Patent application number | Description | Published |
20080199317 | Local indented trailing edge heat transfer devices - A turbine engine component has an airfoil portion having a pressure side and a suction side, a trailing edge discharge slot, and a suction side lip downstream of an exit of the trailing edge slot. The suction side lip is provided with negative features for increasing local heat transfer coefficient in the region of the suction side lip. | 08-21-2008 |
20090047136 | Angled tripped airfoil peanut cavity - A turbine airfoil comprises a wall portion, a cooling channel, an impingement rib, impingement rib nozzles, turbulators and leading edge cooling holes. The wall portion comprises a leading edge, a trailing edge, an outer diameter end, and an inner diameter end. The cooling channel receives cooling air and extends through an interior of the wall portion between the inner diameter end and the outer diameter end. The impingement rib is positioned within the wall portion forward of the cooling channel and between the outer diameter end and the inner diameter end to define a peanut cavity. The impingement rib nozzles extend through the impingement rib for receiving cooling air from the cooling channel. The turbulators are positioned within the peanut cavity to locally influence the flow of the cooling air. The leading edge cooling holes discharge the cooling air from the peanut cavity to an exterior of the wall portion. | 02-19-2009 |
20090096174 | BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE - An air seal assembly includes a featherseal engaged between adjacent turbine engine components to close a gap therebetween. The featherseal includes a first lateral tab and a second lateral tab which defines a tab space therebetween. The tab space locks the featherseal into the turbine engine component to prevent fore-aft movement thereof. | 04-16-2009 |
20110044795 | TURBINE VANE PLATFORM LEADING EDGE COOLING HOLES - A vane for use in a gas turbine engine has a platform connected to an airfoil. There is a cooling passage for supplying cooling air to the platform. A cooling chamber supplies cooling air to a plurality of cooling slots at the platform. The cooling slots have a non-uniform cross section. | 02-24-2011 |
20130209232 | MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS - A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed. | 08-15-2013 |
20130336767 | COOLING FOR A TURBINE AIRFOIL TRAILING EDGE - An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall. | 12-19-2013 |
20130340966 | BLADE OUTER AIR SEAL HYBRID CASTING CORE - A hybrid sacrificial core for forming an impingement space and an internal cooling passageway network separate from the impingement space of a part may comprise a ceramic core having a first surface portion for forming the impingement space, and a refractory metal core that forms a plurality of passages of the internal cooling passageway network. | 12-26-2013 |
20140047843 | PLATFORM COOLING CIRCUIT FOR A GAS TURBINE ENGINE COMPONENT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity. | 02-20-2014 |
20140060084 | GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT ARRANGEMENT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil. | 03-06-2014 |
20140373549 | COOLING HOLE WITH CURVED METERING SECTION - A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface. The component also includes a diffusing section extending from the metering section to the outlet. A gas turbine engine wall includes first and second surfaces and a cooling hole extending between an inlet at the first surface and an outlet at the second surface. The cooling hole includes a metering section commencing at the inlet and a diffusing section in communication with the metering section and terminating at the outlet. The metering section includes a top portion having a first arcuate surface and a bottom portion having a second arcuate surface. The first and second arcuate surfaces have arcs extending in substantially similar directions. | 12-25-2014 |
Patent application number | Description | Published |
20120101792 | TURBINE COMPONENT AND METHOD FOR DEVELOPING A COMPONENT - A method for developing a component includes establishing a performance requirement to predict the secondary crystallographic orientation for a component having orthogonal x, y, and z axes. The component is to be formed from a single crystal material having a primary crystallographic orientation along the z-axis and a secondary crystallographic orientation substantially in the x-y plane. A property of the component is computer simulated as a function of an angle of the secondary crystallographic orientation relative to the x-axis. Based on the computer simulation, the angle for the component is selected which will substantially satisfy the performance requirement. | 04-26-2012 |
20130017058 | BLADE OUTER AIR SEAL HAVING PARTIAL COATINGAANM Joe; Christopher R.AACI WethersfieldAAST CTAACO USAAGP Joe; Christopher R. Wethersfield CT USAANM Lutjen; Paul M.AACI KennebunkportAAST MIAACO USAAGP Lutjen; Paul M. Kennebunkport MI USAANM Mongillo, JR.; Dominic J.AACI West HartfordAAST CTAACO USAAGP Mongillo, JR.; Dominic J. West Hartford CT US - A blade outer air seal member includes a body that extends between two circumferential sides, axially between a leading edge and a trailing edge, and between a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side outside of a blade rub area of the gas path side such that the blade rub area is bare with regard to any ceramic coating. | 01-17-2013 |
20130205791 | COOLING HOLE WITH CURVED METERING SECTION - A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface. The component also includes a diffusing section extending from the metering section to the outlet. A gas turbine engine wall includes first and second surfaces and a cooling hole extending between an inlet at the first surface and an outlet at the second surface. The cooling hole includes a metering section commencing at the inlet and a diffusing section in communication with the metering section and terminating at the outlet. The metering section includes a top portion having a first arcuate surface and a bottom portion having a second arcuate surface. The first and second arcuate surfaces have arcs extending in substantially similar directions. | 08-15-2013 |
