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An armor with rollers is provided that enables a user to move in all positions by rolling on a hard and smooth surface while constantly varying his bearing points on the ground.
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| Number | Title | Issue Date |
| 8387245 | Components with re-entrant shaped cooling channels and methods of manufacture A method of fabricating a component is provided. The method includes forming one or more grooves in a surface of a substrate, where the substrate has at least one hollow interior space. Each of the one or more grooves extends at least partially along the substrate s... | 03/05/2013 |
| 8020296 | Method for the production of secondary fluid ducts A method for the production of secondary fluid ducts for a turbomachine, especially for fluid supply or fluid removal to/from a flow-wetted surface of the turbomachine, with the secondary fluid ducts being produced by an electrochemical machining process. ... | 09/20/2011 |
| 8015705 | Spar and shell blade with segmented shell A turbine rotor blade with a spar and shell construction, where the shell has an airfoil shape and is formed of two shell segments with an upper shell half and a lower shell half. The upper shell half is radially supported by a tip of the spar while the lower shell ... | 09/13/2011 |
| 7950147 | Method for producing gas turbine components A method for producing gas turbine components, in particular blades, blade sections or rotors with integral blades for a jet engine is provided. The method comprises at least the following steps: preparation of at least one metallic powder and at least one expanding... | 05/31/2011 |
| 7584538 | Method of forming a turbine blade with cooling channels A method of constructing a turbine blade for a gas turbine engine is provided. The method includes casting the blade, forming a plurality of spaced-apart notches in the airfoil proximate the tip on the pressure sidewall and forming at least one hole in each tip shel... | 09/08/2009 |
| 7441331 | Turbine engine component manufacture methods A cooled turbine engine component is made by providing first and second pieces respectively having first and second surfaces. At least one circuit is formed in at least one of the first and second surfaces. A first plurality of apertures is provided in the first pie... | 10/28/2008 |
| 7438523 | Blade for a turbine engine and method for production of said blade A blade for a turbine engine is described, having a base body, made from a titanium alloy, with a first and a second component piece, which are connected in the connection region by means of a bonding process. A groove with a groove wall runs through the connection ... | 10/21/2008 |
| 7410342 | Airfoil support A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer ... | 08/12/2008 |
| 7371049 | Manufacturable and inspectable microcircuit cooling for blades A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first h... | 05/13/2008 |
| 7364405 | Microcircuit cooling for vanes A turbine engine component has an airfoil portion with a suction side. The component includes a cooling microcircuit embedded within a wall structure forming the suction side. The cooling microcircuit has at least one cooling film hole positioned ahead of a gage poi... | 04/29/2008 |
| 7351036 | Turbine airfoil cooling system with elbowed, diffusion film cooling hole A cooling system for a turbine airfoil of a turbine engine having an elbowed film cooling hole positioned in an outer wall defining the turbine airfoil. The elbowed film cooling hole may include a first section extending from an inner surface of the outer wall into ... | 04/01/2008 |
| 7334333 | Method for making a hollow fan blade with machined internal cavities 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. The floor and opposite interior walls of each cavity are machined simultaneously. The c... | 02/26/2008 |
| 7322796 | Turbine vane construction A method for forming a component for use in a gas turbine engine, such as a turbine vane construction is provided. The method broadly comprises the steps of: forming a first aerodynamic structure having a first platform with a leading edge and a trailing edge, and a... | 01/29/2008 |
| 7311497 | Manufacturable and inspectable microcircuits A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first h... | 12/25/2007 |
| 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 |
| 7284958 | Separable blade platform A gas turbine engine blade platform including a par of platform retention members. The pair of platform retention members are configured to be located on opposite sides of a disk lug. The retention members interact with the disk lug to restrain radial movement of th... | 10/23/2007 |
| 7282681 | Microwave fabrication of airfoil tips A method of producing a metallic component includes: providing a body made of a first alloy; providing a preform comprising a metallic powder made of a second alloy and formed in the shape of an extension of the body; and heating the preform with microwave energy to... | 10/16/2007 |
| 7278826 | Airfoil cooling passage trailing edge flow restriction An internal metering structure permits the exit apertures of a cooled airfoil to be sized to provide for easy manufacturability. ... | 10/09/2007 |
| 7275585 | Process for the manufacture by lost wax moulding of parts that include at least one cavity A process for the manufacture of a part includes the steps of forming a core in a ceramic material, inserting the core into in a wax mold, placing an element on the core thereby forming a spacer between the core and an internal wall of the wax mold, forming a wax mo... | 10/02/2007 |
