Did You Know...
...that in 1800 ether was first used by partyers as a fun diversion? Sniffing the gas led to hilarious and raucous laughter as people watched each other become more and more intoxicated and silly. Several doctors independently realized the value ether would have to anesthetize surgery patients. Of those who claimed rights to the "discovery," none had a happy ending. One had a seizure and died defending his rights. Another spent his life in an asylum because he had been denied acclaim. A third became addicted to chloroform and, in a New York City jail, he soaked a cloth in the drug, severed an artery and bled to death.
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| Number | Title | Issue Date |
| 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 |
| 7308794 | Combustor and method of improving manufacturing accuracy thereof An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and an interior directly exposed to a combustion region of the combustor... | 12/18/2007 |
| 7299622 | Component for being subjected to high thermal load during operation and a method for manufacturing such a component Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) tha... | 11/27/2007 |
| 7278256 | Pulsed combustion engine A pulsed combustion apparatus includes a conduit having an outer wall and an inner wall. The inner wall has a number of apertures. An interior space is separated from the outer wall by the inner wall. An induction system is positioned to cyclicly admit charges to th... | 10/09/2007 |
| 7278825 | Method and system for regulating fluid over an airfoil or a hydrofoil The present invention features a fluid flow regulator that functions to influence fluid flow across an airfoil or hydrofoil, as well as various rotating or rotary devices, including propellers, impellers, turbines, rotors, fans, and other similar devices, as well as... | 10/09/2007 |
| 7266945 | Fuel injection apparatus A fuel injection apparatus (10) for a gas turbine engine (110) comprising a prefilmer (26), the prefilmer (26) comprises a body (50), the body (50) defines an axis (51), an annular surface (40) and a downstream... | 09/11/2007 |
| 7204089 | Arrangement for the cooling of thermally highly loaded components An inexpensively manufacturable arrangement for the cooling of thermally highly loaded components, for example the combustion chamber of a gas turbine, comprises cavities (4) provided on the thermally loaded inner surface/air exit side (3) of the wall ... | 04/17/2007 |
| 7191665 | Support for a reflective target A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating te... | 03/20/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7140185 | Heatshielded article A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated co... | 11/28/2006 |
| 7137383 | Capillary fuel injector with metering valve for an internal combustion engine A fuel injector for vaporizing a liquid fuel for use in an internal combustion engine. The fuel injector includes at least one capillary flow passage, a heat source arranged along the at least one capillary flow passage, the heat source operable to heat the liquid f... | 11/21/2006 |
| 7124588 | Combustion chamber of gas turbine with starter film cooling A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumfere... | 10/24/2006 |
| 7121096 | Gas turbine engine combustor A combustor for a gas turbine engine comprising a combustion chamber wall having formed therein at least one hole for admitting air into the combustion chamber and at least one air intake chute aligned with said hole. The air intake chutes are attached to the combus... | 10/17/2006 |
| 7114321 | Thermal isolation device for liquid fuel components A thermal isolation device for a gas turbine combustor assembly includes a plurality of substantially flat plates secured in spaced relationship by a plurality of columns, at least one column incorporating a bolt hole for use in securing the device between a pair of... | 10/03/2006 |
| 7104068 | Turbine component with enhanced stagnation prevention and corner heat distribution Aspects of the invention relate to a system for reducing stagnation between substantially adjacent components while providing enhanced heat distribution properties in the corners and edges of the components. Each component is generally hollow and has two walls dispo... | 09/12/2006 |
| 7104067 | Combustor liner with inverted turbulators A combustor liner for a gas turbine, the combustor liner having a substantially cylindrical shape; and a plurality of axially spaced circumferential grooves formed in an outside surface of the combustor liner. ... | 09/12/2006 |
| 7096668 | Cooling and sealing design for a gas turbine combustion system An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received... | 08/29/2006 |
| 7093439 | Heat shield panels for use in a combustor for a gas turbine engine The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plu... | 08/22/2006 |
| 7093837 | Turbine spring clip seal An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal is composed of inner and outer housings and a center sealing member disposed between the inner and outer housings. The center sealing m... | 08/22/2006 |
| 7089748 | Combustion chamber, in particular of a gas turbine The invention relates to a combustion chamber, in particular of a gas turbine, comprising an external wall structure that surrounds an internal area and an internal wall, which is formed by the surface of a housing that is located in the internal area. Said combusti... | 08/15/2006 |
| 7089741 | Gas turbine combustor A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion l... | 08/15/2006 |
