Did You Know...
...that the inventor of the electric motor was a blacksmith named Thomas Davenport? Described as "a brilliantly unsuccessful inventor", Davenport invented the first rotary electric motor. In 1836 he headed out -- on foot -- from his Vermont home to file a patent application at the Patent Office in Washington, D.C. By the time he got there, he had squandered away his money and couldn't afford the $30 filing fee so he turned around and went home. When he later mailed in his application with money he'd raised, the Patent office was destroyed in a fire. He did finally get credit for his invention on Feb. 5, 1837.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Application No. | Application Title | Issue Date |
| 20120128504 | Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine A rotor section for a rotor of a gas turbine is provided. The rotor section includes a rotor disk with rotor blades inserted in retaining grooves thereupon, the rotor blades being secured against displacement along the retaining grooves by means of a sealing element whi... | 05/24/2012 |
| 20120107135 | APPARATUS, SYSTEMS AND METHODS FOR COOLING THE PLATFORM REGION OF TURBINE ROTOR BLADES A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends to the approximate radial height of the platform, and wherein, a pressure s... | 05/03/2012 |
| 20120107134 | APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends from a connection at the root to the approximate radial height of the platf... | 05/03/2012 |
| 20120107136 | SEALING PLATE AND ROTOR BLADE SYSTEM A rotor blade system, for example, of a gas turbine is provided. The rotor blade system includes a plurality of rotor blades which are arranged annularly on a rotor disk. A plurality of sealing plates are arranged on a side surface of the rotor disk. An individual seali... | 05/03/2012 |
| 20120082565 | APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES In a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the airfoil and the root include an interior cooling passage formed therein, wherein, in operation, the interior cooling passage comprises at least a high-pressure coolant ... | 04/05/2012 |
| 20120082566 | APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES A platform cooling arrangement for a turbine rotor blade having a platform and an interior cooling passage and, in operation, a high-pressure coolant region and a low-pressure coolant region, wherein the platform includes a topside, which extends from the airfoil to a p... | 04/05/2012 |
| 20120082568 | TURBINE DISC COOLING ARRANGEMENT A cooling arrangement is provided for a turbine disc of a gas turbine engine. The turbine disc has a plurality of circumferentially spaced disc posts forming fixtures therebetween for a row of turbine blades. Each turbine blade has an attachment formation which engages ... | 04/05/2012 |
| 20120082564 | APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES A platform cooling arrangement in a turbine rotor blade having a platform that includes an interior cooling passage formed therein. The platform cooling arrangement may include: a main plenum residing just inboard of the planar topside and extending from an aft position... | 04/05/2012 |
| 20120082567 | COOLED ROTOR BLADE A cooled turbine rotor blade for a gas turbine engine is provided. The engine has an annular flow path for conducting working fluid though the engine. The blade has an aerofoil section for extending across the annular flow path. The blade further has a root portion radi... | 04/05/2012 |
| 20120082563 | Cooed IBR for a micro-turbine A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied ... | 04/05/2012 |
| 20120070309 | BLADE FOR A GAS TURBINE A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said... | 03/22/2012 |
| 20120070310 | AXIAL TURBOMACHINE ROTOR HAVING BLADE COOLING An axial turbomachine rotor is provided. The rotor includes a rotor disk and a rotor blade ring, which includes a plurality of rotor blades, each of which include a blade root, with which the rotor blade is fixed radially outward on the rotor disk, wherein the blade roo... | 03/22/2012 |
| 20120070308 | COOLED BLADE FOR A GAS TURBINE A cooled blade for a gas turbine includes an airfoil section which extends in the radial direction of the turbine or in the longitudinal direction of the blade between a platform and a blade tip which is provided with a cap. The airfoil section is bounded transversely w... | 03/22/2012 |
| 20120070307 | TURBINE BLADES, TURBINE ASSEMBLIES, AND METHODS OF MANUFACTURING TURBINE BLADES A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side walls, the tip wall recessed from the first tip edge of the first side wa... | 03/22/2012 |
| 20120070305 | SHANK CAVITY AND COOLING HOLE A turbine bucket is provided and includes a shank defining a cavity therein, which is connectible with a rotor such that wheelspace air having an initial pressure is permitted to flow into the cavity and a platform coupled to the shank and defining a cooling hole therei... | 03/22/2012 |
| 20120070306 | TURBINE COMPONENT COOLING CHANNEL MESH WITH INTERSECTION CHAMBERS A mesh (35) of cooling channels (35A, 35B) with an array of cooling channel intersections (42) in a wall (21, 22) of a turbine component. A mixing chamber (42A-C) at each intersection is wider (W1, W2)) than a widt... | 03/22/2012 |
| 20120051941 | COMPONENTS WITH CONFORMAL CURVED FILM HOLES AND METHODS OF MANUFACTURE A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an exit region at the second surface. The second surface has a non-plan... | 03/01/2012 |
| 20120034102 | BUCKET ASSEMBLY COOLING APPARATUS AND METHOD FOR FORMING THE BUCKET ASSEMBLY A bucket assembly and a method for forming the bucket assembly are disclosed. The bucket assembly includes a platform, an airfoil, and a lower body portion. The platform defines a platform cooling circuit configured to flow cooling medium therethrough. The airfoil exten... | 02/09/2012 |
