Entries |
Document | Title | Date |
20080206056 | Modular Tip Turbine Engine - A tip turbine engine assembly includes a compressor module ( | 08-28-2008 |
20080226453 | Balanced Turbine Rotor Fan Blade for a Tip Turbine Engine - A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section ( | 09-18-2008 |
20080298970 | Turbo Machine - A turbo machine ( | 12-04-2008 |
20080310961 | Blade shroud with protrusion - A fluid-flow machine has a main flow path, in which at least one row of blades ( | 12-18-2008 |
20090004012 | COVER PLATE FOR TURBINE ROTOR HAVING ENCLOSED PUMP FOR COOLING AIR - A cover plate for use with a rotor disk in a gas turbine engine includes an enclosed chamber associated with a web on the rotor disk. The enclosed chamber ensures that adequate cooling air is delivered by rotation of the cover plate. | 01-01-2009 |
20090010762 | DAMPER FOR TURBOMACHINE VANES - The present invention relates to a turbomachine vane damper constructed so as to be housed between the lower face of the platforms of two adjacent turbomachine vanes and the rim of the rotor disk on which the vanes are mounted. This damper is noteworthy in that it comprises a weight ( | 01-08-2009 |
20090097980 | STEAM TURBINE ROTOR BLADE ASSEMBLY - The present invention is a steam turbine rotor blade assembly including: an airfoil; a shroud provided at a tip of the airfoil; a blade root (dovetail) projecting toward a radially internal circumferential side of a turbine rotor and fitted to a root attachment provided on an outer circumferential portion of the turbine rotor; a platform provided between the airfoil and the blade root; a pin provided between the blade root and the root attachment; a bore formed between respective surfaces of the shrouds facing each other and included in the respective adjacent rotor blades; and a bar-like member provided in the bore. | 04-16-2009 |
20090148294 | Houseless fan with rotating tip ring as silencer - The stationary housing of a conventional fan assembly is replaced with a rotating tip ring. The rotating tip ring has a shaped cross-sectional profile to enhance performance and eliminate tonal noise associated with the fundamental (or blade passing) frequency and its harmonics. | 06-11-2009 |
20090169386 | ANNULAR TURBINE RING ROTOR - A fan-turbine rotor assembly ( | 07-02-2009 |
20090257876 | Blower Impeller with Partial Tip Blockage - According to embodiments of the invention, an impeller includes a hub, and a plurality of radial blades for drawing the air inflow axially through the hub and delivering the drawn air radially towards the outside. A ring is attached to one or more tips of the plurality of radial blades to block a portion of the tip toward the inlet side of the impeller. The preferred blockage factor, which is the ratio of a height of the ring to a height of the tip, is approximately in a range between 30% and 40%. By blocking a portion of the tip toward the inlet side of the impeller, the low-momentum flow zone toward the inlet side of impeller is blocked, while the high-momentum flow zone toward the back side of impeller is enhanced. As such, the performance of the impeller is enhanced. | 10-15-2009 |
20100086405 | IMPELLER, FAN APPARATUS USING THE SAME, AND METHOD OF MANUFACTURING IMPELLER - An impeller, a fan apparatus, and a method of manufacturing the impeller are provided. The impeller includes a support portion, a plurality of rotor blades, and a joining member. The joining member is a substantially annular member provided to strengthen the rotor blades against influence of a centrifugal force, and extends in a circumferential direction along a circle centered on a central axis so as to join the rotor blades to one another. In each of the rotor blades, a point of intersection of a leading edge of the rotor blade with a radially outer end of the rotor blade is positioned forward, with respect to a rotation direction, relative to a point of intersection of the leading edge with an outside surface of the support portion. The joining member is positioned radially inwards of the radially outer end of each of the rotor blades. | 04-08-2010 |
20100092295 | STEAM TURBINE ROTATING BLADE FOR A LOW PRESSURE SECTION OF A STEAM TURBINE ENGINE - A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. A part span shroud is attached at an intermediate section of the airfoil portion between the ends thereof. The blade includes an exit annulus area of about 47.7 ft | 04-15-2010 |
20100104440 | COATING MATERIAL AND METHOD OF MANUFACTURING SAME, COATING METHOD, AND MOVING BLADE WITH SHROUD - The present invention provides a coating material, a method of manufacturing the coating material and a coating method using the coating material that are capable of forming a coating film that retains high abrasion resistance while offering improved oxidation resistance at high temperatures, and also provides a moving blade fitted with a shroud. A coating material is used that comprises not less than 14% by mass and not more than 30% by mass of Mo, not less than 13% by mass and not more than 20% by mass of Cr, and not less than 0.5% by mass and not more than 4% by mass of Si, may further comprise not more than 1.5% by mass of Ni, not more than 1.5% by mass of Fe, and not more than 0.08% by mass of C, and comprises a balance of Co and unavoidable impurities, wherein the material further comprises at least one added component selected from the group consisting of not less than 0.01% by mass and not more than 3% by mass of Y, not less than 0.01% by mass and not more than 10% by mass of Al, and not less than 0.1% by mass and not more than 10% by mass of Fe. | 04-29-2010 |
