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Pizza Pie With Concentric Rings of Crust
A pizza mold for forming a plurality of concentric raised ridges of dough (i.e., crust) on the surface of a pizza pie.
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| Number | Title | Issue Date |
| 8177496 | Tone noise reduction in turbomachines A blade for a turbomachine extends in use, in a radial direction relative to the axis of the turbomachine. The turbomachine has at least one operating condition which generates supersonic fluid flow at the blade. The blade is adapted to provide, at the supersonic op... | 05/15/2012 |
| 8152459 | Airfoil for axial-flow compressor capable of lowering loss in low Reynolds number region In a transonic region with a Reynolds number not more than a critical Reynolds number, a flow velocity distribution on an extrados of an airfoil has a single supersonic maximum value within a range of up to 6% from a leading edge on a chord, or a shape factor has a ... | 04/10/2012 |
| RE42370 | Reduced shock transonic airfoil A transonic turbine blade. Expansion waves are generated by a lifting surface on the blade. The expansion waves extend downstream, through a shock generated at the trailing edge of an adjacent blade. The invention increases the strength of the shock, thereby attenua... | 05/17/2011 |
| 7845902 | Jet engine inlet-fan system and design method A supersonic aircraft engine axial fan that includes a rotating blade row having blades that receive a supersonic entry flow in the absolute frame and decelerate the flow to a lower supersonic or subsonic velocity exit flow while adding work to the flow to increase ... | 12/07/2010 |
| 7334998 | Low-noise fan exit guide vanes Low-noise fan exit guide vanes are disclosed. According to the present invention a fan exit guide vane has an outer shell substantially shaped as an airfoil and defining an interior cavity. A porous portion of the outer shell allows communication between the fluctua... | 02/26/2008 |
| 7334987 | Fan assembly for vacuum cleaner A fan assembly for a vacuum cleaner, comprising a motor, an impeller rotatably coupled to the motor, and having a plurality of impeller wings, and a diffuser having a plurality of diffuser wings arranged along an outer circumference of the impeller. The plurality of... | 02/26/2008 |
| 7217096 | Fillet energized turbine stage A turbine stage includes a row of airfoils and their platforms spaced laterally apart to define flow passages therebetween. Each airfoil is integrally joined to its platform at a corresponding arcuate fillet which is larger along the pressure side of the airfoil and... | 05/15/2007 |
| 7207772 | Compressor for an aircraft engine On a compressor with compressor blades, a flow transition fixation mechanism (4) is provided on the suction side (2), approximately parallel to the leading edge (3) and upstream of the compression shocks acting upon the blade, which prevents the... | 04/24/2007 |
| 7204676 | Fan blade curvature distribution for high core pressure ratio fan A method for reducing vortex promotion of a rotor blade used in high core PR fans comprises shifting a curvature distribution of a blade section immediately adjacent to the hub such that a major turning of the suction side of the section is located near a trailing e... | 04/17/2007 |
| 7195456 | Turbine engine guide vane and arrays thereof An exit guide vane array for a turbine engine includes a set of guide vanes 28 having a solidity and defining fluid flow passages 74 with a chordwisely converging forward portion 80. The high solidity and convergent passage portion 80 res... | 03/27/2007 |
| 7195454 | Bullnose step turbine nozzle A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and s... | 03/27/2007 |
| 7179053 | Air-blowing apparatus of cleaner Disclosed herein is an air-blowing apparatus of a cleaner. The air-blowing apparatus comprises a fan having a plurality of blades spaced apart from each other in the circumferential direction of the fan for generating a blowing force in the centrifugal direction the... | 02/20/2007 |
| 7153097 | Centrifugal impeller and pump apparatus The centrifugal impeller includes a plurality of blades (3), a plurality of fluid paths (P) for delivering a fluid from an impeller inlet (1) to an impeller outlet (2), and a shroud (4) and a hub (5) for forming the fluid paths (P)... | 12/26/2006 |
| 7147426 | Shockwave-induced boundary layer bleed An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor by bleeding off a shockwave-induced boundary layer from the gas flow passage of the compressor using an array of bleed holes having a downstream edge aligned wi... | 12/12/2006 |
| 7125220 | Axial-flow type fan having an air outlet blade structure An axial-flow type fan includes a fan housing consisting of an air inlet, an air outlet and an air channel, and a fan wheel consisting of a hub and fan blades. The air channel of the fan housing accommodates the fan wheel which has end-cornered cutting blades proxim... | 10/24/2006 |
| 7108486 | Backswept turbojet blade A rotary turbojet blade comprises a plurality of blade sections extending along a line of the centers of gravity of said sections between a base and a tip, said blade presenting along a radial axis a bottom portion, an intermediate portion, and a top portion, said b... | 09/19/2006 |
| 7056089 | High-turning and high-transonic blade A high-turning and high-transonic blade for use in a blade cascade of an axial-flow compressor, wherein a distribution of flow speed on an extrados at a leading edge of the blade has a supersonic region of a substantially constant flow speed in the rear of a first l... | 06/06/2006 |
| 7048509 | Axial flow turbine In the axial turbine according to the present invention, a nozzle blade 1 and/or a movable blade 5 has a profile in which a throat-pitch ratio “s/t” is maximized at a blade-central portion in height, wherein “s” being a shortest distance betwee... | 05/23/2006 |
| 7025557 | Secondary flow control system The present invention is a system (20) for controlling various fluid flows, e.g., secondary fluid flows including cavitating fluid flows, typically developed along the shroud line and usually in or around a leading edge (21) within a flow channel (2... | 04/11/2006 |
