Class / Patent application number | Description | Number of patent applications / Date published |
415207000 | Pump outlet or casing portion expands in downstream direction | 67 |
20090191052 | Exhaust Gas Diffuser Wall Contouring - A diffuser for diffusing the exhaust gas produced by an engine, said diffuser comprising a wall or walls defining sections of the diffuser, said diffuser comprising: an initial section which extends for substantially one third the length of the diffuser, at the entry to said initial section the shape factor of the boundary layer flow at the or each wall of the section being in the range 1.3 to 1.6, said initial section being configured so as to substantially linearly increase said shape factor so that at the exit of said initial section said shape factor is in the range 1.6 to 2.2; and a main section following the initial section and extending for the remaining length of the diffuser, said main section being configured so as to maintain said shape factor in the range 1.6 to 2.2 over the length of the main section. | 07-30-2009 |
20090232650 | TIP TURBINE ENGINE AND CORRESPONDING OPERATING METHOD - A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades. | 09-17-2009 |
20090246010 | Gas turbine arrangement - A gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions, wherein the neck exit of the collector includes a partition device whereby the opposed direction flows at the neck exit are kept substantially separate. | 10-01-2009 |
20090263241 | DIFFUSER AND EXHAUST SYSTEM FOR TURBINE - A diffuser and exhaust system is provided for a turbine having an axial-radial diffuser and an exhaust hood including diffuser inner and outer flow guides that extend from an inlet to an outlet. The exhaust hood includes two throats or flow passages between the diffuser outlet and an exhaust hood side wall. The outer flow guide includes a recess, at one of the said two flow passages. The flow passage is positioned in relation to a point in the exhaust hood in the direction of the tangential flow velocity vector, where the point in the exhaust hood is farthest away from the exhaust hood outlet. The recess prevents a re-acceleration of the flow within the exhaust hood and affects an increase in the performance of the diffuser and exhaust hood system. | 10-22-2009 |
20100021291 | Diffuser Apparatus in a Turbomachine - A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone. | 01-28-2010 |
20100158683 | EXHAUST GAS DISCHARGE SYSTEM AND PLENUM - An apparatus for extending the effective exhaust gas path in order to allow gradual diffusion of the exhaust gases in a turboshaft engine wherein the engine includes an annular engine case with at least an exhaust gas duct having an axial component communicating with an annular duct with a substantially radial component and traversing the engine case, the apparatus comprising a collector plenum having a convex annular shape and a diameter larger than that of the engine case with at least one exhaust outlet defined in the plenum and wherein the annular duct extends into the plenum beyond the diameter of the engine case to extend the exhaust gas path. | 06-24-2010 |
20100166549 | METHODS, SYSTEMS AND/OR APPARATUS RELATING TO INDUCERS FOR TURBINE ENGINES - An inducer that includes a profiled throat. In some embodiments, the inducer includes a conical shape upstream of the profiled throat with a relatively large circular inlet that narrows to the profiled throat and, downstream of the profiled throat, a downstream section that broadens from the profiled throat. The profiled throat may include an approximate convergent-divergent nozzle geometry. | 07-01-2010 |
20100178164 | SYSTEM AND METHOD FOR TURBOCHARGING AN ENGINE - A turbocharger system, in certain embodiments, includes a compressor, a turbine, a shaft coupling the compressor to the turbine, and a turbo casing configured to improve pressure recovery, wherein the turbo casing includes a non symmetrical geometry configured to improve flow towards an exhaust outlet. | 07-15-2010 |
20100226767 | DIFFUSER ARRANGEMENT - A diffuser arrangement through which a fluid may flow is provided. The diffuser includes an outer diffuser comprising an inner surface, and a flow-guiding device, which is configured such that at least part of the boundary layer flow forming on the inner surface of the outer diffuser can be accelerated in the main flow direction, so that a flow separation is prevented on the inner surface of the outer diffuser. Also provided are an exhaust steam plenum of a steam turbine and an exhaust gas plenum of a gas turbine, both including a diffuser arrangement. | 09-09-2010 |
20100239418 | COMPRESSOR DIFFUSER - A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body. | 09-23-2010 |