20100111698 | Fan with locking ring - An airflow apparatus comprising a stator section, at least one stator blade and a plurality of mounting flanges disposed on the stator section is provided. Additionally, the airflow apparatus includes at least one slot disposed between the plurality of mounting flanges, a rotor assembly coupled to the at least one stator blade, whereby the rotor assembly has a proximal end and a distal end. Furthermore, the airflow apparatus includes at least one fan blade coupled to the rotor assembly. The airflow apparatus also includes a locking apparatus, whereby the locking apparatus includes at least one mounting member and at least one coupling member, wherein the at least one slot is coupled to the at least one coupling member. | 05-06-2010 |
20100247316 | High Efficiency Ducted Fan - A fan assembly comprises a hub and fan blades. The hub includes a plurality of sockets configured to receive complementary mounting blocks of the fan blades. The mounting blocks each include at least one tapered shoulder portion. The mounting blocks are each tapered along three dimensions. Each mounting block comprises a rear face seated against a complementary rear face of the corresponding socket and a front face that is exposed relative to the hub. A cap secures the fan blades to the hub. The fan assembly may also include one or more shrouds positioned about the fan blades. The one or more shrouds may be substantially straight cylinders, may be flared or bell-shaped, may comprise a cage, may have any other suitable configuration, or may be omitted altogether. | 09-30-2010 |
20100316498 | FAN MANUFACTURING AND ASSEMBLY - A method of making a fan ( | 12-16-2010 |
20110097209 | Thermal airfoil turbine - The Thermal Airfoil Turbine, as it is conceived, is used to generate mechanical energy, from the thermal energy of an airflow, the energy applied by the airflow to the airfoils in the Thermal Airfoil Turbine, is less by a large factor, usually ten or more than the power generated when the Thermal Airfoil Turbine spins at a certain rotational velocity. This generated power comes from the thermal energy lost, by the airflow passing through the Thermal Airfoil Turbine. It must be emphasized that the difference between this Generator and others that uses airflow, is that the others work with the kinetic energy of the airflow, reducing its velocity so to use it in producing power, on the contrary the Thermal Airfoil Turbine intends not to reduce this velocity at all, producing its power from transforming the thermal energy of the airflow into mechanical energy. | 04-28-2011 |
20110200439 | IMPELLER, COMPRESSOR, AND METHOD FOR PRODUCING IMPELLER - A hub is supported rotatably about an axis of rotation, and the diameter thereof increases from upstream to downstream sides along a fluid flow. A plurality of impeller blades extend radially outward from an outer circumferential surface of the hub. A shroud is formed in a cylindrical shape whose diameter increases from the upstream to downstream sides along the fluid flow and joins outer circumferential ends of the plurality of impeller blades. The impeller blades are composed of upstream blade segments and downstream blade segments bonded at a bonding surface extending in a direction substantially perpendicular to the axis of rotation. The upstream blade segments are integral with at least a portion of the shroud, and the downstream blade segments are integral with at least a portion of the hub. This improves the reliability and performance of an impeller and a compressor. | 08-18-2011 |
20110223024 | SKEWED AXIAL FAN ASSEMBLY - A free-tipped axial fan assembly has a skew distribution which reduces fan noise while minimizing radial tip deflection. The difference between the maximum value of leading-edge skew and the value of leading-edge skew at the fan radius is at least 10 degrees. The ratio of the difference of the leading-edge skew between the maximum value and the value at the fan radius to the difference of the trailing-edge skew between the maximum value and the value at the fan radius is at least 2.5. | 09-15-2011 |
20110299989 | Blade union of a turbo machine - A damping system for damping the vibrations of a blade union is provided. The blades arranged in a neighboring manner are coupled to one another via a coupling element, wherein the coupling element is arranged fixed in a first blade and extends into the second blade, wherein the coupling element is not arranged in the second blade but rather solely contacts there such that, as a consequence of centrifugal forces, a free end of the coupling element presses against the second blade and a friction force thus occurs, leading to an energy dissipation and vibrations being thus damped. | 12-08-2011 |