| 7007475 | Conical helical of spiral combustor scroll device in gas turbine engine A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift re... | 03/07/2006 |
| 7004722 | Axial flow compressor At least part of the inner circumferential wall of the outer casing is provided with a concave surface opposing the rotor blade tips as seen in a longitudinal section. Typically, each of the rotor blades is provided with aerofoil section, and the compressor is desig... | 02/28/2006 |
| 7001140 | Centrifugal fan diffuser At least one embodiment of the present inventive technology focuses on a vaneless diffuser adapted for establishment extra-radially of a centrifugal fan, wherein the diffuser may effect an optimal transformation of velocity pressure into static pressure of a fluid (... | 02/21/2006 |
| 6969232 | Flow directing device A flow directing device of a gas turbine engine, comprising: an airfoil having a leading edge, trailing edge, suction side and pressure side; a wall abutting the airfoil; and a fillet between the airfoil and wall. The fillet has an enlarged section at the leading ed... | 11/29/2005 |
| 6905309 | Methods and apparatus for reducing vibrations induced to compressor airfoils A method enables a rotor blade for a gas turbine engine to be fabricated. The method comprises forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and... | 06/14/2005 |
| 6837678 | Molten metal pump impeller An impeller for a molten metal pump includes a base and a plurality of vanes having openings for flow of molten metal there through during pumping. Alternatively, or in combination with the vane openings, a single drain opening extending through the base of the impe... | 01/04/2005 |
| 6682301 | Reduced shock transonic airfoil A transonic turbine blade. Expansion waves are generated by a lifting surface on the blade. The expansion waves extend downstream, through a shock generated at the trailing edge of an adjacent blade. The invention increases the strength of the shock, ther... | 01/27/2004 |
| 6527510 | Stator blade and stator blade cascade for axial-flow compressor It is an object of the present invention to provide a stator blade for an axial-flow compressor, in which the wave drag due to the generation of a shock wave in a transonic speed range can be suppressed to the minimum. For this purpose, the stator blade i... | 03/04/2003 |
| 6488469 | Mixed flow and centrifugal compressor for gas turbine engine A two stage compressor for a gas turbine engine with a mixed flow first stage, a centrifugal second stage, and an intermediate duct. The mixed flow stage has a mixed rotor rotatable about the central compressor axis with a circumferential array of mixed f... | 12/03/2002 |
| 6358003 | Rotor blade an axial-flow engine A rotor blade airfoil of an axial-flow turbomachine, for a fan or a compressor high-pressure stage of a gas turbine system, configured in the tip area to improve supersonic performance. The blade afflux edge has a forward-back sweep. The tip region of the... | 03/19/2002 |
| 6099249 | Structure of output section of jet propulsion engine or gas turbine A tandem blade lattice having characteristics enhanced is provided. In a high pressure ratio blade lattice, inevitable generation of an shock wave is shifted, as much as possible, toward a rear portion of an upper surface of a front blade to inhibit separ... | 08/08/2000 |
| 6062819 | Turbomachinery and method of manufacturing the same An impeller in a turbomachinery has blades designed such that reduced static pressure difference ƊCp between the hub and the shroud on the suction surface of the blade shows a remarkably decreasing tendency near the impeller exit as it approaches the imp... | 05/16/2000 |
| 6047540 | Small gas turbine engine having enhanced fuel economy A gas turbine engine ducted to have the air pass sequentially through a single stage axial-flow compressor, a single-stage hybrid axial-radial centrifugal compressor, a burner, an inward flow radial turbine, an axial-flow, high-pressure turbine, and then ... | 04/11/2000 |
| 6022188 | Airfoil An airfoil for a combustion turbine comprising a leading edge, a trailing edge, and an airfoil portion defined therebetween is provided. The airfoil has an axial chord length. The airfoil portion has an accelerating flow section and a decelerating flow se... | 02/08/2000 |
| 6017186 | Rotary turbomachine having a transonic compressor stage A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extendi... | 01/25/2000 |
| 5676522 | Supersonic distributor for the inlet stage of a turbomachine The supersonic distributor for the inlet stage of a turbomachine comprises an outer case, a hub, and a set of peripheral blades disposed in a ring and attached to the hub to provide supersonic speed fluid passages between the blades to transform a flow at... | 10/14/1997 |
| 5642985 | Swept turbomachinery blade A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowi... | 07/01/1997 |
| 5616000 | Stator of torque converter for vehicles improved to suppress separation of working fluid To suppress a separation of working fluid from the vane surface during operation at and around a fluid coupling condition attained after a substantial completion of torque conversion, the aerofoil and the array of stator vanes of a torque converter for ve... | 04/01/1997 |
| 5553995 | Method of driving a turbine in rotation by means of a jet device A turbine device and a method of driving the turbine device are disclosed. The turbine device includes an admission channel, a turbine, and an injection channel. The turbine device may also include a regulator. The turbine is driven by injecting a primary... | 09/10/1996 |
| 5554000 | Blade profile for axial flow compressor An axial flow compressor for use in a gas turbine or other industrial application having an improved efficiency is provided through modification of the blade shape and profile of the blades subject to a subsonic high velocity inlet flow so as to avoid sho... | 09/10/1996 |
| 5486091 | Gas turbine airfoil clocking The first stage of vanes (16) and second stage of vanes (24) each contain the same number of vanes. The second stage vanes are located such that the wake flow (38) from the first stage vanes falls on or near the leading edge, after passing through the sta... | 01/23/1996 |