20100247304 | EXHAUST PLENUM FOR A TURBINE ENGINE - An exhaust system for gas turbine engine is provided that reduces turbulence and backflow within the exhaust system and, thus, increases the efficiency of the turbine engine. In various embodiments, the system includes an exhaust plenum that provides a gradual expansion of the exhaust gases. The exhaust plenum may also include one or more flow splitters that further reduce turbulence in the plenum and provide a more uniform gas flow in the plenum and other downstream exhaust components. | 09-30-2010 |
20110097203 | TURBO MACHINERY - Turbo machinery comprising an impeller and a diffuser positioned on a downstream side of the impeller that a channel wall surface of the diffuser is composed of a pair of a shroud side diffuser plate and a hub side diffuser plate which surface each other and a channel width is formed so as to be increased downstream, characterized in that guide vanes in a circular arc shape lower in height than the channel width are installed in a line of a plurality of vanes on both channel walls of the shroud side diffuser plate and hub side diffuser plate of the diffuser, and a total of vane heights of the two guide vanes at an outlet of the diffuser is set so as to be within a range from 30 to 70% of the channel width at the outlet of the diffuser. | 04-28-2011 |
20110097204 | TURBINE ENGINE WITH DIFFUSER - A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating. | 04-28-2011 |
20110176917 | Exhaust Gas Diffuser Wall Contouring - A diffuser for diffusing the exhaust gas produced by an engine is provided. The diffuser includes a wall or walls defining sections of the diffuser, the diffuser including a first section and a second section following the first section, wherein the rate of increase of the cross-sectional area of the diffuser, which includes using an outer annular wall as an outer boundary and the inner annular wall as an inner boundary, in a direction of fluid flow is greater in the first section than it is in the second section. An upstream end of the inner annular wall or an upstream end of the outer annular is bent. | 07-21-2011 |
20110189006 | TURBINE APPARATUS - A fluid turbine apparatus which is able to increase the fluid velocity and consequently increase the rotation speed of the fluid turbine. The fluid turbine apparatus has a convergent section, a fluid turbine section and a divergent section. The fluid enters into the fluid turbine through the convergent section, passes through the fluid turbine and exits through the divergent section. The combination of the convergent section and the divergent section creates a Venturi effect and increases the fluid velocity and thus the energy density entering turbine for increasing the energy extracted by the turbine. | 08-04-2011 |
20110194932 | DIFFUSIVE NACELLE - A nacelle for a propeller gas turbine engine, the nacelle comprising a forebody upstream of the propellers and an afterbody downstream of the forebody. The forebody comprises a first, upstream region and a second, downstream region. The first region has a convex profile and the second region has a concave profile to cause diffusion of the airflow into the propellers. | 08-11-2011 |
20110217162 | TURBO CHARGER HOUSING - A turbocharger compressor housing apparatus comprises a compressor housing and diffuser. These components are configured to provide an interference fit when assembled. An annular projection extends outwardly from one of such components toward the other of the components and engages the other of the components to form an annular joint. One of the compressor housing and diffuser comprises a recess positioned to collect debris generated during the interference fit to prevent the debris from reaching the annular joint. A second recess can be provided at the opposite side of the projection to accommodate deformation of the projection during assembly of the diffuser and compressor housing. The recesses can be annular and can, along with the projection, be included in the diffuser. | 09-08-2011 |
20110223014 | FAN ASSEMBLY - A fan assembly for creating an air current includes a nozzle mounted on a base. The base comprises an outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly. | 09-15-2011 |
20110229316 | IMPROVED AEOLIAN APPARATUS - The invention relates to an eolic silos ( | 09-22-2011 |
20120045324 | HUB FLOWPATH CONTOUR - An apparatus is provided and includes a turbine including a platform, a casing and a turbine bucket having a hub coupled to the platform and a trailing edge defined relative to a direction of fluid flow through the turbine and a diffuser, defined between a central surface and a downstream section of the casing, which is fluidly coupled to the turbine and disposed downstream from the trailing edge, a slope of the hub being angled by at least 6 degrees relative to a slope of the central surface within about 0.5 turbine bucket chord lengths as measured at the hub from the trailing edge, and the central surface and the downstream section of the casing being at least substantially parallel or divergent from the trailing edge. | 02-23-2012 |
