| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416231000 | Apertured or permeable | 14 |
| 20090297357 | PROPFAN ASSEMBLY - A propfan assembly includes a plurality of blades that each include an internal cavity containing a noise attenuation structure. Acoustic energy is communicated to the internal cavity through a plurality of openings in the blade surfaces. The cavities include features for attenuating noise energy to reduce generation of noise emitted from the propfan assembly. | 12-03-2009 |
| 20100074758 | LAMINAR FLOW ROTOR AND RELATED METHODS AND SYSTEMS - A rotor blade including a root attachable to a rotor hub. The blade includes a tip and one or more channels aligned within the blade generally between the root and the tip. Each channel has a sealed first end and a second end vented to outside the blade. The channel(s) are vented to one or more exterior surfaces of the blade through one or more apertures in the exterior surface(s). | 03-25-2010 |
| 20110211970 | WIND TURBINE BLADES WITH IMPROVED BOND LINE AND ASSOCIATED METHOD - A wind turbine blade includes an upper shell member and a lower shell member with an internal cavity therebetween. The shell members are joined at leading and trailing edges of the blade with a bond paste along a bond line having a designed width. A barrier is disposed within the internal cavity between the upper and lower shell members along at least one of the leading or trailing edges and prevents movement of the bond paste into the internal cavity beyond the width of the bond line. The barrier includes a wall that is substantially impermeable to the bond paste and a support member that extends from the wall to the leading or trailing edge of the blade. The support member locates the wall at the bond line and the wall has a shape and resiliency so as to be engaged against the upper and lower shell members within the internal cavity. | 09-01-2011 |
| 20120114495 | GAS TURBINE ENGINE AND BLADE FOR GAS TURBINE ENGINE - One embodiment of the present invention is a unique gas turbine engine blade. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and blades. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 05-10-2012 |
| 20130052029 | HOLLOW CORE AIRFOIL STIFFENER RIB - A stiffener rib for a non-cooled, hollow core airfoil of a turbine blade is described. The stiffener rib is constituted by an elongated solid metal piece dimensioned for securement in a hollow region of a core portion of the airfoil. The stiffener rib is shaped and oriented upwards from a leading edge of the airfoil at a predetermined calculated angle to minimize mode 2 deformation of the blade at a trailing edge thereof while improving the rigidity of the turbine blade. | 02-28-2013 |
| 20140199173 | CERAMIC MATRIX COMPOSITE ARTICLE AND PROCESS OF FABRICATING A CERAMIC MATRIX COMPOSITE ARTICLE - A ceramic matrix composite article and a process of fabricating a ceramic matrix composite are disclosed. The ceramic matrix composite article includes a matrix distribution pattern formed by a manifold and ceramic matrix composite plies laid up on the matrix distribution pattern, includes the manifold, or a combination thereof. The manifold includes one or more matrix distribution channels operably connected to a delivery interface, the delivery interface configured for providing matrix material to one or more of the ceramic matrix composite plies. The process includes providing the manifold, forming the matrix distribution pattern by transporting the matrix material through the manifold, and contacting the ceramic matrix composite plies with the matrix material. | 07-17-2014 |
| 20140255199 | ROTATOR - A rotator may be configured to be accommodated in a casing of a pump for sucking a fluid into the casing and discharging the fluid outside of the casing. The rotator may comprise an insert portion configured to insert a rotating shaft and one or more communicating openings. The one or more communicating openings may be disposed in a vicinity of the insert portion, and pierce the rotator in a direction along the rotating shaft. The rotator may be made of resin. A flow direction of the resin located around the insert portion and the one or more communicating openings may extend at least in the direction along the rotating shaft. | 09-11-2014 |
| 20140255200 | FILM COOLING OF TURBINE BLADES OR VANES - The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (α) towards each other, with the deflection angle (α) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (α) towards each other. | 09-11-2014 |
| 20140301860 | AIRFOIL HAVING A PROFILED TRAILING EDGE FOR A FLUID FLOW MACHINE, BLADE, AND INTEGRALLY BLADE ROTOR - The present invention relates to an airfoil for a fluid flow machine ( | 10-09-2014 |
| 20150322799 | METHOD FOR FORMING COMPONENTS USING ADDITIVE MANUFACTURING AND RE-MELT - A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified. | 11-12-2015 |
| 20160003052 | DAMAGE TOLERANT COOLING OF HIGH TEMPERATURE MECHANICAL SYSTEM COMPONENT INCLUDING A COATING - An article may include a substrate, a plurality of cooling holes in the substrate, wherein each of the plurality of cooling holes defines substantially the same diameter measured parallel to an outer surface of the substrate, and a coating on the surface of the substrate. In accordance with these examples, the coating covers and substantially blocks a first set of cooling holes from the plurality of cooling holes and leaves a second set of cooling holes from the plurality of cooling holes substantially uncovered. In some examples, an article including a substrate, a plurality of cooling holes in the substrate, and a coating on the substrate. In accordance with these examples, the coating covers and partially occludes each cooling hole of the plurality of cooling holes, and the coating does not extend into any of the plurality of cooling holes. | 01-07-2016 |
| 20160160653 | TURBINE WHEEL FOR TURBO CHARGER - A turbine wheel for a turbine charger includes a hub and a set of wheel blades configured to be arranged around the hub. A wheel blade has a section structure of an air-foil which has a pressure side and a suction side. The turbine wheel is capable of remarkably increasing an output of a vehicle engine by increasing a rotation power of the turbine wheel to increase a compression rate of sucked air. | 06-09-2016 |
| 20100322777 | COMPRESSOR BLADE | 12-23-2010 |
| 20150322803 | ROTOR FOR A GAS TURBINE ENGINE - A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor. | 11-12-2015 |
