Patent application number | Description | Published |
20090215599 | DISPOSABLE SERVINGWARE CONTAINERS WITH FLANGE TABS - Disposable containers include peripheral tabs which are useful for positioning and processing the containers and operate as separators. In a preferred embodiment, the tabs correspond to tabs on a paperboard blank where the tabs are useful for controlling the orientation of the blanks so that printed and shape features may be kept in registration during manufacturing of a disposable servingware container. | 08-27-2009 |
20090232926 | SEGMENTED PRESSWARE DIE SET WITH ANTI-TWIST GUIDE KEYS - A heated, segmented pressware die set for making pressware containers from a paperboard blank includes a plurality of guide keys mounted between at least one of an inner member of a punch or die and an outer ring which reciprocates independently. Each guide key extends in an outward direction from the central axis of the die set. The guide keys are positioned, configured and dimensioned to engage the outer ring in order to limit rotation of the outer ring with respect to the inner member of the punch or die. In a preferred construction, the guide keys have radially extending planar surfaces which cooperate with guide channels having like surfaces such that clearances necessary to accommodate thermal expansion are reduced, greatly increasing durability of the tool. | 09-17-2009 |
20110015051 | APPARATUS FOR MAKING PAPERBOARD PRESSWARE WITH CONTROLLED BLANK FEED - An improved apparatus for making pressware features a vacuum belt feeder which accelerates and decelerates a feed blank for controlled insertion into a forming die as well as retainers to limit bounce back of the blank off of forward stops. A pneumatic ejector on the forming ram facilitates product removal | 01-20-2011 |
20140076905 | Pressed Paperboard Servingware with Improved Rigidity and Rim Stiffness - Products and methods of increasing the Rigidity and Rim Stiffness of disposable containers are provided. The containers have an outer flange portion extending outwardly with a brim portion sloping downwardly defining a declivity angle α with respect to a horizontal generally parallel to the bottom portion and generally include an outward turn at the periphery of the container. A preferred method of improving rigidity includes press-forming: (i) a brim transition portion adjoining the downwardly sloping brim portion of the container and (ii) an outwardly extending annular evert portion adjoining the brim transition portion extending outwardly at an eversion angle β of at least about 25 degrees with respect to the downwardly sloping brim portion of the flange. | 03-20-2014 |
Patent application number | Description | Published |
20080298956 | Shroud configuration having sloped seal - A stator shroud segment is provided that includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook, the leading and trailing hooks of each of the inner shrouds being respectively engaged with the leading and trailing edge grooves of the outer shroud so as to axially and radially lock the inner shrouds to the outer shrouds. At least one of the trailing edge hook of the inner shroud and the trailing edge groove of the outer shroud includes a sloped surface disposed at an angle to an axial direction of the rotor and to a radial direction of the rotor and facing the other of the inner and outer shrouds whereby a radial inward force on the inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between the inner and outer shrouds. | 12-04-2008 |
20100072710 | Gas Turbine Seal - A seal is provided for sealing two adjacent components of a gas turbine engine. The seal has first and second sealing surfaces that operate to seal the adjacent components to create an effective seal therebetween. Additionally, the seal has a first end and a second end, with the second end having a necked down portion, which is configured to internally engage the first end in a sliding, overlapping manner. | 03-25-2010 |
20100284800 | TURBINE NOZZLE WITH SIDEWALL COOLING PLENUM - A turbine nozzle segment includes an outer band portion, an inner band portion, and at least one nozzle vane extending between the band portions. A cooling plenum is defined in a mating side face of at least one of the band portions and extends transversely at least partially through the respective band portion. First and second cooling passages extend from the cooling plenum to respective first and second cooling chambers. | 11-11-2010 |
20110110771 | AIRFOIL HEAT SHIELD - Exemplary embodiments include a multi-layer, modular and replaceable heat shield for gas turbines. The heat shield apparatus can include a base layer adjacent the airfoil and a thermal layer coupled to the base layer, wherein the base layer and the thermal layer match a contour of the airfoil. | 05-12-2011 |
20120093632 | VARIABLE TURBINE NOZZLE SYSTEM - A nozzle is disclosed for use in a turbine or compressor. In an embodiment, each of a plurality of vanes is supported by an outer shroud including a plurality of outer shroud segments disposed adjacent to adjoining segments in end-to-end relationship. Each segment includes a hole therethrough, dimensioned to receive a vane extension sleeve. This system may be used in conjunction with a modulated cooling system and may allow for improved removal for overhaul. | 04-19-2012 |