20120063893 | TURBINE EXHAUST PLENUM - In accordance with one embodiment, a system includes a turbine engine including an axial-radial diffuser section disposed about a first longitudinal axis downstream in an exhaust flow path from a turbine section. The system also includes an exhaust plenum including a first plenum portion disposed about the axial-radial diffuser section, wherein the first plenum portion includes a curved wall portion that diverges away from a circumference of the axial-radial diffuser section. The exhaust plenum also includes a second plenum portion extending away from the first plenum portion downstream along a second longitudinal axis of the exhaust plenum approximately crosswise to the first longitudinal axis. | 03-15-2012 |
20120093636 | TURBOMACHINE AND IMPELLER - Turbomachine for increasing the pressure of a fluid or mixture of fluids, comprising an inlet and an outlet, a casing, a rotatable shaft arranged in the casing, diffusers or similar operatively arranged in the turbomachine, and a means for rotation operatively connected to the shaft. The turbomachine is distinguished in that it comprises: at least one impeller of a mixed flow type arranged on the shaft, the impeller having an inlet and an outlet, the inlet is closer to an axis of rotation than the outlet; and at least one further impeller arranged on a common or operatively connected shaft, chosen from the group consisting of axial impellers arranged upstream of the mixed flow type impeller and radial impellers arranged downstream of the mixed flow type impeller. Impeller for use in a turbomachine for increasing the pressure of a fluid or mixture of fluids, the impeller comprising at least one blade, distinguished in that it comprises at least one fluid passageway fluidly connecting the pressure side of the blade with the leeward side of the blade. | 04-19-2012 |
20120121401 | RING DIFFUSER FOR AN AXIAL TURBOMACHINE - An arrangement with a ring diffuser for an axial turbomachine, for example for a gas turbine, is provided. The ring diffuser includes an outer wall and with an inner wall coaxial thereto, between which a diffuser duct extends in ring form along an axial extent so as to diverge from an inflow-side end to an outflow-side end, the inner wall and the outer wall in each case including a wall surface delimiting the diffuser duct. In order to specify a diffuser duct which is adapted to an inflow uneven along the circumference and by means of which a specially efficient conversion of kinetic energy into static energy is possible, the wall surface which delimits the diffuser duct on the inlet side is rotationally asymmetrical. | 05-17-2012 |
20120156026 | AIR CYCLE MACHINE COMPRESSOR ROTOR - A compressor rotor for an air cycle machine (ACM) includes a plurality of blades that each includes a root, a tip, a first surface and second surfaces. The first and second surfaces are defined as a set of X-coordinates, Y-coordinates and Z-coordinates set out in any of Table M-1 and M-2 or Table S1 and S-2 scaled by a desired factor. The X-coordinates being in the tangential direction, the Y-coordinates being in the axial direction and the Z-coordinates being in the radial direction. | 06-21-2012 |
20120156027 | AIR CYCLE MACHINE COMPRESSOR DIFFUSER - A diffuser for an air cycle machine defines airflow both to a compressor rotor from the inlet and from the compressor rotor through a plurality of vanes that define radially extending airflow passages. The size and shape of both the inlet and the vanes of the diffuser define and tailor the character of airflow presented to and leaving the compressor rotor to provide a desired change in air flow. | 06-21-2012 |
20120275916 | DIFFUSER WITH ENHANCED SURGE MARGIN - A diffuser for a centrifugal impeller assembly of a gas turbine engine includes a diffuser case having a plurality of vanes extending therein defining a plurality of circumferentially distributed angled passages in communication with an inlet space. Each vane includes a bleed port defined in a suction surface thereof, in proximity of the leading edge. The diffuser case includes a passive fluid communication defined at least partially through each one of the vanes between each bleed port and the inlet space upstream of the leading edge, such that air bled through the bleed ports is recirculated upstream of the leading edges to the inlet space to increase a surge margin of the diffuser. | 11-01-2012 |
