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| Number | Title | Issue Date |
| 8182223 | Turbine blade cooling A turbine blade with a generally hollow airfoil having an outer wall that defines at least one radially extending chamber for receiving the flow of a coolant, the airfoil including a leading edge that resides in an upstream or forward direction, a trailing edge that... | 05/22/2012 |
| 8157525 | Methods and apparatus relating to turbine airfoil cooling apertures An airfoil assembly for a turbine engine, that may comprise: an airfoil that includes at least one panel opening formed therein; and an aperture panel that includes at least one cooling aperture; wherein the panel opening and the aperture panel are configured such t... | 04/17/2012 |
| 8152468 | Divoted airfoil baffle having aimed cooling holes A baffle insert for an internally cooled airfoil comprises a liner, a divoted segment and a plurality of cooling holes. The liner has a continuous perimeter formed to shape a hollow body having a first end and a second end. The divoted segment of the hollow body is ... | 04/10/2012 |
| 7967565 | Low cooling flow turbine blade A turbine rotor blade made from a spar and a shell each having an airfoil cross sectional shape and each formed from a high temperature exotic material and formed by a wire EDM process to form a thin wall shell from Molybdenum and the spar from Waspalloy or IN100 in... | 06/28/2011 |
| 7918647 | Turbine airfoil with flow blocking insert An airfoil used in a turbine of a gas turbine engine, the airfoil having a blocker insert formed within the serpentine cooling passage of the airfoil. The blocker insert forms a cooling air passage between the serpentine passage within the blade and the outer surfac... | 04/05/2011 |
| 7857588 | Reinforced airfoils A reinforced airfoil includes an airfoil body including opposed walls that define a hollow interior space and a reinforcement member provided on at least one of the walls within the interior space, the reinforcement member increasing the thickness of the at least on... | 12/28/2010 |
| 7819628 | Assembly comprised of a vane and of a cooling liner, turbomachine nozzle guide vanes assembly comprising this assembly, turbomachine and method of fitting and of repairing this assembly An assembly includes a vane and a cooling liner for cooling the vane, the vane having a central cavity with at least one first opening into which the liner extends, the liner having a flange fixed to the rim of the opening. This assembly includes, near the flange, a... | 10/26/2010 |
| 7563072 | Turbine airfoil with near-wall spiral flow cooling circuit A turbine blade with a plurality of spiral flow cooling channels spaced along the walls of the blade. Each spiral flow cooling circuit includes two adjacent channels that twist about each other in a radial direction of the blade to form a spiral flow path. The two s... | 07/21/2009 |
| 7413405 | Bipedal damper turbine blade A turbine blade includes an airfoil, platform, and dovetail. The airfoil includes a plurality of flow channels being separated by partitions. A primary partition includes an inner saddle. And, a bipedal damper includes a pair of legs extending into the flow channels... | 08/19/2008 |
| 7374400 | Turbine blade arrangement A turbine blade arrangement comprises turbine blades which are secured in adjacent positions to a rotor disc with a cavity defined between root segments and platform segments. A flow deflector within the cavity is provided as an insert such that through a recessed p... | 05/20/2008 |
| 7334992 | Turbine blade cooling system A turbine blade cooling system for a gas turbine engine includes a turbine blade having a trailing edge, a concave side, and a convex side. The trailing edge defines at least one set of impingement holes each having a central longitudinal axis which is closer to a n... | 02/26/2008 |
| 7322795 | Firm cooling method and hole manufacture A cooled cast part has an exterior surface. A cooling passageway system extends from at least one inlet port to a plurality of outlet ports. The passageway system includes a first passageway to at least a first of the outlets and surrounding at least one post. The s... | 01/29/2008 |
| 7316539 | Vane assembly with metal trailing edge segment Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. T... | 01/08/2008 |
| 7300251 | Turbine cooling vane of gas turbine engine A cooled blade of a small gas turbine engine can enhance cooling performance without increasing the amount of cooling air in a simple configuration. A cooled turbine blade is provided with a cooling passageway 12 formed inside thereof, making the cooling air ... | 11/27/2007 |
| 7280950 | Locomotive diesel engine turbocharger and turbine stage constructed with turbine blade vibration suppression methodology A method for fabrication of a locomotive diesel engine turbocharger turbine stage so as to avoid harmonic vibration in the turbine blades when the engine is operated at pre-selected throttle settings. Upon determining throttle settings for the engine and modeling of... | 10/09/2007 |
| 7270517 | Turbine blade with vibration damper A blade assembly (10) for a turbine (16) including a vibration damper (12) having a mounting base (38) sealingly disposed at an inlet end (24) of a cooling fluid passageway (22) within the root section (20) of the bla... | 09/18/2007 |
| 7258528 | Internally cooled airfoil for a gas turbine engine and method An internally-cooled airfoil for a gas turbine engine, wherein the airfoil comprises at least one substantially chordwise-extending and internally-projecting stiffener located on an internal surface of one of the sidewalls and adjacent to the insert. ... | 08/21/2007 |
| 7247002 | Lamellate CMC structure with interlock to metallic support structure A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperat... | 07/24/2007 |
| 7223072 | Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor An airfoil for a gas turbine engine blade includes a plurality of film cooling holes extending through its outer surface. The film cooling holes are formed by defining at least a first datum structure and a second datum structure, and then forming each film cooling ... | 05/29/2007 |
