within a fluid or gas due to collisions with the molecules of the fluid or gas. The actuator has dimensions that subject it to the Brownian motion of the surrounding molecules. The actuator utilizes objects having multiple surfaces where the different surfaces result in differing coefficients of restitution. The Brownian motion of surrounding molecules produce molecular impacts with the surfaces. Each surface then experiences relative differences in transferred energy from the kinetic collisions. The sum effect of the collisions produces net velocity in a desired direction. The controlled motion can be utilized in a variety of manners to perform work, such as generating electricity or transporting materials.



Replaceable blade outer air seal design

Tue, 26 May 2015 08:00:00 EDT

A blade outer air seal system includes a body that extends between two circumferential sides, a leading edge and a trailing edge, and a radially inner side and a radially outer side. An attachment section associated with the body and includes at least one engagement surface that is transverse to the radially outer side.



Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine

Tue, 26 May 2015 08:00:00 EDT

A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.



Abrasive handling submersible pump assembly diffuser

Tue, 26 May 2015 08:00:00 EDT

An abrasive handling submersible pump assembly diffuser is described. An electric submersible pump assembly stage comprises a rotatable impeller, and a co-axially mounted diffuser comprising a diffuser bowl, the diffuser bowl comprising a plurality of diffuser bowl wedges having a blunted pie-shape, each of the plurality of diffuser bowl wedges protruding axially from a diffuser bowl floor into a cavity between the rotatable impeller and the co-axially mounted diffuser such that each of the plurality of diffuser bowl wedges protrudes into a path of pumped solid-laden fluid, wherein the blunted pie-shaped wedges extend radially between an inner wall and an outer wall of the diffuser bowl and a thickness of the blunted pie-shaped wedges in a circumferential direction increases towards the outer wall.



Actuator mounted to torque box

Tue, 26 May 2015 08:00:00 EDT

An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via a plurality of bolts.



Seal for a control device of a supercharger with valve means in the form of a waste gate

Tue, 26 May 2015 08:00:00 EDT

In a sealing arrangement for an control device of a charging device which sealing arrangement includes a bearing bushing in which an control shaft is rotatably supported by the bushing in a housing opening of the charging device, the control shaft is provided with a collar disposed in the housing opening at an axial end of the bushing and the collar includes a groove accommodating a seal ring which is in direct contact with the wall of the opening for sealing the shaft supported in the bushing directly with respect to the opening wall.



Turbocharger turbine

Tue, 26 May 2015 08:00:00 EDT

A turbocharger turbine which has a wastegate slide sleeve (8), which is provided in a wastegate arrangement (5) and which closes off the wastegate duct, as a shut-off element. The wastegate arrangement (5) comprises a bypass duct (6) which runs in the turbine housing (2); a wastegate duct (7) which runs in the turbine housing (2) to the turbine housing outlet (4) and which is connected via the bypass duct (6) to the turbine housing inlet (3); and a shut-off element (8) which is arranged in the turbine housing (2). The shut-off element (8) is provided to open and close the wastegate duct (7) and can be moved by means of an actuating device (9) into an open position and closed position.



Sound attenuating chimney element for a turbomachine system

Tue, 26 May 2015 08:00:00 EDT

A sound attenuating chimney element for a turbomachine system includes a high density outer body having an external surface and an internal surface, and one or more acoustic attenuation layers provided on the external surface of the outer body. The one or more acoustic attenuation layers include an outer surface portion and an inner surface portion. A structural layer is provided on the outer surface portion of the one or more acoustic attenuation layers. The structural layer includes an external surface that defines a duct configured and disposed to pass gases from the turbomachine system.



Annular flange for fastening a rotor or stator element

Tue, 26 May 2015 08:00:00 EDT

A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions.



Impingement cooling system for use with contoured surfaces

Tue, 26 May 2015 08:00:00 EDT

The present application provides an impingement cooling system for use with a contoured surface. The impingement cooling system may include an impingement plenum and an impingement plate with a linear shape facing the contoured surface. The impingement surface may include a number of projected area thereon with a number of impingement holes having varying sizes and varying spacings.



Turbocompressor and system for a supercritical-fluid cycle

Tue, 26 May 2015 08:00:00 EDT

A turbocompressor for use with a process fluid and including an axial expansion turbine for expanding the process fluid and a centrifugal compressor for compressing the process fluid. The turbine and compressor share a common shaft, all of which can be housed by a common housing that encloses sealed spaces. The axial expansion turbine has a rotor located between two main bearings, and the centrifugal compressor includes an impeller mounted to one end of the shaft. In one embodiment, the main bearings are lubricated by a portion of the process fluid so that the only fluid in the sealed spaces is the process fluid. The turbocompressor can be used in a power-cycle system that includes a heat source and, optionally, an electrical generator.



