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| 20150056459 | Articles Having Improved Corrosion Resistance - The present application relates to a method for enhancing metal corrosion resistance of a metal deposited on a substrate, the method comprises contacting the metal coated substrate with a treating composition comprising metal oxide nano-particles. Furthermore, the present application relates to a method for making a mirror comprising a substrate having a metal coated thereon, wherein the method comprises contacting the metal coated substrate with a treating composition comprising metal oxide nano-particles. Preferably, the metal oxide nano-particles are selected from one or more oxides of zinc, iridium, tin, aluminum, cerium, chromium, vanadium, titanium, iron, indium, copper, gold, palladium, platinum, manganese, cobalt, nickel, zirconium, molybdenum, rhodium, silver, indium, wolfram, iridium, lead, bismuth, samarium, erbium, or mixtures of these materials. In addition, the present application relates to the products obtainable by these methods. | 02-26-2015 |
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| 20110261473 | Articles Having Improved Corrosion Resistance - The present application relates to a method for enhancing metal corrosion resistance of a metal deposited on a substrate, the method comprises contacting the metal coated substrate with a treating composition comprising metal oxide nano-particles. Furthermore, the present application relates to a method for making a mirror comprising a substrate having a metal coated thereon, wherein the method comprises contacting the metal coated substrate with a treating composition comprising metal oxide nano-particles. Preferably, the metal oxide nano-particles are selected from one or more oxides of zinc, iridium, tin, aluminum, cerium, chromium, vanadium, titanium, iron, indium, copper, gold, palladium, platinum, manganese, cobalt, nickel, zirconium, molybdenum, rhodium, silver, indium, wolfram, iridium, lead, bismuth, samarium, erbium, or mixtures of these materials. In addition, the present application relates to the products obtainable by these methods. | 10-27-2011 |
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| 20110211965 | HOLLOW FAN BLADE - A blade includes a hollow metal airfoil having an opening to an internal cavity in a first major surface. A metal cover is adhesively bonded to a socket formed around the opening. The cover encloses the cavity and provides a continuous first major surface. | 09-01-2011 |
| 20120237351 | RETENTION FOR BONDED HOLLOW FAN BLADE COVER - A two part airfoil has a suction side, a pressure side, a rib extending from one of the pressure side or the second side, the rib having a groove therein, and a riblet extending from an other of the pressure side or the suction side, the riblet fitting within the groove. | 09-20-2012 |
| 20120301292 | HYBRID METAL FAN BLADE - A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium. | 11-29-2012 |
| 20130004322 | FAN BLADE WITH SHEATH - A fan blade includes an airfoil with a leading edge and a trailing edge in a chordwise direction, a root and a tip in a spanwise direction; and a sheath with a solid portion to cover the leading edge and first and second flanks extending in the chordwise direction to bond to the pressure and suction sides of the airfoil, respectively. The dimensions of the sheath are varied with respect to the spanwise direction of the blade. | 01-03-2013 |
| 20130078107 | HOLLOW FAN BLADE CHANNEL CONFIGURATION TO REDUCE STRESS - A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from an open side extending toward an opposed closed side. A plurality of ribs extending across the main body intermediate the channels, the fan blade has a dovetail, and an airfoil extending radially outwardly from said dovetail. A bottom surface of the channels is defined at the closed side of the channels. Sides of the channel merge into sides of the ribs, with a compound fillet at the bottom surface. A first radius of curvature is used along the bottom, and merging into at least a second radius of curvature at the sides. The first radius of curvature is larger than the second radius of curvature. | 03-28-2013 |
| 20130108470 | ROTOR BLADE WITH BONDED COVER | 05-02-2013 |
| 20130149163 | Method for Reducing Stress on Blade Tips - A turbine engine component has an airfoil portion with a tip portion and the tip portion has at least one chamfered edge on one side. If desired, the tip portion may have a first chamfered edge on a first side and a second chamfered edge on a second side opposed to the first side. A flattened tip portion may extend between the first and second chamfered edges. A tip treatment may be applied to the flattened tip portion. | 06-13-2013 |
| 20130167555 | ALUMINUM FAN BLADE CONSTRUCTION WITH WELDED COVER - An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. A cover skin is attached to the main body. The cover skin is welded to the main body at outer edges. An adhesive is placed between inner surfaces of the cover skin and the main body. The adhesive is deposited inwardly of the outer edges of the cover skin. | 07-04-2013 |
