Patent application number | Description | Published |
20090297353 | WIND TURBINE BLADES WITH TWISTED TIPS - A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade. | 12-03-2009 |
20090297354 | WIND TURBINE BLADES WITH TWISTED AND TAPERED TIPS - A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade; and a total normalized chord change of between approximately one percent and approximately two percent between the outer approximately 1 percent to approximately 10 percent of the rotor radius of the blade. | 12-03-2009 |
20100135811 | ROOT SLEEVE FOR WIND TURBINE BLADE - A sleeve for a wind turbine blade includes an opening for receiving a root end of the wind turbine blade; and an inboard edge for substantially abutting a hub of a wind turbine. | 06-03-2010 |
20100166556 | PARTIAL ARC SHROUD FOR WIND TURBINE BLADES - A wind turbine blade includes an arcuate partial annulus arc shroud secured to a tip of the blade. | 07-01-2010 |
20110103950 | SYSTEM AND METHOD FOR PROVIDING A CONTROLLED FLOW OF FLUID TO OR FROM A WIND TURBINE BLADE SURFACE - A wind turbine blade system having a blade rotatably attached to a rotor of a wind turbine. The system further includes a controller and one or more openings disposed along at least one surface of the blade and a fluid moving device arranged and disposed to provide a fluid to or from the one or more openings. A controlled amount of the fluid is provided to the one or more openings. The amount of fluid is determined by the controller. A wind turbine and a method for operating a wind turbine are also disclosed. | 05-05-2011 |
20110158798 | SYSTEMS AND APPARATUS RELATING TO COMPRESSOR STATOR BLADES AND DIFFUSERS IN TURBINE ENGINES - A row of stator blades in a compressor of a combustion turbine engine, the combustion turbine engine including a diffuser located downstream of the compressor, and the row of stator blades disposed in close proximity to the diffuser; the row of stator blades comprising: a plurality of stator blades that include at least one of an inboard forward notch and an outboard forward notch. | 06-30-2011 |
20140157792 | SYSTEM AND METHOD FOR REMOVING HEAT FROM A TURBINE - A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum. | 06-12-2014 |
Patent application number | Description | Published |
20090104028 | METHOD AND APPARATUS FOR DISTRIBUTING FLUID INTO A TURBOMACHINE - An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port. | 04-23-2009 |
20100143152 | METHOD AND APPARATUS FOR INCREASING LIFT ON WIND TURBINE BLADE - A lift device for a wind turbine blade. The lift device includes a first sidewall and an opposing second sidewall. The lift device is configured to be coupled to the wind turbine blade along a leading edge of the wind turbine blade, and to generate lift when airflow is directed across a surface of the lift device. | 06-10-2010 |
20110097210 | TURBINE AIRFOIL - An airfoil is provided and includes a pressure surface and a suction surface. Radially corresponding surface characteristics of the pressure and suction surfaces at a spanwise local portion of the airfoil are formed to cooperatively define at least one of a camber line and a thickness distribution plot of the airfoil as having a radius of curvature with at least two sign changes. The number of sign changes decreases along a radial dimension of the airfoil measured from the spanwise local portion. | 04-28-2011 |
20130051976 | FLOW CONTROL MODULE FOR A TURBOMACHINE - A flow control module for a turbomachine includes an inlet extending to an outlet through a flow passage having at least one side wall. A flow control member is arranged within the flow control module. The flow control member is secured to the at least one side wall between the inlet and the outlet. The flow control member is selectively passively activated to extend into the flow passage to block cooling fluid passing through the flow control module. | 02-28-2013 |
20130170982 | TURBINE AND METHOD FOR SEPARATING PARTICULATES FROM A FLUID - According to one aspect of the invention, a turbine airfoil includes a first cavity inside the turbine airfoil configured to receive a fluid and a second cavity inside the turbine airfoil. The turbine airfoil also includes a passage inside the turbine airfoil that provides fluid communication between the first and second cavities, wherein the passage includes a curved portion configured to separate particulates from the fluid as the fluid flows through the passage. | 07-04-2013 |
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 |
20140064325 | WHEELSPACE FLOW VISUALIZATION USING PRESSURE-SENSITIVE PAINT - A method of measuring local temperature variations at an interface between hot combustion gases in a turbine hot gas path and cooler purge air in a turbine rotor wheelspace includes applying a pressure- or temperature-sensitive paint to a rotatable turbine component where the hot combustion gas interacts with the purge air; locating at least one illumination device and at least one image-detecting device on a stationary component located proximate to the pressure sensitive paint; and, during operation of the turbine, imaging color changes in the pressure sensitive paint caused by local variations in partial pressure of oxygen which changes with temperature. | 03-06-2014 |
20140116660 | COMPONENTS WITH ASYMMETRIC COOLING CHANNELS AND METHODS OF MANUFACTURE - A method of fabricating a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. The fabrication method includes forming at least one groove in the outer substrate surface. Each groove extends at least partially along the outer substrate surface and has an asymmetric cross-section. The method further includes forming at least one access hole in the substrate. Each access hole connects the respective groove in fluid communication with the respective interior space. A coating is disposed over at least a portion of the substrate surface, such that the groove(s) and the coating together define one or more channels for cooling the component. A component is also disclose and has at least one groove with an asymmetric cross-section. | 05-01-2014 |
20140154062 | SYSTEM AND METHOD FOR SEALING A GAS PATH IN A TURBINE - A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed. | 06-05-2014 |
20150041590 | AIRFOIL WITH A TRAILING EDGE SUPPLEMENT STRUCTURE - An airfoil includes a main portion formed of a base material and having an inner core comprising a hollow region. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising a low-melt superalloy operatively coupled to the base material proximate the trailing edge region. Yet further included is at least one cooling passage fluidly coupling the inner core of the main portion to an inner region of the trailing edge region. Also included is a trailing edge region exhaust path disposed in the inner region and configured to route a cooling airflow in a span-wise direction of the airfoil. | 02-12-2015 |
20150052897 | METHOD OF RECOVERING ENERGY IN A STEAM-COOLED GAS TURBINE - A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor. | 02-26-2015 |