A fluid cylinder for a reciprocating pump includes a body having inlet, outlet, and plunger bores. The inlet and outlet bores extend coaxially along a fluid passage axis. The plunger bore extends along a plunger bore axis that extends at an angle relative to the fluid passage axis. The body includes a crossbore at the intersection of the fluid passage axis and the plunger bore axis. The crossbore intersects the inlet, outlet, and plunger bores at respective inlet, outlet, and plunger bore ends. The inlet bore end and outlet bore ends are connected to the plunger bore end at respective first and second corners of the crossbore. The first corner includes a first linear bridge segment connected to the inlet and plunger bore ends by corresponding curved segments. The second corner includes a second linear bridge segment connected to the outlet and plunger bore ends by corresponding curved segments.

A method of manufacturing a fluid apparatus with flanges that are fastened together may include the following steps: fastening the flanges with a fastening member; introducing a fluid into an internal space of the fluid apparatus, and plastically deforming portions of the flanges that form seats for receiving the fastening member and portions of the flanges that form mating surfaces with pressure of the fluid being applied; releasing the fastening member and correcting at least the mating surfaces out of the seats and the mating surfaces; and refastening the flanges.

A combustion chamber liner comprising a plurality of spiral cooling channels is formed from a material component. A combustion chamber liner body extends from a first end and a second end. The combustion chamber liner body comprises a combustion chamber liner internal wall that defines a combustion area cavity extending from the first and second end. The combustion chamber liner body also comprises a combustion chamber liner external wall that is opposite the internal wall. The combustion chamber liner body also defines an inlet port, a nozzle exit port opposite the inlet port, and a throat portion. Along the combustion chamber liner external wall, spiral cooling channels are cut into the external wall such that the spiral cooling channels extend between the first and second end.

A method of coating an area of a wind turbine rotor blade comprises: defining an area to be coated on a surface of the blade, applying a first plurality of strips of masking tape to the surface of the blade proximate a first edge region of the defined area such that each strip is arranged adjacent to at least one other strip of said first plurality of strips, spraying a coating layer onto the defined area up to an innermost strip such that the innermost strip defines an edge of the coating layer, removing the innermost strip(s) to expose an uncoated region of the defined area between the edge of the coating layer and an innermost remaining strip and spraying a further coating layer over the previous coating layer and over the uncoated region up to said innermost remaining strip.

A material core (100) for wind turbine blade, comprising: a core body (101); a first groove (102) extending from a first side (104) of the core body (101), in a first direction (106), into a depth d1 in the core body (101); and a second groove (103) extending from a second side (105) of the core body (101) facing away from the first side (104), in a direction opposite to the first direction (106), into a depth d2 in the core body (101), wherein the second groove (103) is parallel to the first groove (102), and wherein: d2=td1+x, 1 mmx<d1, wherein t is a thickness of the core body (101), and wherein a distance between the first and second grooves is o, wherein: 1 mmo5 mm.

This invention relates to a method and a wind turbine blade, wherein one or more airflow modifying devices are attached to a wind turbine blade having a base aerodynamic profile. The base aerodynamic profile is configured to substantially carry the structural loading of this modified wind turbine blade. The airflow modifying device is manufactured via 3D-printing and/or via 3D-machining and optionally coated or laminated before attachment. Once attached, the airflow modifying device may further be coated or laminated before working the outer surfaces into their finished shape.

The present disclosure is directed methods for manufacturing spar caps for wind turbine rotor blades. In certain embodiments, the method includes forming an outer frame or tray of the spar cap via at least one of three-dimensional (3D) pultrusion, thermoforming, or 3D printing. As such, the outer frame has a varying cross-section that corresponds to a varying cross-section of the rotor blade along a span thereof. The method also includes arranging a plurality of structural materials (e.g. layers of pultruded plates) within the pultruded outer frame of the spar cap and infusing the structural materials and the outer frame together via a resin material so as to form the spar cap. The resulting spar cap can then be easily incorporated into conventional rotor blade manufacturing processes and/or welded or bonded to an existing rotor blade.

Provided is a method of shaping an initial edge seal along a longitudinal edge step of an add-on part mounted on the outer surface of a rotor blade, which method includes the steps of providing an initial edge seal along a longitudinal edge step of an add-on part mounted on an outer surface of a rotor blade, and removing a top layer of the initial edge seal. Further provided is wind turbine rotor blade.

A method of repairing a wind turbine rotor blade, in particular an existing wind turbine rotor blade, that has erosion damage or transport damage. A first region is ablated into a surface or a surface coating of the rotor blade. An adhesive is applied to the ablated region, an erosion protection film is placed on the adhesive and the adhesive is cured.

A tip portion of a compressor blade faces a casing with a clearance therebetween. The tip portion has an upstream-side region including a blade leading edge, and a downstream-side region including a blade trailing edge. The upstream-side region has a small clearance formation portion including a part in which the clearance is a minimum in the tip portion. The downstream-side region forms a large clearance formation portion having a clearance larger than a clearance of the small clearance formation portion throughout the entire region of the downstream-side region.