20110318183 | Method for Producing a Shrouded Impeller from Two or More Components - Provided is a two-piece shrouded impeller, and methods for manufacturing and assembling a two-piece shrouded impeller. The two-piece shrouded impeller, in accordance with one embodiment, may have a one-piece partially shrouded impeller having a central hub, a number of blades integrally attached to the hub, and one or more integral partial shroud sections integrally attached to the blades. The two-piece shrouded impeller in this embodiment may also have a separate shroud section that attaches to the one-piece shrouded impeller, so that the separate shroud section and the partial shroud sections combine to form a completed shroud that covers the impeller blades. The separate shroud section may attach to the one-piece shrouded impeller with a snap joint, or with an interference fit, or using a squeeze deformable ring. Once attached, the shroud section may be bonded to the one-piece shrouded impeller by brazing, stick welding, ultrasonic welding, or electron beam welding. | 12-29-2011 |
20120003097 | AXIAL FLOW FAN - An axial flow fan has structural stability, decreased deformation, decreased blade unbalance and low noise level because the blade distribution angle has an optimum clearance angle and uneven rate. | 01-05-2012 |
20120034083 | FAN WITH AREA EXPANSION BETWEEN ROTOR AND STATOR BLADES - An axial-flow fan structure is disclosed, having a localized area expansion between the rotor (i.e. front rotating impeller) and stator blades (i.e. rear stationary or fixed blades, sometimes called de-swirl vanes). The area expansion is provided by utilizing an impeller having a (slightly) falling tip contour (FTC). | 02-09-2012 |
20120189451 | FAN - A fan, for a ventilation assembly has blades extending from a cup-shaped central hub. The hub has an annular side wall and a bottom wall defining a receptacle for an electric motor. The hub has internal ribs for ventilation of the motor. Each rib has a longitudinal portion which extends along the side wall, a radial portion which extends along the bottom wall and an intermediate portion having an arcuate, transversely protruding profile. The longitudinal portion has a profile whose spacing from the side wall of the hub increases, from a minimum value remote from the bottom wall to a maximum value adjacent the bottom wall. | 07-26-2012 |
20120244000 | Propeller, Engine Cooling Device Comprising Such A Propeller, And Mould For Producing Said Propeller - The invention relates to a propeller ( | 09-27-2012 |
20120251322 | Rotating fluid conduit utilized such a propeller or turbine, characterized by a rotating annulus, formed by a rotating inner hub and a rotating outer shell - A rotating fluid conduit, utilized such as a propeller or turbine, is disclosed that is characterized by a rotating annulus formed by a rotating inner hub and a rotating outer shell. Rotating internal vanes are arranged within the annulus and are affixed to the inner hub and the outer shell. The annulus area varies from the inlet to the outlet and the angle of the vanes, within the annulus, also varies to control the radial velocity and axial velocity of the fluid stream and thereby provide a corresponding change in the axially directed and radially directed energy of a fluid. This rotating fluid conduit is analytically calculated, to an exact solution, to deliver predictable performance at design and off design conditions. | 10-04-2012 |
20120263595 | ANNULUS FILLER SYSTEM - An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove. | 10-18-2012 |
20130071247 | IMPELLER AND METHOD FOR PRODUCING SAME - An impeller integrally includes a substrate and multiple impeller blades provided upright along a curved shape and circumferentially spaced apart on one face of the substrate. The impeller blades expand in diameter and each include an inner circumferential-side blade portion on the inner circumferential side of the substrate and extending in the rotary shaft core direction and have a tip side that is bent, and an outer circumferential-side blade portion on the outer circumferential side of the substrate and extending in the rotary shaft core direction. In the direction along the rotary shaft core, the length of the inner circumferential-side blade portion from the substrate side to the tip side is longer than the length of the outer circumferential-side blade portion from the substrate side to the tip side, and the blade thickness of the inner circumferential-side blade portion gradually decreases from the substrate side toward the tip side. | 03-21-2013 |