20130039753 | GAS TURBINE ENGINE - A gas turbine engine is provided, which comprises an outlet guide vane provided downstream of a compressor; an outer casing supporting a radially outward part of the outlet guide vane; and an inner diffuser supporting a radially inward part. The outlet guide vane includes a radially inward inner flange; a projecting part projecting radially inward from the inner flange; and an engagement part protruding to one side in an axial direction of the projecting part. The inner diffuser includes a smaller-diameter part having a smaller outer diameter than the other part located upstream. The inner diffuser is provided with an engagement groove extending to one side in the axial direction from an outer peripheral surface of the smaller-diameter part or a region in the vicinity thereof. The engagement part is inserted into the engagement groove with a gap between the engagement part and groove. | 02-14-2013 |
20130094955 | CENTRIFUGAL COMPRESSOR DIFFUSER AND CENTRIFUGAL COMPRESSOR PROVIDED WITH THE SAME - A centrifugal compressor diffuser includes a shroud-side wall ( | 04-18-2013 |
20130129496 | Turbomachine - A turbomachine has a housing which has at least one inflow channel. A plurality of blades is arranged on a rotor wheel and an operating medium flows toward the blades. The operating medium flows via the inflow channel into at least one blade channel which is formed between two blades mounted on the rotor. After exiting the rotor region, the operating medium enters a diffuser. A guide body deflects the operating medium flowing out of the blade channel in the direction of the diffuser. A portion of the guide body in the turbomachine is positioned in an intermediate region of the rotor. The intermediate region is surrounded in the radial direction by the rotor blades and lies between a blade-channel outlet and an inlet opening in an outlet channel which is downstream of the rotor and is formed by the diffuser. | 05-23-2013 |
20130136591 | AXIAL-FLOW FAN - An axial-flow fan includes an impeller mounted on a rotating shaft of a rotary drive device and a venturi casing surrounding an outer periphery of the impeller in a radial direction and including a suction port and a discharge port facing each other in an axial direction of the rotating shaft . An inner surface of the venturi casing includes a suction-side slant part | 05-30-2013 |
20130170972 | EXHAUST GAS DIFFUSER OF A GAS TURBINE - An exhaust gas diffuser for a gas turbine includes a flow duct which widens towards a diffuser outlet. The flow duct includes an axially extending guide body, wherein the guide body, at least in an axial section of its longitudinal extent, has a plurality of recesses which are distributed over the circumference and arranged between guide elements. Each guide element extends along a spiral line along the longitudinal extent of the guide body. Further, a gas turbine plant with such an exhaust gas diffuser is provided. | 07-04-2013 |
20130209246 | GAS TURBINE ANNULAR DIFFUSOR - Described is a gas turbine diffuser ( | 08-15-2013 |
20130216371 | TURBOPROP ENGINE SYSTEMS WITH NOISE REDUCING INLET ASSEMBLIES - An inlet assembly for a turboprop engine system is provided. The inlet assembly includes an inlet plenum defining first inlet configured to receive air from the atmosphere; an expansion plenum coupled to the inlet plenum and configured to receive the air from the inlet plenum, the inlet plenum and the expansion plenum defining a flow path for the air with a bend of at least 90°; and a second inlet coupled to the expansion plenum and configured to receive the air from the expansion plenum. | 08-22-2013 |
20130224006 | STEAM TURBINE - A steam turbine | 08-29-2013 |
20130259670 | FLOW PATH STRUCTURE AND GAS TURBINE EXHAUST DIFFUSER - A flow path structure includes a wall surface in which a flow path is formed, a structure configured to extend in a direction intersecting a main stream direction of a fluid flowing through the flow path from the wall surface, and a concave section forming region formed throughout a range including the structure in the main stream direction and having a concave section formed in the wall surface. As the structure occupies a partial range of the flow path in the flow path cross section intersecting the main stream, a cross-sectional area of the flow path is varied in accordance with positional variation in the main stream direction. | 10-03-2013 |
20130280058 | WIND MACHINE WITH AERODYNAMIC ELEMENTS TO CONCENTRATE AND ACCELERATE AN AEOLIAN FLOW ENTERING FROM OUTSIDE - The present invention relates to a wind machine with aerodynamic elements to concentrate and accelerate an Aeolian flow entering from outside, said machine being characterized in that it is provided with a housing ( | 10-24-2013 |
20130336775 | WIND ENERGY SYSTEM AND METHOD FOR USING SAME - A wind energy system comprising a wind turbine comprising a cowling surrounded by a diffuser and a plurality of inner rotor blades located inside of the cowling that rotate about an inner hub, a plurality of outer rotor blades positioned between the diffuser and the cowling that are counter-rotating relative to the plurality of inner rotor blades, a drive mechanism located within the inner rotor hub, a dynamic telescopic tower, and a tower support that connects tne wind turbine to the dynamic telescopic tower. | 12-19-2013 |