Open core continuous helical fin marine drive system

Tue, 26 May 2015 08:00:00 EDT

An open core continuous helical fin marine drive system for use with surface and subsurface marine vessels has a cylindrical fluid container nested within a nacelle enclosure having an intake port and an exhaust port tailpipe. The cylindrical fluid container is driven by a fluid container drive motor through a gear assembly including a pinion gear connected to the fluid container drive motor and an underwater ring gear connected to the cylindrical fluid container. A plurality of continuous helical fins connected along the inner wall of the cylindrical fluid container is positioned about a hollow center core and creates a horizontal centripetal fluid vortex thread along the hollow center core as the cylindrical fluid container rotates. An inflatable marine bladder is positioned aft of the cylindrical fluid container and can be engaged to an inflated configuration in order to compress the exiting water flow through the exhaust port tailpipe.



Cross flow fan, air blower and air conditioner

Tue, 26 May 2015 08:00:00 EDT

Disclosed is a cross flow fan that makes uniform a distribution of wind velocity along an axial direction of the fan at an exit of an air trunk and that lessens chance of separation of an air flow on an inlet side of the fan, and there are thereby provided a cross flow fan that accomplishes a lower input and smaller noise and an air blower and an air conditioner that use the cross flow fan. A cross flow fan being rotatably placed in a horizontally-long air trunk, and including a plurality of annular rings that are substantially parallel to each other and a plurality of blades that are radially interposed between adjacent rings, each having a circular arc cross sectional shape, and a camber angle of the blade is smaller at the ring side than at a center area of the blade between the rings in a longitudinal direction.



Rotor support thermal control system

Tue, 26 May 2015 08:00:00 EDT

Systems for thermally regulating portions of a steam turbine are disclosed. In one embodiment, a thermal control system for a rotor bearing support includes: a housing fluidly connected to an inlet and adapted to substantially enclose the rotor bearing support, the housing defining a first annular cavity adapted to receive a fluid from the inlet; and an outlet fluidly connected to the housing, the outlet adapted to receive the fluid from the annular cavity.



Methods and apparatuses for moving objects based on a buoyancy force

Tue, 26 May 2015 08:00:00 EDT

A pipe of an apparatus has a first gas in a first space and a second gas in a second space. The first gas is in the amount to generate a buoyancy force that exceeds at least a gravity force to position the apparatus in a stationary state at a predetermined distance relative to a reference surface. A fixture is coupled to the apparatus to secure the apparatus in the stationary state relative to the ground without supporting the apparatus. The first gas is lighter than the second gas. The pipe is capable of creating a flow of the second gas.



Method and apparatus for obtaining discrete axial clearance data using radial clearance sensors

Tue, 19 May 2015 08:00:00 EDT

A method and apparatus for determining axial clearance data between a rotor and a stator are disclosed. At least one radial clearance sensor is positioned on the stator and is configured to gather radial clearance data, i.e., measurements of a radial distance between the rotor and the stator taken at discrete time intervals. A computing device is operably connected with the at least one radial clearance sensor and is configured to use the radial clearance data to determine axial clearance data, i.e., an axial distance between the stator and the rotor. In one embodiment, the computing device uses, among other data points, an indication of a loss of signal from at least one radial clearance sensor to extrapolate the axial clearance data.



Heat dissipating module

Tue, 19 May 2015 08:00:00 EDT

A heat dissipating module includes a housing, a first fan and a second fan. The housing has a partition. The first fan is disposed at a side of the partition, and the second fan is disposed at the other side of the partition. The second fan has a plurality of wind deflectors, which are disposed higher than the partition.



Gas turbine engine including lift-off finger seals, lift-off finger seals, and method for the manufacture thereof

Tue, 19 May 2015 08:00:00 EDT

Embodiments of a gas turbine engine including a lift-off finger seal are provided, as are embodiments of a lift-off finger seal and embodiments of a method for the manufacture thereof. In one embodiment, the gas turbine engine includes an engine housing having low and high pressure cavities, a shaft rotatably mounted in the engine housing, and a lift-off finger seal. The lift-off finger seal includes an finger seal backing spring and an aerodynamic foil. The aerodynamic foil extends around the outer circumference of the shaft and is configured to expand radially outward in response to aerodynamic forces generated during rotation of the shaft. The finger seal backing spring resiliently biases the aerodynamic foil toward the shaft, deflects to accommodate the outward radial expansion of the aerodynamic foil, and forms an annular seal around the aerodynamic foil to impede pressurized airflow from the high to low pressure zone.



