Did You Know...
...that Charles Goodyear performed some of his experiments on rubber while in debtor's prison? He was there so often he referred to it as his "hotel". Chronically in debt because of poor business sense and ill health, Goodyear depended on the generosity of friends and family. Even after he unlocked the secret to vulcanizing rubber, he was unable to improve his financial situation. When he died, his estate was $200,000 in debt.
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| Number | Title | Issue Date |
| 8127443 | Method of fabricating a rocket engine nozzle using pressure brazing A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then ... | 03/06/2012 |
| 7941920 | Blade outer seal assembly and method An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereb... | 05/17/2011 |
| 7836596 | Turbine engine rotor retaining methods A rotor stack is assembled to a turbine engine shaft. A force is exerted to at least one of the rotor stack and the shaft to at least one of place the shaft under tension and place the rotor stack under compression. One or more retainer segments are inserted into a ... | 11/23/2010 |
| 7721437 | Methods for assembling gas turbine engine combustors A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, secu... | 05/25/2010 |
| 7721436 | Method of manufacturing a metal injection moulded combustor swirler A combustor swirler for a gas turbine engine and method of manufacturing by metal injection molding an inner component and an outer cylindrical component. Indentations are molded in one of the inner and outer components and sealed by the engagement of the components... | 05/25/2010 |
| 7520055 | Method for manufacturing a stator or rotor component A method for manufacturing a stator or rotor component (8) for a gas turbine in which at least one wall element (3) is joined together with at least one ring element (9). The edges of the wall element (3) are laser-welded firmly on the ri... | 04/21/2009 |
| 7442006 | Integral diffuser and deswirler with continuous flow path deflected at assembly An integrated assembly is provided for a centrifugal compressor, which integrates selected static portions of the centrifugal compressor into a monolithic structure to allow a small deflection of the inner flow path at assembly. The integrated assembly may include a... | 10/28/2008 |
| 7430802 | Labyrinth seal in a stationary gas turbine The invention relates to a segmented inner ring for holding guide blades. According to the invention, a lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially, and respectively one half of... | 10/07/2008 |
| 7416389 | Methods and apparatus for assembling rotatable machines Methods and systems for ordering blades in a rotatable machine is provided. The method includes receiving at least one geometric parameter measurement of each blade in a row of blades, determining a root sum squared value of a difference of a selected one of the rec... | 08/26/2008 |
| 7389583 | Method of manufacturing a stator component The invention relates to a method for manufacturing a stator component that is intended in operation to guide a gas flow and to transfer loads. The component is constructed of at least two sectors in the direction of its circumference. The sectors are cast in separa... | 06/24/2008 |
| 7377036 | Methods for tuning fuel injection assemblies for a gas turbine fuel nozzle A fuel nozzle assembly for a gas turbine includes a plurality of circumferentially spaced vanes with holes for flowing fuel from plenums within the vanes through holes in the vane walls for premixing with air. To tune the nozzle assembly, the holes are resized by re... | 05/27/2008 |
| 7363762 | Gas turbine engines seal assembly and methods of assembling the same A method of assembling a gas turbine engine includes providing a gas turbine engine including a compressor, a combustor downstream from the compressor, and a turbine coupled to the compressor, and coupling a seal assembly aft of the compressor such that air discharg... | 04/29/2008 |
| 7360988 | Methods and apparatus for assembling turbine engines A method facilitates the assembly of a gas turbine engine. The method comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, wherein the vane includes a first sidewall and a sec... | 04/22/2008 |
| 7360990 | Methods and apparatus for assembling gas turbine engines A method enables a variable vane assembly for a gas turbine engine including a casing and an inner shroud to be assembled. The method comprises providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional ... | 04/22/2008 |
| 7341427 | Gas turbine nozzle segment and process therefor A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle... | 03/11/2008 |
| 7331755 | Method for coating gas turbine engine components A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and exec... | 02/19/2008 |
| 7322796 | Turbine vane construction A method for forming a component for use in a gas turbine engine, such as a turbine vane construction is provided. The method broadly comprises the steps of: forming a first aerodynamic structure having a first platform with a leading edge and a trailing edge, and a... | 01/29/2008 |
| 7320175 | Production process of gas turbine The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbi... | 01/22/2008 |
| 7311495 | Vane support in a gas turbine engine A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane ... | 12/25/2007 |