| 416231000 | Slotted blade | 2 |
| 20090297357 | PROPFAN ASSEMBLY - A propfan assembly includes a plurality of blades that each include an internal cavity containing a noise attenuation structure. Acoustic energy is communicated to the internal cavity through a plurality of openings in the blade surfaces. The cavities include features for attenuating noise energy to reduce generation of noise emitted from the propfan assembly. | 12-03-2009 |
| 20100074758 | LAMINAR FLOW ROTOR AND RELATED METHODS AND SYSTEMS - A rotor blade including a root attachable to a rotor hub. The blade includes a tip and one or more channels aligned within the blade generally between the root and the tip. Each channel has a sealed first end and a second end vented to outside the blade. The channel(s) are vented to one or more exterior surfaces of the blade through one or more apertures in the exterior surface(s). | 03-25-2010 |
| 20110211970 | WIND TURBINE BLADES WITH IMPROVED BOND LINE AND ASSOCIATED METHOD - A wind turbine blade includes an upper shell member and a lower shell member with an internal cavity therebetween. The shell members are joined at leading and trailing edges of the blade with a bond paste along a bond line having a designed width. A barrier is disposed within the internal cavity between the upper and lower shell members along at least one of the leading or trailing edges and prevents movement of the bond paste into the internal cavity beyond the width of the bond line. The barrier includes a wall that is substantially impermeable to the bond paste and a support member that extends from the wall to the leading or trailing edge of the blade. The support member locates the wall at the bond line and the wall has a shape and resiliency so as to be engaged against the upper and lower shell members within the internal cavity. | 09-01-2011 |
| 20120114495 | GAS TURBINE ENGINE AND BLADE FOR GAS TURBINE ENGINE - One embodiment of the present invention is a unique gas turbine engine blade. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and blades. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 05-10-2012 |
| 20130052029 | HOLLOW CORE AIRFOIL STIFFENER RIB - A stiffener rib for a non-cooled, hollow core airfoil of a turbine blade is described. The stiffener rib is constituted by an elongated solid metal piece dimensioned for securement in a hollow region of a core portion of the airfoil. The stiffener rib is shaped and oriented upwards from a leading edge of the airfoil at a predetermined calculated angle to minimize mode 2 deformation of the blade at a trailing edge thereof while improving the rigidity of the turbine blade. | 02-28-2013 |
| 20140199173 | CERAMIC MATRIX COMPOSITE ARTICLE AND PROCESS OF FABRICATING A CERAMIC MATRIX COMPOSITE ARTICLE - A ceramic matrix composite article and a process of fabricating a ceramic matrix composite are disclosed. The ceramic matrix composite article includes a matrix distribution pattern formed by a manifold and ceramic matrix composite plies laid up on the matrix distribution pattern, includes the manifold, or a combination thereof. The manifold includes one or more matrix distribution channels operably connected to a delivery interface, the delivery interface configured for providing matrix material to one or more of the ceramic matrix composite plies. The process includes providing the manifold, forming the matrix distribution pattern by transporting the matrix material through the manifold, and contacting the ceramic matrix composite plies with the matrix material. | 07-17-2014 |
| 20140255199 | ROTATOR - A rotator may be configured to be accommodated in a casing of a pump for sucking a fluid into the casing and discharging the fluid outside of the casing. The rotator may comprise an insert portion configured to insert a rotating shaft and one or more communicating openings. The one or more communicating openings may be disposed in a vicinity of the insert portion, and pierce the rotator in a direction along the rotating shaft. The rotator may be made of resin. A flow direction of the resin located around the insert portion and the one or more communicating openings may extend at least in the direction along the rotating shaft. | 09-11-2014 |
| 20140255200 | FILM COOLING OF TURBINE BLADES OR VANES - The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (α) towards each other, with the deflection angle (α) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (α) towards each other. | 09-11-2014 |
| 20140301860 | AIRFOIL HAVING A PROFILED TRAILING EDGE FOR A FLUID FLOW MACHINE, BLADE, AND INTEGRALLY BLADE ROTOR - The present invention relates to an airfoil for a fluid flow machine ( | 10-09-2014 |
| 20150322799 | METHOD FOR FORMING COMPONENTS USING ADDITIVE MANUFACTURING AND RE-MELT - A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified. | 11-12-2015 |
| 20160003052 | DAMAGE TOLERANT COOLING OF HIGH TEMPERATURE MECHANICAL SYSTEM COMPONENT INCLUDING A COATING - An article may include a substrate, a plurality of cooling holes in the substrate, wherein each of the plurality of cooling holes defines substantially the same diameter measured parallel to an outer surface of the substrate, and a coating on the surface of the substrate. In accordance with these examples, the coating covers and substantially blocks a first set of cooling holes from the plurality of cooling holes and leaves a second set of cooling holes from the plurality of cooling holes substantially uncovered. In some examples, an article including a substrate, a plurality of cooling holes in the substrate, and a coating on the substrate. In accordance with these examples, the coating covers and partially occludes each cooling hole of the plurality of cooling holes, and the coating does not extend into any of the plurality of cooling holes. | 01-07-2016 |
| 20160160653 | TURBINE WHEEL FOR TURBO CHARGER - A turbine wheel for a turbine charger includes a hub and a set of wheel blades configured to be arranged around the hub. A wheel blade has a section structure of an air-foil which has a pressure side and a suction side. The turbine wheel is capable of remarkably increasing an output of a vehicle engine by increasing a rotation power of the turbine wheel to increase a compression rate of sucked air. | 06-09-2016 |
| 20100322777 | COMPRESSOR BLADE | 12-23-2010 |
| 20150322803 | ROTOR FOR A GAS TURBINE ENGINE - A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor. | 11-12-2015 |