20140023493 | TURBINE EXHAUST STRUCTURE AND GAS TURBINE - In a turbine exhaust structure and a gas turbine, a turbine casing ( | 01-23-2014 |
20140037441 | RAM AIR FAN DIFFUSER - A disclosed ram air assembly includes a housing that defines an inlet and an inner cavity. A fan disposed at the inlet generates air flow and is driven by an electric motor. Airflow through the ram air fan assembly is directed through a passageway defined by a diffuser. The diffuser includes a first diameter at a forward end, and a second diameter at an aft end with the second diameter being larger than the forward end to diffuse airflow and increase fan efficiency. | 02-06-2014 |
20140044535 | WIND TURBINES AUGMENTED WITH ROTATING DIFFUSERS - Diffuser-augmented wind turbines can include a first diffuser ring arranged to form a turbine rotor cowling, the diffuser being fixed to and rotatable with the turbine rotor about the horizontal axis of the wind turbine. The first diffuser ring may have one or more dynamic, aero-elastic, vortex entrainment devices attached to a trailing edge of the diffuser. The first diffuser ring may include one or more slot gaps arranged within its body, each slot gap creating a channel between the interior and exterior surfaces of the first diffuser ring. In some embodiments the diffuser may optionally further include one or more further diffuser rings, the one or more further diffuser rings being static rings (e.g. non-rotatable about the horizontal axis) or dynamic diffuser rings (e.g. rotatable around the horizontal axis | 02-13-2014 |
20140161603 | EXHAUST DIFFUSER - An exhaust diffuser is provided having a center body having an inlet adapted for coupling to a turbine. The center body has an outer wall, and a guide member disposed inside the center body. A flow path reducing member is disposed inside the center body. The flow path reducing member is configured to be movable into a first position and a second position. The first position is an inactive position having no impact on an exit flow area of the exhaust diffuser, and the second position is a deployed position that reduces the exit flow area of the exhaust diffuser. | 06-12-2014 |
20140161604 | AIRFLOW DIFFUSER FOR IN-TRANSIT REFRIGERATION - A diffuser apparatus for a space of a refrigeration container includes a housing having an internal chamber extending to a nozzle portion comprising a height less than a height of the internal chamber and a width greater than a width of the internal chamber, a fan disposed for operation in the internal chamber, and a heat exchanger disposed for operation in the internal chamber between the fan and the nozzle portion. | 06-12-2014 |
20140178191 | Diffuser Assemblies Having at Least One Adjustable Flow Deflecting Member - A diffuser assembly is provided herein. In certain embodiments, the diffuser assembly may include an outer boundary member and an inner boundary member, with the inner boundary member being positioned radially inward of the outer boundary member. The diffuser assembly also may include an exhaust flow path defined between the outer boundary member and the inner boundary member. Further, the diffuser assembly may include at least one flow deflecting member operatively attached to the outer boundary member. The flow deflecting member may be adjustable about the outer boundary member to produce a substantially uniform velocity distribution within the exhaust flow path. | 06-26-2014 |
20140205448 | EXHAUST DIFFUSER AND METHOD FOR MANUFACTURING AN EXHAUST DIFFUSER - An exhaust diffuser and method for manufacturing an exhaust diffuser is provided. An exhaust diffuser for a torque-generating turbine, in particular a torque-generating gas turbine is provided herein. The exhaust diffuser having an inner member, the inner member having an outer surface and an outer member having an inner surface, the inner member and the outer member forming an annular channel, at least a first supporting strut connecting the inner member and the outer member, the first supporting strut extending essentially radially from the inner surface to the outer surface, the first supporting strut having a middle section having a first airfoil and an outer section having a second airfoil, and the second airfoil differing from the first airfoil in shape to be able to handle a higher range of angle of attack. Furthermore, it is described a method for manufacturing an exhaust diffuser. | 07-24-2014 |
20140212281 | Flow Feed Diffuser - A feed diffuser is disclosed. The diffuser may comprise a base disposed orthogonal to a flow, a body extending from the base toward the flow, and an apex provided at a termination of the body in a direction toward the flow. The body may decrease in cross-sectional area from the base to the apex. | 07-31-2014 |
