Bizarre Patents
Crispy Chip Sandwich and Process of Producing a Sandwich Product
A food product comprising a multilayer cookie or snack having outer layers formed from a crispy type edible food product such as a potato chip or corn chip, etc. with an intermediate marshmallow layer being in contact with the inner surface of each crispy chip and one or more filler substances.
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.
| Number | Title | Issue Date |
| 8109724 | 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 in... | 02/07/2012 |
| 7988417 | Air cooled turbine blade A turbine blade with a 5-pass serpentine flow cooling circuit for mid-blade cooling that is formed from a 3-pass forward flowing serpentine circuit followed by a 2-pass aft flowing serpentine circuit with the first leg or supply channel for the circuit located betwe... | 08/02/2011 |
| 7819627 | Aerofoil An aerofoil made from a sheet metal blank which is bent in the shape of an aerofoil such that it has a leading edge, a trailing edge, a pressure side and a suction side, and the blank is joined at the trailing edge. The regions of the sheet metal blank that form the... | 10/26/2010 |
| 7438527 | Airfoil trailing edge cooling A turbine airfoil includes a span wise extending cavity formed from a ceramic mold and a slot extending from the cooling air cavity to a trailing edge being formed by a refractory metal core. The refractory metal core facilitates the reduction in the size of the slo... | 10/21/2008 |
| 7357351 | Linear shock wave absorber A linear cavity is provided on the leading edge of an object that is subject to the flow of liquids or gasses, where said cavity preferably has a wall that follows the curvature of a diminishing sine wave, although other configurations are possible that do not follo... | 04/15/2008 |
| 7354247 | Blade for a rotor of a wind energy turbine A blade for a rotor of a wind energy turbine includes opposite upper and lower faces, opposite leading and trailing edges connecting the upper and lower and at least one air outlet opening arranged on at least one of the upper face, the lower face and the trailing e... | 04/08/2008 |
| 7341429 | Methods and apparatuses for cooling gas turbine engine rotor assemblies A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the... | 03/11/2008 |
| 7329102 | Blade With regard to hollow blades for turbine engines, it will be understood there is a problem with respect to percussive impact resulting in excessive distortion of the blade as well as potential failure as a result of blade tip bulging. By provision of ridges 107, ... | 02/12/2008 |
| 7320575 | Methods and apparatus for aerodynamically self-enhancing rotor blades An airfoil having a root, a tip, and an outer surface for pressuring air flowable thereover. The outer surface includes one or more slots elongate in a direction selected to preclude or reduce circulation within the slots, and the one or more slots are configured to... | 01/22/2008 |
| 7303375 | Refractory metal core cooling technologies for curved leading edge slots A turbine engine component has an airfoil portion with a leading edge portion. The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the airfoil portion. A method for forming the leading edge portion using refra... | 12/04/2007 |
| 7293962 | Cooled turbine blade or vane A turbine blade or vane (1) has a shell (2), including a first side wall (8) and a second side wall (9), which are connected together at a leading edge (10) and at a trailing edge (11), which extend longitudinally from a roo... | 11/13/2007 |
| 7275720 | Actively cooled ceramic thermal protection system An apparatus and method for thermal protection is provided. A thermal protection apparatus includes a porous layer attached to an inner structural member requiring thermal protection. The porous layer serves as both a cooling air plenum and a transpiring medium. The... | 10/02/2007 |
| 7244101 | Dust resistant platform blade A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation. ... | 07/17/2007 |
| 7241113 | Vorticity control in a gas turbine engine An arrangement for reducing vorticity downstream of a turbine nozzle guide vane 34 in a gas turbine engine. The arrangement including directing cooling air through the guide vane 34 and out through outlets 40 in directions to counteract the wave... | 07/10/2007 |
| 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 |
| 7210906 | Internally cooled gas turbine airfoil and method An internally cooled airfoil for a gas turbine engine and a method of cooling in which at least two substantially parallel passages are in fluid communication with an exit plenum and adapted to reduce stagnation and improve strength, particularly in wide chord blade... | 05/01/2007 |
| 7207775 | Turbine bucket with optimized cooling circuit A turbine bucket includes a cooling circuit through a dovetail section, a shank section and an airfoil section. The cooling circuit is configured to maximize cooling ability and maximize a useful life at base load operation at firing temperatures of up to 2084° F. ... | 04/24/2007 |
| 7195460 | Francis turbine A Francis runner and a hydraulic turbine equipped with such a runner, wherein the runner includes a ceiling, a belt, and blades which extend between the ceiling and the belt and which define liquid flow channels therebetween. A ratio (e/L) of a maximum thickness Ce)... | 03/27/2007 |
| 7186082 | Cooled rotor blade and method for cooling a rotor blade A rotor blade and a method for cooling a rotor blade are provided. The rotor blade includes a root and a hollow airfoil having a cavity defined by suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage config... | 03/06/2007 |
| 7156622 | Compressor blade for an aircraft engine A compressor blade for an aircraft engine includes a blade core made of a fiber compound material and a metallic enclosing structure. The enclosing structure is of a multi-part design and includes blanks (4, 5) attached to the blade core by a metallic weave (... | 01/02/2007 |