| 20130195633 | GAS TURBINE ROTARY BLADE WITH TIP INSERT - A rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip. The slot extends in a chordwise direction between the leading edge and trailing edge. The tip insert has a base end and a rub end. The base end of the tip insert is disposed within the slot. The rub end of the tip insert extends radially outward from the airfoil tip. | 08-01-2013 |
| 20130319010 | AIRFOIL COVER SYSTEM - An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first cover includes a first portion cooperates with a corresponding second portion. A second cover covers the first cover and forms at least a portion of the first surface with the body. The first cover is disposed between the body and the second cover. The first cover and the second cover have a different coefficient of thermal expansion than the body. | 12-05-2013 |
| 20140072427 | HOLLOW FAN BLADE WITH HONEYCOMB FILLER - A fan blade has an airfoil main body extending between a leading edge and a trailing edge. The airfoil also has suction and pressure sides. A cavity is formed into said main body, and receives a filler material. A cover closes off the cavity, and is attached to the main body, with the cover having a thickness defined in a direction perpendicular to the suction side. The main body has a spar which extends along the cavity, with a thickness of the spar at a central location between ends of the cavity which has a second thickness. A ratio of the first thickness to the second thickness is between 0.5 and 2. A fan rotor and a gas turbine engine are also disclosed. | 03-13-2014 |
| 20140169935 | LIGHTWEIGHT SHROUDED FAN BLADE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan. | 06-19-2014 |
| 20140170435 | HOLLOW AIRFOIL WITH COMPOSITE COVER AND FOAM FILLER - A hollow article includes a metallic hollow article formed from a having a first major surface, an internal cavity with an opening in the first major surface, and a socket around the opening; a cover of composite material received in the socket and covering the opening; and a filler material of foam in the internal cavity. | 06-19-2014 |
| 20140212261 | LIGHTWEIGHT SHROUDED FAN - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan. | 07-31-2014 |
| 20140219807 | UNDER-ROOT SPACER FOR GAS TURBINE ENGINE FAN BLADE - A gas turbine engine rotor includes a hub having a slot. A blade includes a root received in the slot. An under-root area is provided between the root and the fan hub in the slot. A spacer includes first and second portions that cooperate with one another to provide an adjustment feature with discrete height settings. The adjustment feature provides different radial heights of the spacer. The spacer is arranged in the under-root area beneath the root. | 08-07-2014 |
| 20140286781 | INTEGRAL FAN BLADE WEAR PAD AND PLATFORM SEAL - A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub. A fan blade has a root that is received in the slot. A wear pad is provided between the fan hub and the root and includes a flap integral with the wear pad to provide a seal relative to the platform. A fan blade for a gas turbine engine includes an airfoil extending from a root. A wear pad is secured to the root and has a free end providing a flap canted toward the root. | 09-25-2014 |
| 20150110636 | WEAR PAD TO PREVENT CRACKING OF FAN BLADE - A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate. | 04-23-2015 |
| 20150132142 | ROTOR BLADE WITH BONDED COVER - An airfoil comprises an airfoil body with an internal cavity and inner and outer covers. The airfoil body defines a first major surface of the airfoil, and a rib extends along the internal cavity. The inner cover is bonded to the airfoil body over the internal cavity, and includes a coupling element extending along the internal cavity in cooperative engagement with the rib. The outer cover is bonded to the airfoil body over the inner cover, and defines a second major surface of the airfoil. | 05-14-2015 |
| 20150198173 | Fan Blade With Variable Thickness Composite Cover - A fan blade having an opening on one side exposing one or more cavities, and a composite cover that fits over the opening, is provided. The composite cover has a variable thickness resulting from the layering of cover plies having different shapes, and is designed to achieve a lightweight fan blade having an optimal level of stiffness. | 07-16-2015 |
| 20150267541 | Fan Blade Composite Cover with Tapered Edges - A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening exposing at least one cavity to reduce the weight of the fan blade. The cover overlays the opening and includes a leading portion and a trailing portion that are tapered in the direction of the cover leading edge and cover trailing edge. | 09-24-2015 |