20140241870 | PUMPING APPARATUS AS WELL AS A DIFFUSOR FOR A PUMPING APPARATUS - Disclosed are a diffuser and a pump including a feed column extending around a diffusor axis of the pump and having a rotor housing which is arranged between an intake and a diffusor arranged in a diffusor section. During operation, fluid is sucked by the pump rotor via the intake, and is discharged from the feed column via the diffusor section, the feed tube and the outlet stub. The diffusor includes an inlet section arranged between an outlet section and the pump rotor, wherein a first part section adjacent to the inlet section is formed at the outlet section, the first part section is inclined with respect to the diffusor axis at a first angle (α). A second part section adjoining the first part section is inclined with respect to the diffusor axis at a second angle (β) different from the first outlet angle (α). | 08-28-2014 |
20140248142 | GAS TURBINE ENGINE IMPELLER SYSTEM FOR AN INTERMEDIATE PRESSURE (IP) COMPRESSOR - A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser. | 09-04-2014 |
20140271168 | Radial Diffuser Exhaust System - The present application provides a radial diffuser exhaust system for use with a gas turbine engine. The radial diffuser exhaust system may include a radial diffuser positioned within an asymmetric exhaust collector. The asymmetric exhaust collector may include a closed end chamber and an exhaust end chamber. The closed end chamber may have a first size, the exhaust end chamber may have a second size, and the first size may be smaller than the second size. | 09-18-2014 |
20140341728 | ANGULAR DIFFUSER SECTOR FOR A TURBINE ENGINE COMPRESSOR, WITH A VIBRATION DAMPER WEDGE - The invention provides an angular diffuser sector ( | 11-20-2014 |
20140348647 | EXHAUST DIFFUSER FOR A GAS TURBINE ENGINE EXHAUST SYSTEM - An exhaust diffuser for a gas turbine engine includes a diffuser inlet, a diffuser exit, an inner diffuser wall, and an outer diffuser wall. The inner diffuser wall may include a first tubular member with a flared downstream portion. The outer diffuser wall may include a second tubular member at least partially about the inner diffuser wall and with a second flared downstream portion. The outer diffuser wall and the inner diffuser wall extend between the diffuser inlet and the diffuser exit, and form a diffusing flowpath therebetween. The second flared downstream portion may include a lower section and an upper section, with the upper section extending further downstream in an axial direction than the lower section, relative to the diffuser axis. | 11-27-2014 |
20140369826 | TORNADO WIND ENERGY CONVERSION SYSTEM WIND TURBINE - A Vertical-Axis Double-Ducted Vortex-Diffuser-Augmented Wind Turbine comprises an apparatus further comprising a large, hollow, cylindrical tower with external fixed, wind concentrating cowlings and internal hinged, wind inlet vanes. The cowlings are large curved sections that extend outward from the cylindrical tower and perform two functions: 1) capture the wind, entraining it into a tower's core on an upwind side of the tower; and 2) shade a downwind side of the cylindrical tower from the wind, creating a negative pressure on downwind inlet vanes. The inlet vanes extend into the tower's cylindrical core, automatically opening to allow the wind to enter on the upwind side of the tower and automatically close on the downwind side of the cylindrical tower. By working together the external cowlings and internal inlet vanes enable the cylindrical tower to capture and entrain the wind stream into a contained tornado-like vortex. | 12-18-2014 |
20140369827 | ROTOR FOR A TURBOMACHINE - A rotor for a double-flow turbomachine is provided, wherein the first flow and the second flow have several rows of rotor blades, wherein at least one row of rotor blades is different from the corresponding row of rotor blades of the other flow. | 12-18-2014 |
20150016982 | EXHAUST DIFFUSER FOR A GAS TURBINE - An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions. | 01-15-2015 |
20150023787 | AIR CYCLE MACHINE COMPRESSOR DIFFUSER - A diffuser for an air cycle machine defines airflow both to a compressor rotor from the inlet and from the compressor rotor through a plurality of vanes that define radially extending airflow passages. The size and shape of both the inlet and the vanes of the diffuser define and tailor the character of airflow presented to and leaving the compressor rotor to provide a desired change in air flow. | 01-22-2015 |
20150044039 | EXHAUST DIFFUSER SHELL WITH FLANGE AND MANUFACTURING METHOD - Manufacture of an arcuate diffuser shell ( | 02-12-2015 |