| 7086232 | Multihole patch for combustor liner of a gas turbine engine A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from imping... | 08/08/2006 |
| 7082771 | Combustion chamber A combustion chamber (4) of a gas turbine (1), the combustion space (24) of which is bounded by an annular combustion chamber inner wall (28) and a combustion chamber outer wall (26), in which in order to generate a working medium ... | 08/01/2006 |
| 7080514 | High frequency dynamics resonator assembly Aspects of the invention relate to resonator assemblies for use in non-uniform flow environments. The resonator assemblies include one or more features, such as a box or a scoop, for substantially equalizing the pressure on the resonator. In the box configuration, a... | 07/25/2006 |
| 7051532 | Methods and apparatus for film cooling gas turbine engine combustors A method facilitates assembling a combustor for a gas turbine engine. The method includes providing a dome assembly that includes at least one cooling slot lip and at least one filler projection, wherein a gap defined between the cooling slot lip and the at least on... | 05/30/2006 |
| 7051531 | Flow control body In order to develop a flow control body (6) for separate control of a cooling fluid inflow and a cooling fluid outflow for combustion chambers with a closed cooling system for turbines such that a simplified cooling fluid flow control is made possible in the ... | 05/30/2006 |
| 7047722 | Small scale hybrid engine (SSHE) utilizing fossil fuels This invention describes a miniaturized hybrid diesel-electric engine formed by a closed-loop system powered by plasma-aided combustion of JP-8 fuel (or other hydrocarbon fuels) working in tandem with a vapor cycle utilizing miniaturized expanders and condensers. Th... | 05/23/2006 |
| 7048505 | Method and system for regulating fluid flow over an airfoil or a hydrofoil The present invention features a fluid flow regulator that functions to significantly influence fluid flow across an airfoil or hydrofoil, as well as various rotating or rotary devices, including propellers, impellers, turbines, rotors, fans, and other similar devic... | 05/23/2006 |
| 7043921 | Tube cooled combustor An innovative cooling tube assembly is disclosed for use in cooling the liner of a combustor in a gas turbine engine. Each cooling tube has a serpentine shape that conforms to the contour of the liner as the tube extends from one end of the combustor to the other to... | 05/16/2006 |
| 7032386 | Gas turbine combustor A combustor for a gas turbine has an arrangement to form a layer of cooling-air on an inner surface of a liner of a combustion chamber. This layer of the cooling air extends from a fuel nozzle block of the combustor toward a downstream side with respect to the liner... | 04/25/2006 |
| 7022940 | Combustor linear and method for making thereof A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such... | 04/04/2006 |
| 7010921 | Method and apparatus for cooling combustor liner and transition piece of a gas turbine A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an... | 03/14/2006 |
| 7007481 | Thick coated combustor liner A combustor liner includes panels joined together at a cooling nugget including a bridge and a lip extending therefrom. The lip defines a slot terminating in an outlet. Thermal barrier coating covers inboard surfaces of the panels and lip with a nominal thickness. T... | 03/07/2006 |
| 7000396 | Concentric fixed dilution and variable bypass air injection for a combustor A combustor for a gas turbine includes a combustor body having an aperture and a casing enclosing the combustor body and defining a passageway therebetween for carrying compressor discharge air. There is at least one injection tube for supplying an amount of the com... | 02/21/2006 |
| 6973419 | Method and system for designing an impingement film floatwall panel system A method and system for designing an impingement film floatwall panel system for a combustion chamber for a gas turbine engine comprising the steps of creating an impingement film floatwall panel knowledge base of information. The knowledge base has a plurality of d... | 12/06/2005 |
| 6931855 | Attachment system for coupling combustor liners to a carrier of a turbine combustor A system for attaching liners to a carrier for forming inner surfaces of turbine combustor. The system may include one or more liners attached to a carrier using connectors engaged to the carrier on a cold side of the liner and may include one or more liners attache... | 08/23/2005 |
| 6925810 | Gas turbine engine transition liner assembly and repair A method of repairing a damaged combustion gas transition liner for a gas turbine engine and an improved damage-resistant transition liner that mounts adjacent to the edge of one of the engine's combustion chambers. In a particular embodiment, the gas turbine engine... | 08/09/2005 |
| 6912782 | Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and r... | 07/05/2005 |
| 6910853 | Structures for attaching or sealing a space between components having different coefficients or rates of thermal expansion A structure for attaching together or sealing a space between a first component and a second component that have different rates or amounts of dimensional change upon being exposed to temperatures other than ambient temperature. The structure comprises a first attac... | 06/28/2005 |
| 6907736 | Gas turbine combustor having an acoustic energy absorbing wall A gas turbine combustor in which a part or all of the wall of the combustor disposed within an intake chamber is formed as an acoustic energy absorbing member that can absorb the acoustic energy of a combustion variation generated within the combustor. The acoustic ... | 06/21/2005 |