| 20150361798 | FAN BLADE INCLUDING EXTERNAL CAVITIES - A blade of a gas turbine engine includes a blade portion. The blade portion includes a first portion located radially outwardly that is located in a flow path and a second portion located radially inwardly of the first portion that is not located in the flow path. A plurality of external cavities is in the second portion of the blade portion. | 12-17-2015 |
| 20150377031 | COVERS FOR CAVITIES IN AIRCRAFT FAN BLADES - Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed. | 12-31-2015 |
| 20150377036 | FAN AIRFOIL SHROUDS WITH AREA RULING IN THE SHROUDS - A shrouded airfoil may have a suction surface and a pressure surface. An at least first suction surface shroud may be disposed on the suction surface and an at least first pressure surface shroud may be disposed on the pressure surface. The at least first suction surface shroud may include a first and second contoured surface and a first mating face. The first contoured surface may have a first substantially concave portion and a first substantially convex portion. The second contoured surface may have a second substantially concave portion and a second substantially convex portion. The at least first pressure surface shroud may include a third and fourth contoured surface and a second mating face. The third contoured surface may have a third substantially concave portion and a third substantially convex portion. The fourth contoured surface may have a fourth substantially concave portion and a fourth substantially convex portion. | 12-31-2015 |
| 20160024934 | ALUMINUM FAN BLADE CONSTRUCTION WITH WELDED COVER - An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. A cover skin is attached to the main body. The cover skin is welded to the main body with a weld at outer edges. An adhesive is placed between inner surfaces of the cover skin and the main body. The adhesive is deposited inwardly of the outer edges of the cover skin. A method of constructing an airfoil is also disclosed as is a gas turbine engine. | 01-28-2016 |
| 20160024946 | ROTOR BLADE DOVETAIL WITH ROUND BEARING SURFACES - A blade for use in a gas turbine engine, the blade having an airfoil portion and a dovetail root portion, wherein the dovetail root portion is dimensioned and configured to enable the blade to rotate within a shaped slot formed in a supporting hub of the engine about a center of rotation that extends parallel to a central axis of the hub in response to an impact force on the airfoil portion of the blade. | 01-28-2016 |
| 20160040541 | LIGHTWEIGHT BLADE FOR GAS TURBINE ENGINE - A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge. A rotor and a gas turbine engine are also disclose | 02-11-2016 |
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| 20100107868 | Multi-part piston for an internal combustion engine and method for its production - The present invention relates to a multi-part piston ( | 05-06-2010 |
| 20100107999 | Multi-part piston for an internal combustion engine and method for its production - A multi-part piston for an internal combustion engine has an upper piston part with a piston crown, and a lower piston part with pin boss supports and pin bosses connected with the pin boss supports. The upper piston part and the lower piston part each have an inner and an outer support element, which elements delimit an outer circumferential cooling channel. The inner support elements delimit a cavity that is open toward the pin bosses. The cavity is provided with a separate cooling oil collector that has at least one cooling oil opening. | 05-06-2010 |
| 20100108000 | Multi-part piston for an internal combustion engine and method for its production - A multi-part piston for an internal combustion engine has an upper piston part having a piston crown, and a lower piston part. The lower piston part has pin boss supports and pin bosses connected with them and the upper piston part and the lower piston part each have an inner and an outer support element, which elements delimit an outer circumferential cooling channel. The inner support elements delimit a cavity that is open toward the pin bosses. The cavity has a separate cooling oil collector that has at least one cooling oil opening. The piston is produced by manufacturing the upper piston part and lower piston part, inserting the cooling oil collector into the upper piston part or lower piston part, and joining the upper and lower piston parts together by friction welding. | 05-06-2010 |
| 20100108001 | Multi-part piston for an internal combustion engine and method for its production - A multi-part piston for an internal combustion engine has an upper piston part having a piston crown, and a lower piston part having pin boss supports and pin bosses connected with them. The upper piston part and lower piston part each have an inner and an outer support element, which delimit an outer circumferential cooling channel. The inner support elements delimit a cavity that is open toward the pin bosses, and the cavity is provided with a separate cooling oil collector that has at least one cooling oil opening. In a method for producing a piston, the upper and lower piston parts are manufactured, the cooling oil collector is inserted into one of the upper and lower piston parts in a region of the cavity, and the upper and lower piston parts are connected together at their support elements. | 05-06-2010 |