| 7287958 | Methods and apparatus for assembling rotatable machines A method, rotor assembly, and apparatus for ordering blades in a rotatable machine is provided. The rotor assembly includes a disk including a plurality of circumferentially-spaced blade root slots defined therein, and a plurality of blades, each blade including a r... | 10/30/2007 |
| 7278821 | Methods and apparatus for assembling gas turbine engines A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within ea... | 10/09/2007 |
| 7260892 | Methods for optimizing turbine engine shell radial clearances A method facilitates the assembly of a stator assembly for a turbine engine. The method includes providing a cantilevered shell including a first end and a second end, and coupling a second member within the turbine engine. The method also includes coupling the shel... | 08/28/2007 |
| 7255929 | Use of spray coatings to achieve non-uniform seal clearances in turbomachinery The invention provides spray coatings to achieve circumferentially non-uniform seal clearances in turbomachines. In steam and gas turbines it is desirable to assemble the machines with elliptical seal clearances to compensate for expected casing distortion, rotordyn... | 08/14/2007 |
| 7249929 | Bleed housing A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint ... | 07/31/2007 |
| 7238003 | Vane attachment arrangement A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing. ... | 07/03/2007 |
| 7200933 | Method for manufacturing a stator component Method and arrangement for providing a stator component intended during operation to conduct a gas flow. The component is made up of at least two sections (113) in its circumferential direction, which sections each have at least one wall part (101, 102... | 04/10/2007 |
| 7195452 | Compliant mounting system for turbine shrouds The mounting of low expansion full ring shrouds in a turbine engine requires radial compliance to limit the stresses experienced by the shroud due to thermal growth differences between the shroud and its support. A method provides radial compliance with no looseness... | 03/27/2007 |
| 7185433 | Turbine nozzle segment and method of repairing same A method for repairing a stationary turbine nozzle segment having at least one vane disposed between outer and inner structural bands includes providing an engine-run turbine nozzle segment having at least one vane disposed between outer and inner bands, wherein the... | 03/06/2007 |
| 7186070 | Method for modifying gas turbine nozzle area A method of modifying a turbine nozzle area comprises depositing a thermal barrier coating (TBC) on the nozzle endwalls to provide a minimum nozzle area, evaluating an airflow through the nozzle, and machining the TBC to increase the nozzle area. Adjacent segment ar... | 03/06/2007 |
| 7179052 | Assembly type nozzle diaphragm, and method of assembling the same A nozzle diaphragm assembly includes a diaphragm outer ring having a groove opened toward an inner diameter side to be continuous in an inner peripheral direction; a diaphragm inner ring having a groove opened toward an outer diameter side to be continuous in an out... | 02/20/2007 |
| 7172389 | Method for making a repaired turbine engine stationary vane assembly and repaired assembly A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the ... | 02/06/2007 |
| 7165937 | Methods and apparatus for maintaining rotor assembly tip clearances A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferen... | 01/23/2007 |
| 7160078 | Mechanical solution for rail retention of turbine nozzles A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment se... | 01/09/2007 |
| 7147434 | Nozzle ring with adhesive bonded blading for aircraft engine compressor Blades (3) extending radially from the inner shroud (1) to the outer shroud (2) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive. ... | 12/12/2006 |
| 7140835 | Corner cooled turbine nozzle A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore... | 11/28/2006 |
| 7128522 | Leakage control in a gas turbine engine A gas turbine engine expansion joint comprises first and second members having confronting faces defining a gap therebetween. At room temperature, the gap varies in accordance with the temperature distribution profile of the first and second members during normal en... | 10/31/2006 |
| 7114927 | Fixing method for the blading of a fluid-flow machine and fixing arrangement A fixing method for blading of a fluid-flow machine, in which first of all the turbine blades (31, 32) are inserted into the fastening slot (1) of a rotor (2) or stator until only the intermediate fitting gap is left... | 10/03/2006 |
| 7097420 | Methods and apparatus for assembling gas turbine engines A method of assembling a gas turbine engine includes providing a plurality of stator vane sectors that each include an equal number of stator vanes that are circumferentially-spaced such that a first circumferential spacing is defined between each pair of adjacent s... | 08/29/2006 |
| 7090464 | Methods and apparatus for assembling rotatable machines A method and apparatus for ordering blades in a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method includes determining a moment weight of each blade in a row of blades, determining a geo... | 08/15/2006 |
| 7048504 | Machine stator and mounting and dismounting methods A machine stator and assembly and disassembly methods. The elements of a casing portion are formed of consecutive shells in line with grooves configured to house roots of guide vane stages that are fixed in place by springs and pins for stopping rotation. The elemen... | 05/23/2006 |