20130206733 | EDM METHOD FOR MULTI-LOBED COOLING HOLE - A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges. | 08-15-2013 |
20130251538 | TRAILING EDGE COOLING - An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, a cooling passageway, and a plurality of oblong pedestals. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil. The cooling passageway is located between the suction surface and the pressure surface. The oblong pedestals connect the suction surface to the pressure surface at the trailing edge of the airfoil. | 09-26-2013 |
20130251539 | TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION - An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis. | 09-26-2013 |
20130266454 | TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING - An airfoil comprises leading and trailing edges with pressure and suction surfaces defining a chord length therebetween. The pressure and suction surfaces extend from a root section of the airfoil to a tip section. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate between 10% and 25% of the chord length measured from the trailing edge. | 10-10-2013 |
20130280081 | GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS - A core for an airfoil includes a refractory metal structure having a variable thickness. An airfoil includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness, and the second thickness is less than 0.060 inch (1.52 mm). A method of manufacturing a refractory metal core includes depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of a refractory metal core, and producing the core having a variable thickness. | 10-24-2013 |
20130280091 | GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING - An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil. | 10-24-2013 |
20130280093 | GAS TURBINE ENGINE CORE PROVIDING EXTERIOR AIRFOIL PORTION - A core has a body that includes a cooling passage portion with a film cooling passage portion extending there from to a film cooling hole portion. An exterior airfoil portion is connected to the film cooling hole portion and is spaced apart from the cooling passage portion to provide a space surrounding the film cooling hole portion that corresponds to an exterior airfoil wall. | 10-24-2013 |
20140056717 | GAS TURBINE ENGINE AIRFOIL INTERNAL COOLING FEATURES - An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and suction walls to provide cooling passageways. The cooing passageways have interior pressure and suction surfaces that are respectively provided on the pressure and suction walls. Trip strips include a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces. | 02-27-2014 |
20140137407 | METHOD OF EXTENDING LIFE OF ROTATING PARTS - A method of refurbishing a gas turbine engine rotor is disclosed and includes an initial step of inspecting a rotor for defects such as cracks. A strain is then generated around any detected cracks in the rotor to create enhanced plasticized zones about the detected defects that delay defect propagation. Strain is generated by rotating the rotor at speeds greater than operational speeds to induce the desired strain and delay the propagation of defects. | 05-22-2014 |
20140208771 | GAS TURBINE ENGINE COMPONENT COOLING ARRANGEMENT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion having an exterior surface and an internal surface. A cavity is disposed inside of the body portion. A cooling hole extends between the exterior surface and the internal surface and includes a metering section having an outlet and an inlet. The inlet is shaped dissimilar to the outlet. | 07-31-2014 |
20140212297 | GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS - A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing. | 07-31-2014 |
20140219813 | GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE - A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion | 08-07-2014 |
Patent application number | Description | Published |
20080270550 | Electronic mail connector - Technologies are described herein for providing a bi-direction e-mail transport between a management (“CRM”) server computer and an e-mail server computer. An e-mail connector communicates with a CRM server computer to determine whether any e-mail messages are pending send at the CRM server computer. If any e-mail messages are pending send, the e-mail connector retrieves the e-mail messages from the CRM server computer. The e-mail connector then communicates with an e-mail server computer to send the retrieved e-mail messages to their intended recipients. The e-mail connector may also retrieve e-mail messages from the e-mail server computer and determine whether the e-mail messages are CRM related. If the e-mail messages are CRM related, the e-mail connector is operative to transmit the CRM-related e-mails to the CRM server. | 10-30-2008 |
20080275957 | Identifying and correlating electronic mail messages - Technologies are described herein for identifying and correlating e-mail messages. The contents of the subject and recipients fields of e-mail messages received at and sent from a computing system are hashed and stored in a database. When an incoming e-mail message is received at the computing system, the contents of its subject and recipients fields are also hashed. A search is then made of the database to locate e-mail messages identified in the database that have a sufficient number of subject and address hash values that match the subject and address hash values generated for the incoming e-mail message so that the messages may be correlated. A correlation is made between the incoming e-mail message and the best matching e-mail message located during the search of the database. | 11-06-2008 |
20090007250 | Client authentication distributor - The claimed method and system provides a client authentication distributor component (CAD) that handles multiple client application requests for authentication to a common authentication provider. In one embodiment, only a single user sign on process may be required after which the CAD manages future authentication processes on behalf of the user without the user requiring to provide credentials. | 01-01-2009 |