Exhaust system for steam turbine

Tue, 19 May 2015 08:00:00 EDT

An exhaust system for a steam turbine provided with an improved annular flow guide in a high or intermediate turbine. The improved flow guide reduces flow turbulence in an exhaust hood and reduces pressure loss to thereby improve turbine plant efficiency. The shape (vertically symmetric) of a flow guide 5A according to a conventional technology was modified into the shape (vertically asymmetric) of a flow guide 5 such that the length of a downstream flow guide portion 5d is greater than that of a upstream flow guide portion 5u. Numerical analyses were performed to find the optimum flow guide occupation ratio of the conventional technology and the corresponding total pressure loss coefficient. The obtained values were used as reference values. Further, the flow guide occupation ratio of the upstream flow guide portion 5u was set at 0.4 and the flow guide occupation ratio of the downstream flow guide portion 5d was set at 0.7; at values where the total pressure loss coefficient becomes lower than the reference value. The rectification effect of the flow guide can thus be enhanced.



Multiblade air blower

Tue, 19 May 2015 08:00:00 EDT

A multiblade air blower has a multiblade impeller, an orifice, an axially overlaid portion, and an airflow collision prevention device. The multiblade impeller includes a main plate and a blade. The blade is provided at the main plate to form a blade inner periphery. The orifice has an open end and an orifice inner periphery. The open end is positioned toward the main plate from a blade end face. The orifice inner periphery has an inner diameter larger than that of the blade inner periphery, and guides air to the multiblade impeller. The axially overlaid portion is a part where the orifice and the blades are overlaid. The airflow collision prevention device is provided at the blade and at an inner side of the orifice inner periphery. The multiblade air blower suppresses loss of air distribution efficiency and increased noise.



Variable geometry vane system for gas turbine engines

Tue, 19 May 2015 08:00:00 EDT

One embodiment of the present invention is a unique variable geometry vane system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and turbomachinery variable geometry vane systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.



Gas turbine engine fan drive gear system damper

Tue, 19 May 2015 08:00:00 EDT

A gas turbine engine includes a fan section, a turbine section coupled to the fan section through a geared architecture, a first member supporting the geared architecture, and a second member supporting the first member relative to an engine static structure. The first member and the second members are spaced apart from one another at a location. A damper includes opposing ends and extending between the first member and the second member at the location for limiting relative movement between the first member and the second member. A fan drive gear system and a method are also disclosed.



Method and apparatus for cooling gas turbine rotor blades

Tue, 19 May 2015 08:00:00 EDT

An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.



Flow distributed buffered/educted gas seal

Tue, 19 May 2015 08:00:00 EDT

A system, in certain embodiments, includes a seal assembly having a seal body. The seal body includes an inlet buffer port and an outlet eduction port. The inlet buffer port is configured to receive a compressed buffer gas, such as shop air, which is injected into the inlet buffer port. The compressed buffer gas blocks the flow of a compressed process gas, such as land fill gas, by opposing the flow of the compressed process gas through the seal assembly. Both the compressed buffer gas and the compressed process gas may be expelled through the outlet eduction port.



Variable blade type tidal and wind power generator with increased generation efficiency

Tue, 19 May 2015 08:00:00 EDT

Disclosed herein is a variable blade type tidal and wind power generator with increased generation efficiency. The tidal and wind power generator includes an installation frame (10), a vertical rotating shaft (20), blade installation bars (30) and (30′), support rings (40) and (40′), vertical support rods (50); rotor blades (60) and (60′), vertical support frames (70), horizontal frames (80), an installation member (20′), a support wire (50′), a blade-spreading-degree control means (90), a generation efficiency enhancing means (100) and a generation means (200) which is coupled to the lower end of the vertical rotating shaft to generate power. The tidal and wind power generator can be operated even in conditions of gentle winds or low tides regardless of the direction of the wind or the tidal flow.



Corrosive environment monitoring system and corrosive environment monitoring method

Tue, 19 May 2015 08:00:00 EDT

Provided are corrosive environment monitoring systems and methods whereby corrosive factors are measured in a steam turbine and a corrosive environment is correctly monitored. A corrosive environment monitoring system measures corrosive factors having a part in damaging and deteriorating structural members in a steam turbine and is configured in such a way that steam in the steam turbine is permitted to flow into the corrosive environment monitoring system. Furthermore, in the steam turbine, a condensing mechanism condenses steam that has flowed in and a corrosive factor measuring device is equipped with corrosive factor sensors that measure corrosive factors in condensed water generated by the condensing mechanism.