20130084187 | BLADE STRUCTURE FOR CENTRIFUGAL FAN - A blade structure for centrifugal fan includes a hub, a first blade unit, and a second blade unit. The hub has a connection section formed therearound and the connection section has a first side and an opposite second side. The first and the second blade unit are radially outward extended from the first and the second side, respectively, of the connection section. By providing the first and the second blade unit around the hub of a centrifugal fan, the air flows and air pressure produced by the centrifugal fan can be largely increased at effectively reduced noise. | 04-04-2013 |
20130115087 | Axial Fan - An axial fan has a hub whose axis coincides with the rotational axis of the fan, a plurality of vanes that extend from the hub, and an outer ring which is coaxial with the hub. The ring has a front portion and a rear portion. The outer ring defines within itself a passage towards the rear portion. The radially outermost ends of the vanes are connected to the inner surface of the passage. The rear portion of the ring has a plurality of appendages that extend axially away from the front portion of the ring, and which alternate circumferentially with corresponding intermediate recesses. Each vane has its radially outermost end connected to an inner surface of one of the appendages. | 05-09-2013 |
20130129513 | CENTRIFUGAL FAN IMPELLER STRUCTURE - A centrifugal fan impeller structure includes a hub and a second annular body. The hub has an extension section. A first annular body is connected to a free end of the extension section. The first annular body has a first side and a second side. A first blade set is disposed on the first side. The second annular body has a third side and a fourth side. A second blade set is disposed on the third side. The fourth side is mated and connected with the second side. The centrifugal fan impeller structure is able to greatly increase air volume and wind pressure of the fan. Moreover, in operation, the centrifugal fan impeller structure makes less noise. | 05-23-2013 |
20130170994 | DEVICE AND METHOD FOR ALIGNING TIP SHROUDS - A device for aligning tip shrouds includes a platform configured to connect to a blade, a first projection that extends circumferentially across at least a portion of the platform, and a first complementary alignment feature on the first projection. A method for aligning tip shrouds includes rotating a plurality of tip shrouds, wherein each tip shroud is coupled to a blade, and aligning adjacent tip shrouds by nesting a first alignment feature of a first tip shroud into a second alignment feature of a second tip shroud. | 07-04-2013 |
20130202439 | ROTATING ASSEMBLY FOR A TURBINE ASSEMBLY - A rotating assembly for a turbine assembly includes an airfoil extending radially outward from, and rotatable about, an axial centerline. Also included is a tip shroud integrally connected proximate a radially outer tip of the airfoil. Further included is a substrate operably coupled to the tip shroud. Yet further included is at least one hard face interface member secured to the substrate. | 08-08-2013 |
20130266446 | RINGED AIRFOIL WITH MIXING ELEMENTS - A shrouded fluid turbine includes a ringed airfoil having a leading edge, a trailing edge, an outer surface, an inner surface, and a body extending from the leading edge to the trailing edge. The shrouded turbine further includes a rotor surrounded by the ringed airfoil. The rotor is disposed downstream of the leading edge and about a central axis of the fluid turbine. The shrouded turbine further includes an aperture extending through the body of the ringed airfoil between the outer surface and the inner surface. The aperture is configured to mix a first fluid flow adjacent to the outer surface of the ringed airfoil and a second fluid flow downstream of the rotor. | 10-10-2013 |
20130336794 | F-class Gas Turbine Compressor Exit Guide Vane Repair - A system and method for repairing a turbine. The method includes applying a coating on an outer surface of a tenon that extends from a stator vane. The tenon may be inserted at least partially into an opening defined by an inner shroud segment of the turbine. A bushing may be inserted at least partially into the opening in the inner shroud segment of the turbine such that the tenon becomes at least partially disposed within an opening defined by the bushing. A bolt may be inserted through the opening in the bushing and at least partially into an opening defined by the tenon. The bolt may be threadably engaged with the tenon. | 12-19-2013 |
20140003948 | Repair Of A Shrouded Blade | 01-02-2014 |
20140056710 | Propeller For Ventilator, With A Variable Chord Length - A blower wheel comprises a hub, a guide and blades extending radially between the hub and the guide, each blade comprising a root at its junction with the hub and a head at the junction with the guide, each blade having a leading edge and a trailing edge between which, at each flattened cross section, a chord is defined. For each blade, between the root and the head, the length of the chord varies and the variation in the length of chord between the root and the head has a point of inflexion between two levels. | 02-27-2014 |