| 20100108016 | Multi-part piston for an internal combustion engine and method for its production - The present invention relates to a multi-part piston ( | 05-06-2010 |
| 20120131795 | METHOD FOR THE PRODUCTION OF A MULTI-PART PISTON FOR AN INTERNAL COMBUSTION ENGINE - A multi-part piston for an internal combustion engine has an upper piston part having a piston crown, and a lower piston part. The lower piston part has pin boss supports and pin bosses connected with them and the upper piston part and the lower piston part each have an inner and an outer support element, which elements delimit an outer circumferential cooling channel. The inner support elements delimit a cavity that is open toward the pin bosses. The cavity has a separate cooling oil collector that has at least one cooling oil opening. The piston is produced by manufacturing the upper piston part and lower piston part, inserting the cooling oil collector into the upper piston part or lower piston part, and joining the upper and lower piston parts together by friction welding. | 05-31-2012 |
| 20120151766 | MULTI-PART PISTON FOR AN INTERNAL COMBUSTION ENGINE AND METHOD FOR ITS PRODUCTION - A method for the production of a multi-part piston for an internal combustion engine involves producing an upper piston part having a piston crown as well as an inner and an outer support element, and producing a lower piston part having a skirt and having pin boss supports and pin bosses connected with the pin boss supports, and an inner and an outer support element. A separate cooling oil collector having at least one cooling oil opening is inserted into the upper piston part or the lower piston part. The upper piston part and the lower piston part are connected in such a manner that the inner and outer support elements of the upper and lower piston parts, delimit an outer circumferential cooling channel and a cavity that is open toward the pin bosses and provided with the cooling oil collector. | 06-21-2012 |
| 20120222645 | Piston for an internal combustion engine and method for its production - The present invention relates to a piston ( | 09-06-2012 |
| 20120240881 | MULTI-PART PISTON FOR AN INTERNAL COMBUSTION ENGINE - A multi-part piston for an internal combustion engine has an upper piston part having a piston crown, and a lower piston part having pin boss supports and pin bosses connected with them. The upper piston part and lower piston part each have an inner and an outer support element, which delimit an outer circumferential cooling channel. The inner support elements delimit a cavity that is open toward the pin bosses, and the cavity is provided with a separate cooling oil collector that has at least one cooling oil opening. | 09-27-2012 |
| 20130068096 | LASER WELDED PISTON ASSEMBLY - An exemplary piston may include a piston body having radially inner and outer body mating surfaces. The piston may further include a cooling gallery ring cooperating with the piston body to form a continuous upper combustion bowl surface and a cooling gallery. The cooling gallery ring may have radially inner and outer ring mating surfaces abutted along their corresponding radially inner and outer body mating surfaces, such that the cooling gallery is substantially enclosed. The piston body and cooling gallery ring may be joined together along the radially inner and radially outer interface regions to form a generally one-piece piston assembly. The radially outer interface region may be elongated in a direction parallel to the piston axis, e.g., facilitating a laser welding joining process. | 03-21-2013 |
| 20140190443 | PISTON FOR AN INTERNAL COMBUSTION ENGINE AND METHOD FOR ITS PRODUCTION - A piston for an internal combustion engine, having a piston base body, a piston ring element having at least an inner region of a piston crown, and a piston skirt. The piston is provided with pin bosses having pin bores and the ring element has at least an outer region of a piston crown having a circumferential top land and a circumferential ring belt provided with ring grooves. The piston base body and piston ring element are joined together by way of corresponding, conical joining surfaces configured on them. | 07-10-2014 |
| 20140272188 | ANTI-FRICTION COATING TO PISTON ASSEMBLY - A method of applying an anti-friction coating to a piston assembly is provided including applying an anti-friction coating to at least a portion of the surface area of a piston. The anti-friction coating comprises a binder matrix and a solid lubricant. A localized curing energy is applied to only a portion of the surface area. The localized curing energy comprises a first curing energy. | 09-18-2014 |