Cooled gas turbine engine member

Tue, 19 May 2015 08:00:00 EDT

A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes. The thermal fluid can be at a different temperature than the vane such that heat is transferred between the two. In one embodiment the vane forms part of an intercooler for a compressor of the gas turbine engine. The vane can have a fin disposed at the end of the heat tube to facilitate a heat transfer.



Heat dissipation module

Tue, 19 May 2015 08:00:00 EDT

A heat dissipation module includes a centrifugal fan and a heat pipe. The centrifugal fan includes an outer housing, a heat dissipation fin array, a retaining wall, an impeller and a rotation-driving device. The outer housing includes an axial air inlet, an axial air outlet and a radial air outlet. The heat dissipation fin array is located at an inner wall of the radial air outlet. The retaining wall is located on a flat wall of the outer housing on which the axial air outlet is located. The retaining wall is in contact with an inner wall of an electronic device to collectively form a circulation channel so as to guide airflows output from the axial air outlet through the flat wall with which the heat dissipation fin array is aligned, and into the axial air inlet. The heat pipe is in contact with the heat dissipation fin array.



Condenser cooling system and method including solar absorption chiller

Tue, 19 May 2015 08:00:00 EDT

A system configured to thermally regulate exhaust portions of a power plant system (e.g. steam turbine) is disclosed. In one embodiment, a system includes: a condenser adapted to connect to and thermally regulate exhaust portions of a steam turbine; and a cooling system operably connected to the condenser and adapted to supply a cooling fluid to the condenser, the cooling system including a solar absorption chiller adapted to adjust a temperature of the cooling fluid.



Suction sealing for turbocharger

Tue, 19 May 2015 08:00:00 EDT

A system can include a turbine housing that defines a turbine wheel space, an exhaust chamber in fluid communication with the turbine wheel space and a control shaft bore that extends from the exhaust chamber to an outer surface of the turbine housing; a blunt body positionable above the turbine wheel space where the blunt body includes an opening and a lumen in fluid communication with the opening; and a suction conduit connectable for fluid communication between the control shaft bore of the turbine housing and the lumen of the blunt body. Various other examples of devices, assemblies, systems, and methods are also disclosed.



Composite fan case with integral containment zone

Tue, 19 May 2015 08:00:00 EDT

A turbofan engine which has a composite fan case surrounding a fan with a plurality of fan blades is disclosed. The composite fan case includes a containment zone having an inner fabric layer composed of resin-impregnated fibers substantially uni-axially oriented in a common angular direction corresponding to a blade release angle of the fan blades. The fan case also includes a composite outer shell and an energy absorbing core disposed radially between the inner fabric layer and the composite outer shell. The energy absorbing core includes non resin impregnated multidirectional fibers.



Mounting apparatus for fan

Tue, 12 May 2015 08:00:00 EDT

A mounting apparatus includes a mounting member and a cage configured for receiving a fan. The cage includes two side plates. Each of the two side plates defines a pair of first locking openings. The mounting member includes a body and two first mounting portions extending from each of two opposite sides of the body. The two first mounting portions engage in the first locking openings of the two side plates to secure the mounting member to the cage, for preventing the fan from moving out of the cage.



Liquid flotation system with energy recovery devices

Tue, 12 May 2015 08:00:00 EDT

A system and method of operating the same includes an absorption tank having a compressor communicating gas thereto, a suspended solid filtration tank having a primary inlet, a secondary inlet, a primary outlet and a secondary outlet and a pump comprising a pump inlet coupled to the secondary outlet and a pump outlet communicating fluid to the absorption tank. The absorption tank forms a solution from the fluid and gas. A turbine mechanically couples the pump with a common shaft extending to the pump. The turbine has a turbine inlet coupled to the absorption tank and a turbine outlet coupled to the secondary inlet. The turbine depressurizes the solution. The system may also use a centrifugal pump in place of a turbine and absorption tank.



Turbomachine alignment pin

Tue, 12 May 2015 08:00:00 EDT

Various embodiments include an alignment pin for a turbomachine. In some embodiments, the alignment pin includes a hollowed head section for engaging a diaphragm slot in the turbomachine. In these embodiments, the alignment pin further includes an expandable sleeve section connected with the hollowed head, the expandable sleeve section for engaging a casing slot in the turbomachine.