20120280455 | SPRING SEAL ASSEMBLY AND METHOD OF SEALING A GAP - A spring seal assembly includes a first plate and a second plate. One or more spring elements are located between the first plate and the second plate and compressible therebetween. The spring seal assembly is insertable into a gap between two adjacent components such that at least one of the first plate and the second plate at least partially block a flow between the two adjacent components while exerting a force on the two adjacent components to prevent vibration of the seal in the gap. A method of sealing between adjacent components includes at least partially compressing a spring seal assembly. The spring seal assembly is inserted into the gap and allowed to expand in the gap thereby at least partially blocking a flow between the two adjacent components while exerting a force on the two adjacent components to prevent vibration of the seal in the gap. | 11-08-2012 |
20120324898 | COMBUSTOR ASSEMBLY FOR USE IN A TURBINE ENGINE AND METHODS OF ASSEMBLING SAME - A combustor assembly for use with a turbine engine that includes a rotor assembly. The combustor assembly includes a casing that includes a plenum and a combustor liner that is spaced a distance from the plenum and that defines a combustion chamber therein. A transition nozzle extends between the combustor liner and the rotor assembly for channeling combustion gases from the combustion chamber to the rotor assembly. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. An annular flowsleeve is coupled radially outward from the transition nozzle such that an annular flow path is defined between the flowsleeve and the transition nozzle. The flowsleeve includes a plurality of openings extending through an outer surface of the flowsleeve for providing flow communication between the plenum and the annular flow path to facilitate impingement cooling of the flowsleeve. | 12-27-2012 |
20130042668 | HOT GAS PATH MEASUREMENT - A hot gas path measurement apparatus is provided and includes a substrate having a coating applied on a surface thereof such that the coating is interposed between the substrate and a hot gas path; and a measurement device fixed in a recess formed in the substrate, the measurement device including a sensor, and a holder configured to position the sensor in an alignment condition with a plane of a surface of the coating or at least partially within a span of the hot gas path. | 02-21-2013 |
20130280040 | COOLING ASSEMBLY FOR A GAS TURBINE SYSTEM - A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure. | 10-24-2013 |
20130283814 | TURBINE COOLING SYSTEM - A system includes a turbine. The turbine includes a rotor, a stator, and a cooling insert. The rotor includes multiple turbine blades. The stator surrounds the rotor and includes an inner wall surrounding the multiple turbine blades, an outer wall surrounding the inner wall, and a cooling chamber between the inner wall and the outer wall. The cooling insert extends through an opening in the outer wall into the cooling chamber. The insert includes a side wall extending around an axis, an end wall crosswise to the axis, a set of lateral ports extending through the side wall, and end ports extending through the end wall. The cooling insert is configured to direct a cooling fluid through the set of lateral ports and end ports into the cooling chamber. | 10-31-2013 |
20140133971 | ROTATING SEAL CONFIGURATION AND METHOD OF SEALING A ROTATING MEMBER TO A HOUSING - A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face. | 05-15-2014 |
20140338364 | TURBINE ROTOR BLADE FOR A TURBINE SECTION OF A GAS TURBINE - A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls. | 11-20-2014 |
20150056073 | METHOD AND SYSTEM FOR COOLING ROTOR BLADE ANGELWINGS - A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity. The at least one outlet opening is located in an upper surface of the angelwing. The at least one cooling passage receives pressurized cooling air channeled from the inner wheelspace, such that the pressurized cooling air is channeled into the at least one inlet opening and discharged from the at least one outlet opening. | 02-26-2015 |
Patent application number | Description | Published |
20110259015 | Tangential Combustor - A combustion section for a gas turbine includes a casing defining a chamber, a plurality of combustor cans disposed in the casing and oriented in an annular pattern, and a plurality of transition pieces each coupled with one of the combustor cans. The transition pieces direct products of combustion from the combustor cans into contact with rotating buckets of the gas turbine. Each of the transition pieces is angled in two planes to effect turning of the products of combustion and to shorten the gas turbine. | 10-27-2011 |
20120324897 | METHODS AND SYSTEMS FOR TRANSFERRING HEAT FROM A TRANSITION NOZZLE - Methods and systems are provided for transferring heat from a transition nozzle. The transition nozzle includes a transition portion, a nozzle portion integrally formed with the transition portion, and at least one surface feature configured to transfer heat away from the transition portion and/or the nozzle portion. The transition portion is oriented to channel the combustion gases towards the nozzle portion. | 12-27-2012 |
20120328421 | METHODS AND SYSTEMS FOR COOLING A TRANSITION NOZZLE - A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion. | 12-27-2012 |
20130167543 | METHODS AND SYSTEMS FOR COOLING A TRANSITION NOZZLE - A transition nozzle for use with a turbine assembly is provided. The transition nozzle includes a liner defining a combustion chamber therein, a wrapper circumscribing the liner such that a cooling duct is defined between the wrapper and the liner, a cooling fluid inlet configured to supply a cooling fluid to the cooling duct, and a plurality of ribs coupled between the liner and the wrapper such that a plurality of cooling channels are defined in the cooling duct. | 07-04-2013 |