A method of manufacturing a turbine blade includes forming a blade body divided body constituting a blade body of the turbine blade by a three-dimensional lamination method; individually forming a plurality of shroud divided bodies constituting a shroud of the turbine blade for each of the shroud divided bodies by a three-dimensional lamination method; joining the shroud divided bodies together; and joining the blade body divided body and the shroud divided bodies.

A mounting plate for forming a gas turbine engine component according to an example of the present disclosure includes, among other things, a plate body defining an abutment dimensioned to mate with a forming die. The plate body defines at least one internal cooling circuit. The at least one internal cooling circuit includes a passageway having an intermediate portion interconnecting inlet and outlet portions. The intermediate portion is dimensioned to follow a perimeter of the abutment. The intermediate portion includes a plurality of fins extending partially from a first sidewall towards a second sidewall opposed to the first sidewall. A method of forming a gas turbine engine component is also disclosed.

A method for producing a rotor disk or a rotor blade for a gas turbine compressor stage or turbine stage of an aeroengine, wherein at least one blade groove of the rotor disk for arrangement of a blade foot of a rotor blade for fastening the rotor blade to the rotor disk, or a blade foot of the rotor blade for arrangement in a blade groove of a rotor disk for fastening the rotor blade to the rotor disk is fabricated using an electrochemical material removal and in the axial direction has a profile which is curved once or more.

A blade component of a compressor or turbine stage of a gas turbine, in particular of a gas turbine engine is provided. The blade component has at least two structural elements which can be connected together by means of a connection process, in particular sintering. The at least two structural elements can be coupled and/or connected to at least one means for internal cooling of the blade component, and/or the means for internal cooling of the blade component is arranged in at least one of the least two structural elements. The at least two structural elements, when assembled, can be coupled to a cooling insert inside the blade component, wherein during operation, cooling air flowing into the cooling insert can be guided in targeted fashion via impingement cooling openings onto the inside of the blade component, in particular as impingement flow cooling.

A turbocharger includes a housing and a rotating group supported for rotation within the housing. The rotating group includes a compressor wheel disposed within a compressor section of the turbocharger, and the rotating group includes a turbine wheel disposed within a turbine section of the turbocharger. The turbine wheel includes a bleed pressure surface. The turbocharger further includes a bleed passage that extends at least partly through the housing to fluidly connect the compressor section to the turbine section. The bleed passage is configured to direct a bleed flow of fluid from the compressor section to the bleed pressure surface to supply a thrust counterbalance load to the bleed pressure surface.

The invention relates to a method for reinforcing a part of the outer surface of a wind turbine blade, said method comprises the steps: i) providing a blade plug having an outer surface resembling the topography of the outer surface of at least a leading portion of at least part of the length of a wind turbine blade; ii) casting a mold of part of the blade plug obtained in step i) in such a way that the topography of an inner surface of said mold corresponds to the topography of part of an outer surface of said blade plug provided in step i); iii) from the mold obtained in step ii), preparing a protective shell by making a casting of the inner surface of said mold; said protective shell is comprising an inner surface and an outer surface, said protective shell is being made from one or more predetermined materials; iv) starting from the topography of the surface of the wind turbine blade; or starting from a blade plug as obtained in step i) preparing an enlarged plug; said enlarged plug thereby comprising an outer surface resembling the topography of the outer surface of at least a leading part of said wind turbine blade; said outer surface of said enlarged plug is having larger dimensions than said outer surface of said blade plug; v) from the enlarged plug obtained in step iv), casting a mounting shell having an inner surface and an outer surface, in such a way that the topography of at least part of an inner surface of said mounting shell corresponds to the topography of part of an outer surface of said enlarged plug; vi) applying an adhesive to at least part of the inner surface of said protective shell and/or to at least part of the outer surface of at least a leading portion of said outer surface of said wind turbine blade; vii) fitting the inner surface of said protective shell onto at least a leading portion of the outer surface of said wind turbine blade; viii) fitting the inner surface of said mounting shell onto said outer surface of said protective shell; ix) applying a force to said mounting shell, and thereby also to said outer surface of said protective shell; wherein said force comprises a force component in a cord direction from the leading surface to the trailing surface of said wind turbine blade; wherein said force additionally comprises a force component in a direction perpendicular to the cord direction and perpendicular to the lengthwise direction of said wind turbine blade; thereby pressing said mounting shell and said protective shell against the outer surface of the wind turbine blade; x) allowing said adhesive applied in step vi) to cure, and subsequently removing said mounting shell from said wind turbine blade and from said pro

An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

A fixture assembly including a first fixture portion; a second fixture portion that interfaces with the first fixture portion; and a bladder assembly mounted to the second fixture portion to face the first fixture portion. A method of manufacturing a fan blade includes inserting a blade body and a cover into a fixture; and deploying a bladder assembly within the fixture to press the cover into the blade body.

A fixture assembly including a first fixture portion; a second fixture portion that interfaces with the first fixture portion; and a bladder assembly mounted to the second fixture portion to face the first fixture portion. A method of manufacturing a fan blade includes inserting a blade body and a cover into a fixture; and deploying a bladder assembly within the fixture to press the cover into the blade body.