| 20120034100 | RECESSED METERING STANDOFFS FOR AIRFOIL BAFFLE An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides surrounding an internal cooling channel. The baffle is disposed within the intern... | 02/09/2012 |
| 20120020787 | COOLED BLADE FOR A GAS TURBINE A cooled blade for a gas turbine includes a blade airfoil extending between leading and trailing edges in a flow direction and on suction and pressure sides is delimited by a wall, which include an interior space in which cooling air flows towards the trailing edge in t... | 01/26/2012 |
| 20120014809 | HIGH PRESSURE TURBINE VANE COOLING HOLE DISTRUBUTION A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, third and fourth sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respe... | 01/19/2012 |
| 20120014810 | TURBINE VANE WITH DUSTING HOLE AT THE BASE OF THE BLADE A cooled turbine vane for a turbine engine, that includes a blade mounted on a platform carried by a base, the blade including one or more cavities formed therein for cooling air circulation, the cavity extending along the trailing edge and being supplied with cooling a... | 01/19/2012 |
| 20120014808 | NEAR-WALL SERPENTINE COOLED TURBINE AIRFOIL A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the ai... | 01/19/2012 |
| 20110318191 | THERMALLY LOADED, COOLED COMPONENT A thermally loaded, cooled component thermally coupled to a cooling system configured to receive a gaseous cooling introduced in a forced manner from outside that flows through the cooling system so as to absorb and transport heat away from the component as a result of ... | 12/29/2011 |
| 20110311369 | GAS TURBINE ENGINE COMPONENTS WITH COOLING HOLE TRENCHES An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface to the exterior surface; and a concave trench extending from the cooling hole at the exterior surface of the... | 12/22/2011 |
| 20110305582 | Film Cooled Component Wall in a Turbine Engine A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is define... | 12/15/2011 |
| 20110305583 | COMPONENT WALL HAVING DIFFUSION SECTIONS FOR COOLING IN A TURBINE ENGINE A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single coo... | 12/15/2011 |
| 20110299999 | MULTI-COMPONENT ASSEMBLY CASTING Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component (12) and a preformed shroud heat resistant material (18) in a mold, wherein the airfoil component (12) and the shroud heat re... | 12/08/2011 |
| 20110300000 | Component Having a Film Cooling Hole Conventionally coated components with film cooling holes are known, comprising a diffuser, extending through the layers into the substrate. According to the invention, the component is embodied such that the whole diffuser is largely arranged in the layer.... | 12/08/2011 |
| 20110286857 | CERAMIC CORE TAPERED TRIP STRIPS A core for creating an airfoil has a ceramic material that forms a body. The body has an outer dimension, a slot extending through the outer dimension and into the body for receiving an insert, the slot disposed at an angle to the outer dimension, and a trip strip havin... | 11/24/2011 |
| 20110280735 | VENTILATION OF A HIGH-PRESSURE TURBINE IN A TURBOMACHINE A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc ... | 11/17/2011 |
| 20110274559 | Turbine Airfoil with Body Microcircuits Terminating in Platform A turbine engine component includes a platform and one or more microcircuit cooling passages embedded within one or more walls of an airfoil portion of the component. Each microcircuit cooling passage terminates within the thickness of the platform so as to provide cool... | 11/10/2011 |
| 20110268583 | AIRFOIL TRAILING EDGE AND METHOD OF MANUFACTURING THE SAME A method for machining an airfoil including a plurality of internal cooling channels is provided. The method includes selectively removing a pressure side section proximate to a trailing edge of the airfoil to expose a portion of the plurality of internal cooling channe... | 11/03/2011 |
| 20110268584 | BLADES, TURBINE BLADE ASSEMBLIES, AND METHODS OF FORMING BLADES Blades, turbine blade assemblies, and methods of forming blades are provided. The blade includes an airfoil including a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root, and a tip, the convex suction side wall, the concave ... | 11/03/2011 |
| 20110255990 | BLADES A rotor blade for a gas turbine engine has an aerofoil portion and a tip region. The tip region is at the radially outermost end of the blade. The radially outermost surface carries abrasive material (not shown) to interact with an abradable surface. The tip has a reces... | 10/20/2011 |
| 20110255991 | INTEGRALLY BLADED ROTOR DISK FOR A TURBINE An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is... | 10/20/2011 |
| 20110255989 | Cooling system of ring segment and gas turbine In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the m... | 10/20/2011 |
| 20110243755 | COOLED BLADE FOR A GAS TURBINE, METHOD FOR PRODUCING SUCH A BLADE, AND GAS TURBINE HAVING SUCH A BLADE A blade for a gas turbine includes an airfoil extending in radial direction of the turbine or longitudinal direction of the blade, respectively, between a platform and a blade tip. The airfoil is bordered across the airfoil by a leading edge and a trailing edge and has ... | 10/06/2011 |
| 20110243756 | METHOD FOR PRODUCING A BLADE BY CASTING AND BLADE FOR A GAS TURBINE A method is provided for producing a blade, by casting, for a gas turbine. The blade includes an elongate airfoil which extends in a blade longitudinal direction, merges into a blade root at the lower end, has a shroud segment at the blade tip and is pervaded by a singl... | 10/06/2011 |
| 20110243711 | INTERIOR COOLING CHANNELS Cooling channels through the interior of a machine component that include: a first set of cooling channels, the first set of cooling channels including a plurality of parallel channels that reside in a first plane; a second set of cooling channels, the second set of coo... | 10/06/2011 |