20140119922 | IMPELLER FOR CENTRIFUGAL FAN AND CENTRIFUGAL FAN - An impeller for a centrifugal fan includes a main plate having a disc shape, a plurality of blades arranged along a circumferential direction about a center part of the main plate, and an outer ring having a ring shape connecting the respective blades. The outer ring is connected to tip end portions of the respective blades at a side of a fluid discharge opening, and each of the blades has a shape which is bent in a rotating direction of the impeller in a vicinity of the tip end portion. | 05-01-2014 |
20140133988 | Centrifugal fan and air conditioner using the same - A centrifugal fan and an air conditioner using the same are provided. A gurney flap having a rectangular plate or a S-shaped, twisted gurney flap may be formed in a tip of a blade provided in or on a hub of the centrifugal fan, so that noise may be effectively reduced, and efficiency increased. Further, the blade with the gurney flap may be easily formed integrally with the hub, enhancing productivity. | 05-15-2014 |
20140147282 | FAN STRUCTURE - A fan structure includes a hub and at least one set of blades connected to and extending away from the hub, each of the blades having a plurality of steps with a height difference formed away from the periphery of the hub, the height of the inside one of the steps higher than that of the outside one of the steps, thereby providing a disturbed flow-guiding effect so as to enhance the air pressure and the air flow of the wind flow field. | 05-29-2014 |
20140147283 | METHOD FOR MODIFYING A AIRFOIL SHROUD AND AIRFOIL - According to one aspect of the invention, a method is provided for modifying an airfoil shroud located at a tip of an airfoil of a airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut. | 05-29-2014 |
20140147284 | METHOD FOR MODIFYING AN AIRFOIL SHROUD - A turbine engine, bucket and method for modifying an airfoil shroud of turbine bucket is disclosed. A reference location is located in a second end edge of the airfoil shroud proximate a seal rail of the airfoil shroud. A relief cut is formed in the airfoil shroud to remove the reference location. Additionally, another reference location may be located in a first end edge of the airfoil shroud proximate the seal rail. Another relief cut may be formed in the airfoil shroud to remove the other reference location. | 05-29-2014 |
20140169972 | FAN WITH INTEGRAL SHROUD - An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils. | 06-19-2014 |
20150064010 | Turbine Bucket Tip Shroud - The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface. | 03-05-2015 |
20150064011 | FAN AND IMPELLER THEREOF - An impeller includes a fan frame, a hub, a plurality of axial blades and a plurality of wind guiding blades. The fan frame has a wind inlet, a wind outlet and an inner ring-shaped oblique surface, wherein the wind inlet is opposite to the wind outlet, and the inner ring-shaped oblique surface is formed at an inner side wall of the fan frame and adjacent to the wind inlet. The hub is disposed in the fan frame. The axial blades are connected to the inner side wall of the fan frame and the hub. The wind guiding blades protrude from the inner ring-shaped oblique surface. | 03-05-2015 |
20150071782 | FAN IMPELLER - A fan impeller for the conveyance of a gaseous fluid includes several blades arranged with constant angular spacing around a rotation axis. At least one blade has a boundary zone and an inner zone, together with a bead extending between them along a curved path and/or the boundary zone is determined by a first blade surface and the inner zone is determined by a second blade surface, which are arranged with varying geometry. | 03-12-2015 |
20150354394 | SHROUD ABRADABLE COATINGS AND METHODS OF MANUFACTURING - Methods of manufacturing turbine shrouds with an abradable coating that balance the apparently contradictory requirements of high flowpath solidity, low blade tip wear, and good durability in service may include forming an abradable coating on a surface of a coating system to form a substantially smooth flowpath surface. Forming the abradable coating includes forming a relatively porous, smooth abradable coating. The methods may also include machining the abradable so as to achieve a substantially smooth flowpath surface. | 12-10-2015 |
20150360760 | PROPULSION DEVICE FOR SHIP - A propulsion device for a ship is introduced. The propulsion device for the ship comprises a duct having a nose corresponding to the front vertex of a hydrofoil cross-section and a tail corresponding to the rear vertex of the hydrofoil cross-section, wherein the shape of the duct cross-section comprises: an outer surface formed upward in a convex shape at the front end of the duct and formed downward in a concave shape at the rear end of the duct; an inner front part of the duct formed downward in a convex shape at the front end of the duct; an inner rear part of the duct formed downward in a convex shape at the rear end of the duct; and a parallel part for connecting the inner forward part and the inner backward part in parallel to each other. | 12-17-2015 |