| 7217093 | Rotor blade with a stick damper A rotor blade damper is provided that includes a body having a base, a tip, a first contact surface, a second contact surface, a trailing edge surface, and a leading edge surface. The trailing edge and the leading edge surfaces extend between the contact surfaces. T... | 05/15/2007 |
| 7217091 | Methods and apparatus for deicing airfoils or rotor blades A method for deicing a rotor blade having a blade root, a blade tip, and a leading edge in which the rotor blade is operably coupled to a hub of a turbine includes circulating heated air through an outflow channel from the blade root towards the blade tip, recircula... | 05/15/2007 |
| 7204675 | Cooled gas turbine engine vane A cooled gas turbine vane includes a cast part and a longitudinal sleeve obtained by shaping metal sheet The cast part includes a longitudinal body provided with a longitudinal cavity having a first opening and a second opening at the ends The sleeve is mounted in t... | 04/17/2007 |
| 7201564 | Turbine vane system A turbine vane, especially a turbine vane of the last stages, respectively includes a lower area which is radially and externally arranged, an upper area which is radially and internally arranged, and a radial cooling air channel extending between the upper area and... | 04/10/2007 |
| 7179047 | Vane apparatus for a gas turbine engine A vane assembly for a gas turbine engine, the vane assembly comprising an aerodynamic main body across which gas can flow in streamlines, the main body defining a chamber and a plurality of cooling apertures extending through the main body, the cooling apertures bei... | 02/20/2007 |
| 7175391 | Turbine blade A blade has an airfoil body having an internal cooling passageway network and a body tip pocket. At least one plate is secured within the body tip pocket and has inboard and outboard surfaces. A recess is in the outboard surface and an associated protrusion is on th... | 02/13/2007 |
| 7144220 | Investment casting An article may be manufactured by providing a reticulate core element in a mold shell having a shape at least partially corresponding to a shape of the article. The molten metallic material is introduced to the shell so as to at least partially infiltrate into the r... | 12/05/2006 |
| 7137783 | Cooled gas turbine blades A cooled gas turbine blade includes a foundry part and a longitudinal sleeve obtained by the forming of metal sheet. The foundry part includes a longitudinal body provided with a longitudinal cavity with first and second apertures at its ends. The sleeve is mounted ... | 11/21/2006 |
| 7137781 | Turbine components A turbine component, such as a turbine blade 1, 21, has a coolant supply passage 4, 24 and a cooling chamber 3, 23 connected by an injection passage 5, 25. The cooling chamber 3, 23 includes flow guides in the form of vanes 7, 8... | 11/21/2006 |
| 7137776 | Film cooling for microcircuits An embedded microcircuit for producing an improved cooling film over a surface of a part, comprising an inlet through which a coolant gas may enter, a circuit channel extending from the inlet through which the coolant gas may flow, and a slot film hole formed at a t... | 11/21/2006 |
| 7131816 | Airfoil locator rib and method of positioning an insert in an airfoil An airfoil for a gas turbine engine, the airfoil comprising a locator rib provided at a bottom of a cavity in the airfoil core, the locator rib having an inclined surface to be engaged by a leading end of the insert during installation thereof in the cavity. ... | 11/07/2006 |
| 7125225 | Cooled rotor blade with vibration damping device A rotor blade for a rotor assembly is provided that includes a root, an airfoil, and a damper. The airfoil has a length, a base, a tip, a first side wall, a second side wall, and at least one cavity. The length extends the base and the tip. The at least one cavity i... | 10/24/2006 |
| 7121796 | Nozzle-cooling insert assembly with cast-in rib sections A cooling insert/nozzle assembly for use in gas turbines or similar machinery includes a nozzle having inner and outer ribs with cast-in âTâ sections and âLâ sections, respectively, at the end of the ribs in which air flow enters the nozzle. The assembly fur... | 10/17/2006 |
| 7115158 | Fan having blade members that heat and cool and has an ionizing grid for air purification A ceiling fan that incorporates into its blades both a system for air purification by removing dust and other particulate pollutants from the air in a room through ionization of the air stream passing over an ionizer grid and also a system for heating and cooling th... | 10/03/2006 |
| 7114917 | Vane assembly for a gas turbine engine An exhaust diffuser unit for a gas turbine engine includes an outer ring, a diffuser cone and vanes, all made from a ceramic matrix composite material. Each vane has end components which have apertures through which a metallic support strut extends. The support stru... | 10/03/2006 |
| 7104756 | Temperature tolerant vane assembly A vane assembly 10 suitable for a turbine engine features a refractory vane 12 with an internal cavity 20 and a pair of flexible metallic baffles 26 extending into the cavity from spanwisely opposite ends of the vane. A rigid fastener ... | 09/12/2006 |
| 7080971 | Cooled turbine spar shell blade construction A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a ti... | 07/25/2006 |
| 7070386 | Airfoil insert with castellated end Provided is an airfoil insert for discharging an increased volume of cooling air. The insert comprises a perforated, tubular-shaped body with a first end for introducing the cooling air. A second end located opposite the first end and discharges an increased volume ... | 07/04/2006 |
| 7056083 | Impingement cooling of gas turbine blades or vanes A turbine blade or vane comprises an impingement tube located generally in a radial direction within the blade or vane aerofoil, the impingement tube comprising two parts, extending into the blade or vane from opposite radial ends thereof and locating against a spec... | 06/06/2006 |
| 7029236 | Closed circuit blade-cooled turbine In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades. The holes in the radial direction and the cooling air supply holes... | 04/18/2006 |
| 7025568 | Turbomachine aerofoil A fan blade (26) comprises a leading edge (44), a trailing edge (46), a concave wall portion (50) extending from the leading edge (44) to the trailing edge (46) and a convex wall portion (52) extending from the leadin... | 04/11/2006 |