20090064303 | TRANSFERABLE RESTRICTED SECURITY TOKENS - In a web-based service environment, third party providers need to have varying degrees of access to user data for their complementary services. To prevent third party providers from having broader access than necessary or not adequate levels of access, transferable restricted security tickets are employed to determine an appropriate level of access for third parties. Tickets with expiration and restriction roles define a duration and level of access for a third party. The restrictions are determined through an intersection of the authorizing user's security role and restriction roles defined in the system. | 03-05-2009 |
20140149517 | SYSTEMS AND METHODS FOR MIGRATING MAILBOX DATA FROM SYSTEMS WITH LIMITED OR RESTRICTED REMOTE ACCESS - Examples described include software hosting systems able to provide software as a service to client systems through a firewall and/or to client systems which do not have web service capability. Examples include mailbox migration systems for migrating mailboxes from a source messaging system (e.g. a Lotus Notes system) to a destination messaging system. Software hosting systems described herein may maintain an action buffer including a next action to be performed by the source messaging system, and wait for data (e.g. messaging system content) to be returned and stored in a data buffer. Communication between the software hosting system and the source messaging system may occur over a communication channel which may be operated through a firewall using HTTP. | 05-29-2014 |
Patent application number | Description | Published |
20110180459 | METHODS FOR EXTRACTING BITUMEN FROM BITUMINOUS MATERIAL - Methods for preparing solvent-dry, stackable tailings. The method can include the steps of adding a first quantity of first solvent to a bitumen material to form a first mixture, separating a first quantity of bitumen-enriched solvent from the first mixture and thereby creating first solvent-wet tailings, adding a quantity of second solvent to first solvent-wet tailings to separate a first quantity of first solvent component from the first solvent-wet tailings and thereby producing second solvent-wet tailings, and adding a quantity of water to the second solvent-wet tailings to separate a first quantity of second solvent component from the second solvent-wet tailings and thereby forming solvent-dry, stackable tailings. | 07-28-2011 |
20120152809 | Methods and Apparatus for Bitumen Extraction - Methods and system for extracting bitumen can include the use of a mixing drum for spraying solvent over bituminous material to help dissolve bitumen and create a bitumen-laden solvent phase that can be separated from the non-bituminous components of the bituminous material. The mixing drum can be rotating during the spraying step to help promote dissolution of bitumen. The mixing drum can also include an internal screen for separating bitumen-laden solvent from the non-bituminous material. In some embodiments, two or more mixing drums are used in series, with the non-bituminous material from the first mixing drum being sprayed with additional solvent in the second mixing drum and bitumen laden solvent from the second mixing drum being used as the solvent sprayed over bituminous material in the first mixing drum. Hydrocyclones can also be incorporated in the in system and methods for increased extraction efficiency. | 06-21-2012 |
20130026077 | Methods and Apparatus for Bitumen Extraction - A bitumen extraction method can include the use of a two or more mixing drums aligned in series for spraying solvent over bituminous material and/or tailings loaded in the mixing drums while the mixing drums rotate. Such mixing can result in the dissolution of bitumen into the solvent, which then allows for the separation of a “dilbit” stream from the bituminous material. | 01-31-2013 |
20130026078 | Methods for Extracting Bitumen From Bituminous Material - Methods for preparing solvent-dry, stackable tailings. The method can include the steps of adding a first quantity of solvent to a bitumen material to form a first mixture, separating a first quantity of bitumen-enriched solvent from the first mixture and thereby creating solvent-wet tailings, and adding a quantity of water to the solvent-wet tailings to separate a solvent component from the solvent-wet tailings and thereby forming solvent-dry, stackable tailings. The solvent used in the methods can include paraffinic solvent, such as pentane. | 01-31-2013 |
20130092599 | METHODS AND SYSTEMS FOR UPGRADING HYDROCARBON - Methods and systems of upgrading hydrocarbon material, such as bituminous material, are described. The methods and systems can reduce or eliminate the need for the use of atmospheric and/or vacuum distillation towers by instead using clyconic separation apparatus. The methods and systems can include the use of one or more cyclonic separation apparatus aligned in series in order to separate out a high boiling point fraction of the hydrocarbon material and then upgrading the high boiling point hydrocarbon material in a nozzle reactor. | 04-18-2013 |
20130161238 | Methods and Systems for Removing Material from Bitumen-Containing Solvent - Methods and systems for preparing bitumen-laden solvent for downstream processing are described. The bitumen-laden solvent can be treated with various materials, such as water and emulsion breakers, followed by treating the bitumen-laden solvent in a desalter. The desalted bitumen-laden solvent can then be subjected to downstream processing, such as upgrading in a nozzle reactor. | 06-27-2013 |
20130251597 | NOZZLE REACTOR AND METHOD OF USE - A nozzle reactor includes a passage having one or more regions with a converging-diverging shape. The nozzle reactor accelerates a reacting fluid to supersonic velocities and mixes it with a feed material. The reacting fluid and the feed material may be pre-heated. The high speed collision between the reacting fluid and the feed material at elevated temperatures causes the materials to react. | 09-26-2013 |
20130341245 | Methods and Systems for Upgrading Hydrocarbon Residuum - A hydrocarbon upgrading method is described. The method can generally include a step of providing a nozzle reactor, a step of injecting hydrocarbon residuum into the feed passage of the nozzle reactor, and a step of injecting a cracking material into the main passage of the nozzle reactor, and a step of collecting a product stream exiting the exit opening of the main passage of the nozzle reactor. The hydrocarbon residuum used in the method can be obtained from a hydroconversion-type upgrader, such as an ebullating bed hydrocracker. | 12-26-2013 |