| 7273351 | Component having a film cooling arrangement A component such as a turbine blade of a gas turbine engine includes a film cooling arrangement which is optimized by a process in which a component is manufactured having a film cooling arrangement of an initial design and evaluation of the performance of the film ... | 09/25/2007 |
| 7255536 | Turbine airfoil platform cooling circuit An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from b... | 08/14/2007 |
| 7241107 | Gas turbine airfoil with adjustable cooling air flow passages An airfoil for a gas turbine engine, the airfoil includes a plurality of cooling air passages to supply cooling air to an external surface of the airfoil, the cooled surface of the airfoil having a critical temperature in which any cooled surface of the airfoil shou... | 07/10/2007 |
| 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 |
| 7216689 | Investment casting Pre-molding of wax or similar sacrificial material over one or more cores facilitates a subsequent molding over a core assembly. Individual cores or groups thereof may be pre-molded in a wax body. One or more such wax bodies may be assembled with other bodies and/or... | 05/15/2007 |
| 7216485 | Adjusting airflow in turbine component by depositing overlay metallic coating A method for adjusting the airflow in a turbine component having a plurality of airflow holes. The method comprises the step of depositing an overlay metallic coating on the surface of the turbine component in a manner such that at least some of the airflow holes ar... | 05/15/2007 |
| 7204019 | Method for repairing an apertured gas turbine component A method for repairing defects in a gas turbine component that comprises a substrate and an existing coating on the substrate. The article includes cooling holes having a predetermined air flow requirement and an outer shaped portion and an inner metering portion. T... | 04/17/2007 |
| 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 |
| 7163718 | Method of selective region vapor phase aluminizing A process for forming diffusion aluminide coatings on an uncoated surface of a substrate, without interdiffusing a sufficient amount of aluminum into a coating layer to adversely affect the coating growth potential and mechanical properties of said coating layer. A ... | 01/16/2007 |
| 7144215 | Method and apparatus for cooling gas turbine engine rotor blades A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and formin... | 12/05/2006 |
| 7137784 | Thermally loaded component A thermally loaded component has at least one cooling passage for the flow of a cooling fluid passing through it. In the region of a bend, at least one diverter device for the integral capturing of the flow of the cooling fluid is provided within the cooling passage... | 11/21/2006 |
| 7094445 | Dimensionally controlled pack aluminiding of internal surfaces of a hollow article An article such as a hollow gas turbine blade has an internal cavity therein with an inlet and outlet. The outlet has an outlet minimum transverse dimension of from about 0.009 inch to about 0.012 inch. An aluminiding source powder has a minimum particle size of gre... | 08/22/2006 |
| 7093359 | Composite structure formed by CMC-on-insulation process A method of manufacturing a composite structure uses a layer of an insulating material (22) as a mold for forming a substrate of a ceramic matrix composite (CMC) material (24). The insulating material may be formed in the shape of a cylinder (10... | 08/22/2006 |
| 7090463 | Guide vane A guide vane 100 is provided in which sheet portions 14, 15 are secured together to define an aerofoil profile 11. Between ends 20, 21 of the guide vane 100 there is a non linear variation in the maximum chordal thickness 13... | 08/15/2006 |
| 7066717 | Ceramic matrix composite airfoil trailing edge arrangement An airfoil (30) having a continuous layer of ceramic matrix composite (CMC) material (34) extending from a suction side (33) to a pressure side (35) around a trailing edge portion (31). The CMC material includes an inner wrap (3... | 06/27/2006 |
| 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 |
| 7028881 | Method for providing removable weld backing Method for welding objects having limited backside access to a cavity behind a region to be welded. The method includes inserting a fugitive backing material in an installation state into a first portion of the cavity proximate the region to be welded and then trans... | 04/18/2006 |
| 7014424 | Turbine element A turbine element airfoil has a cooling passageway network with a slot extending from a trailing passageway toward the trailing edge. A number of discrete posts span the slot between pressure and suction sidewall portions. ... | 03/21/2006 |
| 6994525 | 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... | 02/07/2006 |
| 6933459 | Methods and apparatus for fabricating a turbine engine blade A method for fabricating a turbine engine blade. The method includes providing a resistance welding system, and welding a metering plate to the turbine engine blade using the resistance welding system. ... | 08/23/2005 |
| 6923247 | Cooled components with conical cooling passages A thermally highly loaded machine component (10), which is protected from overheating by film cooling, is provided with conical cooling passages (30) of circular cross section. The cooling passages are designed so as to be divergent from the cold-gas s... | 08/02/2005 |