20150063995 | AIR DIFFUSER SYSTEMS, METHODS, AND APPARATUSES - Aircraft, air conditioning systems, and air diffusers that may be used to create a quiet, comfortable environment within an aircraft cabin are disclosed. The systems and apparatuses are configured to flow air at a rate that meets and/or exceeds the FAA minimum requirement of 0.55 lbs/min (about 250 g/min) per occupant. In use, even at higher flow rates, the systems and apparatuses are configured to create a quiet cabin experience, by contributing little to ambient cabin noise. Thus, the systems and apparatuses may be used to provide fresh air at a comfortable rate and a comfortable noise level. | 03-05-2015 |
20150063996 | INDUCER AND DIFFUSER CONFIGURATION FOR A GAS TURBINE SYSTEM - A system includes at least one inducer including a flow passage configured to guide a fluid flow into a cavity defined by a casing and rotor of a gas turbine engine, the flow passage includes an inlet configured to receive the fluid flow from a compressor diffuser of the gas turbine engine, and an outlet configured to discharge the fluid flow into the cavity. The at least one inducer is configured to be disposed within the gas turbine engine so that the second outlet is axially disposed forward of a diffuser outlet of the compressor diffuser. | 03-05-2015 |
20150098811 | ADJUSTABLE BRACING APPARATUS AND ASSEMBLY METHOD FOR GAS TURBINE EXHAUST DIFFUSER - Length adjustable braces ( | 04-09-2015 |
20150147168 | ABRASIVE HANDLING SUBMERSIBLE PUMP ASSEMBLY DIFFUSER - 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. | 05-28-2015 |
20150292362 | METHOD OF REMANUFACTURING A MACHINE COMPONENT - A method is provided for remanufacturing a machine component having multiple holes. The holes are provided to match in alignment with corresponding holes of an adjacent component in a machine assembly. First and second sets of holes are selected from the holes of the machine component on the basis of being located within first and second limits of positional tolerance with respect to corresponding holes of the adjacent component. Each hole from the first set of holes is bored to define openings in axial alignment with holes of the adjacent component. Each hole from the second set of holes is bored to an enlarged diameter and then plugged with a deformable insert. Each of these inserts is then drilled to define openings in axial alignment with holes of the adjacent component. | 10-15-2015 |
20150292406 | PANEL ATTACHMENT SYSTEM AND A METHOD OF USING THE SAME - A panel attachment system comprises a panel, a hanger, a plurality of anchors and a casing. Each anchor comprises an elongate post portion superimposed by a planar cap portion with each anchor having a second ‘T’-shaped cross sectional area. The hanger is removably secured to the casing by a plurality of fastening elements with each fastening element passing through a corresponding hole in the casing and being accommodated in a respective one of the plurality of bosses. The plurality of anchors is spaced along a first surface of the panel with each post portion being secured to and protruding from the first surface of the panel, the spacing between adjacent anchors corresponding to the spacing between adjacent slots in the second edge of the hanger plate, with each slot receivably accommodating a respective one of the anchors to secure the panel to the casing. | 10-15-2015 |
20150300372 | Diffusor, ventilator having such a diffusor, and device having such ventilators - The invention relates to a diffusor having a wall ( | 10-22-2015 |
20160053774 | RADIAL OR MIXED-FLOW COMPRESSOR DIFFUSER HAVING VANES - The invention relates to a vane ( | 02-25-2016 |
20160076554 | BACKING PLATE - An annular backing plate for a diffuser in a centrifugal compressor comprises an inner diameter and an outer diameter disposed radially opposite the inner diameter. The backing plate also includes a first surface extending between the inner diameter and the outer diameter of the backing plate. A step is formed on the first surface proximate the inner diameter, wherein the step shifts a portion of the first surface encompassed by the step axially aft relative a portion of the first surface not encompassed by the step. | 03-17-2016 |
20160097401 | AIR CYCLE MACHINE STRUT PLATE ASSEMBLY - According to one aspect, an air cycle machine includes a fan rotor, a diffuser cone axially aligned with the fan rotor, and a strut plate assembly. The strut plate assembly includes a first strut plate and a second strut plate with an ejector formed between the first strut plate and the second strut plate. The first strut plate is axially positioned between the fan rotor and the ejector, and the second strut plate is axially positioned between the fan rotor and the diffuser cone. The first strut plate includes a plurality of outer struts and is absent inner struts between the fan rotor and the ejector. The second strut plate includes a plurality of inner struts and outer struts, where the inner struts are axially positioned between the ejector and the diffuser cone. | 04-07-2016 |
20160169245 | High Compressor Exit Guide Vane Assembly to Pre-Diffuser Junction | 06-16-2016 |
20190145427 | FAN SHROUD | 05-16-2019 |