Patent application number | Description | Published |
20090208397 | DRY SULFUR DIOXIDE (SO2) SCRUBBING - A system for removing sulfur dioxide (SO | 08-20-2009 |
20090320725 | FURNACE SYSTEM WITH INTERNAL FLUE GAS RECIRCULATION - A furnace system | 12-31-2009 |
20120145052 | APPARATUS AND METHOD OF CONTROLLING THE THERMAL PERFORMANCE OF AN OXYGEN-FIRED BOILER - Disclosed herein is a method of controlling the operation of an oxy-fired boiler; the method comprising combusting a fuel in a boiler; producing a heat absorption pattern in the boiler; discharging flue gases from the boiler; recycling a portion of the flue gases to the boiler; combining a first oxidant stream with the recycled flue gases to form a combined stream; splitting the combined stream into several fractions; and introducing each fraction of the combined stream to the boiler at different points of entry to the boiler. | 06-14-2012 |
20120178030 | SYSTEM AND METHOD FOR REDUCING EMISSIONS FROM A BOILER - A system and method for reducing emissions from a boiler. A boiler generally has a combustion area. The system further includes a fuel pipe for delivering fuel. The system further includes a conduit. A bore extends through the conduit. The bore of the conduit is in fluid communication with the fuel pipe and the combustion area of the boiler. A pre-ignition source is positioned in the conduit. The pre-ignition source operates to pre-ignite at least a portion of the fuel flowing through the conduit. | 07-12-2012 |
20130160857 | METHOD AND SYSTEM FOR TREATING AN EFFLUENT STREAM GENERATED BY A CARBON CAPTURE SYSTEM - A system for treating an effluent stream including a carbon capture system utilizing an amine-containing solution to remove carbon dioxide from a flue gas stream, the carbon capture system generating an effluent stream comprising degradation products generated by the amine-containing solution; storage means for storing at least a portion of the effluent stream, the storage means being fluidly coupled to the carbon capture system. The system also including at least one nozzle connected to a combustion zone of a boiler, the at least one nozzle being fluidly coupled to the storage means for providing at least a portion of the effluent stream present in the storage means to the combustion zone of the boiler through the at least one nozzle, wherein the effluent stream provided to the combustion zone is co-incinerated with a fuel in the combustion zone. | 06-27-2013 |
20140208994 | FLUID DISTRIBUTION AND MIXING GRID FOR MIXING GASES - A grid for distributing and mixing fluids in a duct includes a plurality of lances arranged in a first plane and configured to be positioned transverse to a direction of a first fluid flowing outside of the lances and within a predetermined flow area. Each of the plurality of lances has at least one first inlet and a plurality of outlet nozzles. One or more of the outlet nozzles is directed generally in the flow direction of the first fluid outside of the lances, and is configured to discharge a second fluid therefrom. | 07-31-2014 |
20140212825 | OXY-COMBUSTION COUPLED FIRING AND RECIRCULATION SYSTEM - A combustion system is provided for an oxy-combustion furnace. The combustion system includes at least one windbox mountable on the oxy-combustion furnace and having at least one main firing location. At least one primary inlet is positioned in the at least one main firing location for conveying fuel and the first oxidant into the oxy-combustion furnace. At least one secondary inlet is positioned in the at least one main firing location for conveying the second oxidant into the oxy-combustion furnace. The at least one secondary inlet is angularly offset from the at least one primary inlet. | 07-31-2014 |
Patent application number | Description | Published |
20090245997 | METHOD AND DEVICE TO AVOID TURBO INSTABILITY IN A GAS TURBINE ENGINE | 10-01-2009 |
20090272122 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. | 11-05-2009 |
20100115914 | TRANSLATING CORE COWL HAVING AERODYNAMIC FLAP SECTIONS - An example core nacelle for a gas turbine engine includes a core cowl positioned adjacent an inner duct boundary of a fan bypass passage having an associated discharge airflow cross-sectional area. The core cowl includes at least one translating section and at least one flap section. The translating section of the core cowl is selectively moveable to vary the discharge airflow cross-sectional area. | 05-13-2010 |
20100139240 | BLADDER TYPE VARIABLE AREA FAN NOZZLE - A variable fan nozzle for use in a gas turbine engine includes a nozzle section, such as an inflatable bladder, associated with a fan bypass passage for conveying a bypass airflow. The nozzle section has an internal fluid pressure that is selectively variable to influence the bypass airflow. | 06-10-2010 |