Pipeline pump shaped by stamping and welding

Tue, 12 May 2015 08:00:00 EDT

A pipeline pump shaped by stamping and welding, comprises a pump body, a pedestal, a pump rear cover and a motor installed at the opening of the pump body, and an impeller arranged inside the pump body. The pump body is comprised of an inner cylinder and an outer cylinder. A flow guide part, the impeller, an exhaust part, and the pump rear cover mounted on the opening of the outer cylinder are coaxially arranged upwards in turn from the opening of the inner cylinder. The impeller is axial suction and radial discharge. The disk bottom of the flow guide part is sealed with the opening of the inner cylinder. The impeller is coaxially arranged inside the flow guide part, and a flow guide vanes corresponding to a radial exhaust port of the impeller are provided on a circumferential wall of the flow guide part.



Air turbine starter turbine nozzle airfoil

Tue, 12 May 2015 08:00:00 EDT

A vane profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Z-coordinates.



Cooled component wall in a turbine engine

Tue, 12 May 2015 08:00:00 EDT

A component wall in a turbine engine includes a substrate, a diffusion section, and at least one cooling passage. The diffusion section is located in a surface of the substrate and is defined by a first sidewall and a second sidewall. The cooling passage(s) include an outlet portion through which cooling air exits in a direction toward the first sidewall. The outlet portion includes a rear section, a front section, and an inner wall having proximal and distal ends. The rear section is located between the first and second sidewalls. The front section extends between the first sidewall and the distal end of the inner wall. The first sidewall extends into the outlet portion of the cooling passage(s) to the inner wall and extends from the first lateral wall to the second lateral wall so as to block the front section of the outlet portion.



Thermally actuated assembly for a gas turbine system and method of controlling a cooling airflow path

Tue, 12 May 2015 08:00:00 EDT

A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity.



Variable blade outer air seal

Tue, 12 May 2015 08:00:00 EDT

A system for a turbofan has a variable outer air seal, an actuator coupled to the variable outer air seal, a sensor positioned inside the turbofan for sensing an engine parameter, and a flight controller connected to the turbofan for receiving the parameter from the sensor. The flight controller directs the actuator to regulate the position of the actuator based on the flight condition resulting form the received parameter.



Centrifugal pump assembly

Tue, 12 May 2015 08:00:00 EDT

The centrifugal pump assembly comprises a device for separating gas from the fluid to be delivered, which is arranged on the suction side. The gas separation device is provided with an impact body (2) which at least partly is arranged in the suction-side flow path (11) of the fluid to be delivered, and on the housing side is arranged at a distance to the suction port of the pump.



Air diffuser system for industrial pumps

Tue, 12 May 2015 08:00:00 EDT

An air diffuser device suitable for use in an air diffuser system for a centrifugal pump the pump including a pump casing with a pumping chamber therein, an impeller mounted within the pumping chamber for rotation about a rotation axis, the impeller including a front side and a rear side. The air diffuser system comprises one or more passages extending through the impeller from the front side to the rear side, the or each passage having a first opening at the rear side and a second opening at the front side of the impeller. The air diffuser device comprises a main body having a seal side and an impeller side, and at least one channel extending through the main body from the seal side to the impeller side, the or each channel having an intake opening at the seal side, a discharge opening at the impeller side, and a base wall extending through the main body, the base wall having a leading end portion at the seal side, and a trailing end portion at the impeller side, the discharge opening being in fluid communication with the first opening of the passage in the impeller when installed.



Variable geometry turbine

Tue, 12 May 2015 08:00:00 EDT

A variable geometry turbine includes a fluid space formed by a nozzle mount and a nozzle plate; and a plurality of nozzle vanes arranged in the fluid space at certain intervals in the circumferential direction so as to partition the fluid space. The nozzle vanes are supported by shafts on the nozzle mount, in such a manner as to be capable of turning. The flow rate of the discharged fluid can be adjusted by opening or closing the cross-sectional area of a flow path formed by the adjacent nozzle vanes. The nozzle plate is provided with plate projections protruding toward the nozzle vanes further than, at least, end surfaces of the nozzle vanes, so as to cover the spaces between leading edges of the nozzle vanes and trailing edges of the nozzle vanes adjacent thereto, when the nozzle vanes are at a closed position.



Off axis pump with integrated chain and sprocket assembly

Tue, 12 May 2015 08:00:00 EDT

An off axis hydraulic pump for an automatic motor vehicle transmission includes an integrated chain and sprocket assembly. A first, chain drive sprocket is mounted on a shaft driven by an input to a torque converter and a second, driven chain sprocket is attached to a stub shaft which drives the pump. A multi-link chain encircles the sprockets and transfers drive torque from the torque converter input to the stub shaft. The first, chain drive sprocket is retained on the input shaft by a retainer cap which includes seals between both the shaft and a torque converter housing. The second, driven chain sprocket is retained on the stub shaft by a snap ring or similar component.