| 7150601 | Turbine airfoil cooling passageway An internally cooled gas turbine engine turbine vane has an outboard shroud and an airfoil extending from an outboard end at the shroud to an inboard end. A cooling passageway has an inlet in the shroud, a first turn at least partially within the airfoil, a first le... | 12/19/2006 |
| 7137780 | Internal cooling system for a turbine blade A turbine blade for a turbine engine having a cooling system with at least one serpentine cooling channel in internal aspects of the turbine blade. The serpentine cooling channel includes at least one root turn proximate to a root of the turbine blade. The root turn... | 11/21/2006 |
| 7086829 | Film cooling for the trailing edge of a steam cooled nozzle A nozzle assembly (10) for a turbine engine includes an inner band (16) and an outer band (14) spaced apart from each other. An airfoil (12) installed between the bands has a leading edge (18) and a trailing edge (20). The a... | 08/08/2006 |
| 7070391 | Hollow fan blade for gas turbine engine Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming o... | 07/04/2006 |
| 7056095 | Impeller and method using solid free form fabrication The present invention relates to the use of solid freeform fabrication (SFF) technology in the manufacture of impeller blades. The impeller blades may be metal plated and further incorporated onto a rigid skeletal frame to allow for more desirable wear resistance an... | 06/06/2006 |
| 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 |
| 7021896 | Turbine blade A turbine blade (20) has cooling air passageways (30) and (30a, 30b, 30c.) through the leading edge wall portion (24) which are positionally arranged so as to intersect each other within the wall thickne... | 04/04/2006 |
| 6997676 | Bifurcated outlet guide vanes A turbine rear frame includes a row of outlet guide vanes extending between outer and inner bands. Each of the vanes is bifurcated into a forward prow integrally joined to an aft stern by a septum therebetween. The prow and stern collectively define the aerodynamic ... | 02/14/2006 |
| 6948906 | Rotor blade system with reduced blade-vortex interaction noise A rotor blade system with reduced blade-vortex interaction noise includes a plurality of tube members embedded in proximity to a tip of each rotor blade. The inlets of the tube members are arrayed at the leading edge of the blade slightly above the chord plane, whil... | 09/27/2005 |
| 6929451 | 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 includes a base, a tip, a pressure side wall, a suction side wall, and a cavity disposed therebetween. The cavity extends substantially between the base and th... | 08/16/2005 |
| 6926499 | Thin-walled, lightweight cooled turbine blade A blade 10 is composed of a front blade portion 10a, a rear blade portion 10b and a middle blade portion 10c. The belly side of the middle blade portion 10c forms a recess towards the back side. High-tem... | 08/09/2005 |
| 6921014 | Method for forming a channel on the surface of a metal substrate A method for forming a channel within a coated, metal-based substrate is described. In one technique, a channel-forming material is first deposited on the substrate, followed by the deposition of a bonding agent, such as a braze. One or more coatings can then be app... | 07/26/2005 |
| 6910864 | Turbine bucket airfoil cooling hole location, style and configuration First, second and third sets of cooling holes are provided in a turbine airfoil. The first set of holes adjacent a leading edge have turbulators commencing at a predetermined distance from the root of the airfoil and terminating short of the airfoil tip. A second se... | 06/28/2005 |
| 6905301 | Turbine blade/vane A turbine blade/vane, having a blade/vane aerofoil which extends along a blade/vane axis and through which cooling medium flows, mainly in the longitudinal direction of the turbine blade/vane, is configured comparatively simply for reliable and effective closed cool... | 06/14/2005 |
| 6761534 | Cooling circuit for a gas turbine bucket and tip shroud An open cooling circuit for a gas turbine airfoil and associated tip shroud includes a first group of cooling holes internal to the airfoil and extending in a radially outward direction generally along a leading edge of the airfoil; a second group of cooling holes i... | 07/13/2004 |
| 6499950 | Cooling circuit for a gas turbine bucket and tip shroud An open cooling circuit for a gas turbine bucket wherein the bucket has an airfoil portion, and a tip shroud, the cooling circuit including a plurality of radial cooling holes extending through the airfoil portion and communicating with an enlarged intern... | 12/31/2002 |
| 6454533 | Hollow blade for hydraulic turbine or pump A runner for a hydraulic turbine or pump includes a hub and a plurality of blades extending from the hub at spaced intervals therearound. Each blade includes an inner edge secured to the hub and a distal outer edge, a leading edge and an opposed trailing ... | 09/24/2002 |
| 6439756 | Agitator An agitator for agitating liquids in an agitator vessel for suspending solids and dispersing gas in a liquid, in particular in an absorber of a flue gas desulfurizing plant, includes an agitator vessel, an agitator shaft extending into the agitator vessel... | 08/27/2002 |
| 6193468 | Hollow-cast component In a hollow-cast component, a core opening (13) created during manufacturing is closed with a closure piece (14). This closure piece is located inside a recess (15) in the component, whereby the recess is arranged so that it is imbedded completely in the ... | 02/27/2001 |
| 6155783 | Hollow blade for hydraulic turbine or pump A runner for a hydraulic turbine or pump includes a hub and a plurality of blades extending from the hub at spaced intervals therearound. Each blade includes an inner edge secured to the hub and a distal outer edge, a leading edge and an opposed trailing ... | 12/05/2000 |