20120301306 | HYBRID ROTOR DISK ASSEMBLY FOR A GAS TURBINE ENGINE - A rotor disk assembly for a gas turbine engine includes a rotor hub defined about an axis of rotation, the rotor hub includes a blade mount section with a first radial flange having a multiple of first apertures and a second radial flange with a multiple of second apertures. | 11-29-2012 |
20120301314 | HYBRID ROTOR DISK ASSEMBLY WITH A CERAMIC MATRIX COMPOSITE AIRFOIL FOR A GAS TURBINE ENGINE - A Ceramic Matrix Composite (CMC) airfoil for a gas turbine engine includes a CMC root section which extends to form a CMC airfoil section, the CMC root section defines a bore along a non-linear axis. | 11-29-2012 |
20120301317 | HYBRID ROTOR DISK ASSEMBLY WITH CERAMIC MATRIX COMPOSITES PLATFORM FOR A GAS TURBINE ENGINE - A Ceramic Matrix Composite (CMC) platform for an airfoil of a gas turbine engine includes a CMC platform segment which at least partially defines an airfoil profile. | 11-29-2012 |
20130205802 | COOLING HOLE WITH CRENELLATION FEATURES - A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section in communication with the inlet and extending to the outlet. The diffusing section includes a plurality of crenellation features that encourage lateral spreading of cooling air flowing through the cooling hole. | 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 |
20130209229 | GAS TURBINE ENGINE COMPONENT WITH CONVERGING/DIVERGING COOLING PASSAGE - A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet. The inlet portion converges in a first direction from the inlet to the transition and diverges in a second direction from the inlet to the transition. The outlet portion diverges at least in one of the first and second directions from the transition to the outlet. | 08-15-2013 |
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 |
20130209233 | COOLING HOLE WITH ENHANCED FLOW ATTACHMENT - A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet. | 08-15-2013 |
20140119944 | Film Cooling Channel Array with Multiple Metering Portions - A cooling channel array for a gas turbine engine is provided. The cooling channel array is carried by a component wall having an inner surface and an outer surface and comprises at least two metering portions that communicate with a diffusion cavity. | 05-01-2014 |
20140193246 | COOLING HOLE WITH CRENELLATION FEATURES - A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region. | 07-10-2014 |
20150107223 | HIGH DURABILITY TURBINE EXHAUST CASE - A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material. | 04-23-2015 |
20150132110 | HIGH DURABILITY TURBINE EXHAUST CASE - A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material. | 05-14-2015 |
20150204212 | HIGH DURABILITY TURBINE EXHAUST CASE - A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material. | 07-23-2015 |
20150233302 | OPERABILITY GEARED TURBOFAN ENGINE INCLUDING COMPRESSOR SECTION VARIABLE GUIDE VANES - A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compressor. At least one first variable guide vane controls operation of the first compressor and at least one second variable guide vane controls operation of the second compressor. A combustor is in fluid communication with the compressor section and a turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. | 08-20-2015 |
20150267618 | GEARED TURBOFAN HIGH GEARBOX POWER DENSITY - A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency. | 09-24-2015 |
20160047251 | COOLING HOLE HAVING UNIQUE METER PORTION - A gas turbine engine component has a cooling hole with a metering section. The metering section includes a convex surface and a concave surface, with a first arcuate channel connecting an end of the convex surface and an end of the concave surface. The end of the convex surface and the end of the concave surface define a dimension that is smaller than a diameter of the arcuate channel. | 02-18-2016 |
Patent application number | Description | Published |
20100170264 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. | 07-08-2010 |
20110206522 | ROTATING AIRFOIL FABRICATION UTILIZING CMC - Disclosed is an airfoil comprising a plurality of ceramic matrix composite (CMC) fabric sheets which are layered to form a single, layered fabric sheet. The layered fabric sheet is formed so as to define a pressure and suction side of the airfoil. The airfoil includes primary fibers which extend radially outwardly from a rotor disk, for example. In this way, the airfoil is suitable for use in a gas turbine engine due to the temperature resistance of CMC and the strength provided by the primary fibers. | 08-25-2011 |
20120070276 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained. | 03-22-2012 |
20130094946 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud for a gas turbine engine includes a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots, and a trailing portion adjacent to the leading portion. The trailing portion has a trailing edge. | 04-18-2013 |