20150377246 | IMPELLER FOR A CENTRIFUGAL SLURRY PUMP - A improved impeller for use in a centrifugal slurry pump is provided, comprising: a top shroud; a bottom shroud; and a middle portion therebetween, said middle portion having at least one substantially vertical wall defining a slurry flow channel, wherein the top shroud, bottom shroud and middle portion are configured as one piece to together define a first unitary body; at least one vane nose positioned at a leading edge of the at least one substantially vertical wall; and, optionally, a retaining ring mounted over the top shroud to secure the vane nose within the body. | 12-31-2015 |
20160001406 | ROTATION PART OF ROTARY MACHINE AND METHOD OF MANUFACTURING THE SAME - There is provided a rotation part of a rotary machine, the rotation part including: a base unit including a surface constituting fluid channels; a plurality of blade units protruding from the base unit; a plurality of shroud segment support units connected to the plurality of blade units and extending in a parallel direction to the surface of the base unit; a shroud segment disposed between and bonded to adjacent shroud segment support units of the plurality of shroud segment support units; and a first reinforcing unit provided on an intersection portion between a blade unit of the plurality of blade units and a shroud segment support unit of the plurality of shroud segment support units, wherein a distance from a protruding direction center line of the blade unit to an end portion of the shroud segment support unit is greater than a maximum distance from the protruding direction center line of the blade unit to an end portion of the first reinforcing unit. | 01-07-2016 |
20160003257 | METHOD FOR MAKING AN IMPELLER FROM SECTOR SEGMENTS - A manufacturing technique for impellers for a centrifugal rotating machine is provided. The impeller is made by composition of single vanes pieces that fit to the hub or directly to the rotor shaft by welding, friction welding or a mechanical locking system. The manufacturability of the segments is easy fast and cheap and make it possible to use advanced manufacturing technologies like additive manufacturing of the type of Direct Metal Laser Melting. | 01-07-2016 |
20160017721 | COMPOSITE TURBINE COMPONENTS ADAPTED FOR USE WITH STRIP SEALS - A turbine shroud for a turbine of a gas turbine engine is disclosed. The turbine shroud is configured to direct products of a combustion reaction in a combustor of the gas turbine engine toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate. | 01-21-2016 |
20160032733 | OUTER SHROUD WITH GUSSET - A turbine blade comprises an airfoil. An outer shroud at a tip of the airfoil, has a main surface facing the airfoil and forming a first plateau. A gusset or gussets have a periphery raising from the main surface, and a second plateau between the periphery and the airfoil. A gas turbine engine with such turbine blade is also provided. | 02-04-2016 |
20160090855 | TURBINE WHEEL FOR A TURBINE ENGINE - A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities. | 03-31-2016 |
20160115816 | GAS TURBINE ENGINE WITH SEAL INSPECTION FEATURES - A turbine shroud of a turbine of a gas turbine engine and methods of making the turbine shroud are disclosed. The turbine shroud is configured to direct products of a combustion reaction in a combustor of the gas turbine engine toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate. | 04-28-2016 |
20160115967 | CENTRIFUGAL FAN, AIR-CONDITIONING APPARATUS, AND METHOD OF MANUFACTURING CENTRIFUGAL FAN - A centrifugal fan | 04-28-2016 |
20160177786 | TURBINE SHROUD | 06-23-2016 |
20160186770 | METHOD OF MANUFACTURING CENTRIFUGAL FAN - A method of manufacturing a centrifugal fan is provided that includes cutting a metal sheet to form a positive pressure surface forming member and a negative pressure surface forming member, respectively, forming a positive pressure surface and a negative pressure surface; pressing the positive pressure surface forming member and the negative pressure surface forming member to form a first curved surface forming the positive pressure surface and a second curved surface forming the negative pressure surface; trimming the positive pressure surface forming member provided with the fast curved surface and the negative pressure surface forming member provided with the second curved surface to form a shroud bonding surface and a main plate bonding surface; bending the shroud bonding surface and the main plate bonding surface; bonding the positive pressure surface forming member and the negative pressure surface forming member to each other; and bonding the shroud bonding surface and a shroud to each other and bonding the main plate bonding surface and a main plate to each other in a bonded state of the positive pressure surface forming member and the negative pressure surface forming member. | 06-30-2016 |