Abstract: A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to: ( D ? 1 eq ? min D ? 2 eq ? min ) ? ( R D ? 2 eq ? min ) .

Abstract: A method of forming a component that includes identifying an acute angle in an original model that is a virtual model of the component. The acute angle is defined by a first surface and a second surface. The method includes compensating the original model at the acute angle to create a compensated acute angle in a compensated model. The method also includes forming, by additive manufacturing, the component based upon the compensated model, where the formed component is more alike the original model than the compensated model.

Abstract: A method of using additive manufacturing to form or print a component based on an original model of a component, where the geometry of the original model is compensated to form a compensated model. The compensated model can be used to form or print the component. The printed component as a final model can then be compared to the original model.

Abstract: The disclosure relates to a component for a turbine engine with a heated airflow and a cooling airflow. The component includes a wall separating the heated airflow from the cooling airflow. The wall can have a heated surface confronting the heated airflow and a cooled surface confronting the cooling airflow. The component can also include a baffle with a set of cooling holes.

Abstract: An engine component for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side. The engine component further comprising at least one cooling conduit provided in the interior and having conduit sidewalls and a set of cooling passages formed in the wall and fluidly coupling the at least one cooling conduit to the outer surface, at least one of the cooling passages in the set comprising a primary cooling passage portion and a secondary cooling passage portion. A diffusion slot located in the primary cooling passage portion and an impingement zone fluidly coupled to the diffusion slot.

Abstract: An airfoil for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the airfoil comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side extending between a leading edge and a trailing edge to define a chord-wise direction; at least one cooling conduit located within the interior and fluidly coupled to the cooling airflow. A primary cooling passage having at least one inlet fluidly coupled to the at least one cooling conduit, a primary outlet on the outer surface. A passage connecting the at least one inlet to the primary outlet, the passage separated into a first portion and a second portion. The primary outlet spaced from the trailing edge a predetermined distance.

Abstract: An engine component for a turbine engine comprising a wall defining an interior and having an outer surface over which flows the combustion airflow. The outer surface defining a first side and a second side extending between an upstream edge and a downstream edge and extending between a root and a tip. At least one cooling conduit provided in the interior and having conduit sidewalls; a set of cooling passages with at least one of the cooling passages in the set comprising: a first cooling passage portion having a surface outlet opening on the surface; a second cooling passage portion, intersecting the first cooling passage portion, and having an inlet fluidly coupled to the cooling conduit and an intermediate outlet fluidly connecting the second cooling passage portion to the first cooling passage at the intersection. The cooling passage comprising at least one fillet.

Abstract: An airfoil for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the airfoil comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side extending between a leading edge and a trailing edge to define a chord-wise direction; at least one cooling conduit located within the interior and fluidly coupled to the cooling airflow. A primary cooling passage having at least one inlet fluidly coupled to the at least one cooling conduit, a primary outlet on the outer surface. A passage connecting the at least one inlet to the primary outlet, the passage separated into a first portion and a second portion. The primary outlet spaced from the trailing edge a predetermined distance.

Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.

Abstract: A method of using additive manufacturing to form or print a component based on an original model of a component, where the geometry of the original model is compensated to form a compensated model. The compensated model can be used to form or print the component. The printed component as a final model can then be compared to the original model.

Abstract: The disclosure relates to a component for a turbine engine with a heated airflow and a cooling airflow. The component includes a wall separating the heated airflow from the cooling airflow. The wall can have a heated surface confronting the heated airflow and a cooled surface confronting the cooling airflow. The component can also include a baffle with a set of cooling holes.

Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.

Abstract: A shroud for a turbine engine includes a body having a first surface with an inlet fluidly coupled to a cooling fluid flow, and a second surface facing a heated fluid flow. A cavity within the body can be fluidly coupled to the inlet and include an impingement zone thermally coupled to the second surface.

Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.

Abstract: A shroud for a gas turbine is provided. The shroud can include an outer box having a first wall and a second wall circumferentially spaced apart from the first wall. An inner box is positioned within the outer box. The inner box defines one or more passageways extending therethrough and a first chamber. The inner box and the outer box collectively define a second chamber. The one or more passageways defined by the inner box fluidly couple the first chamber and the second chamber. The first wall of the outer box defines a first boss and first notch, and the second wall of the outer box defines a second boss and notch. A gas turbine is also provided that can include a plurality of such turbine shrouds.

Abstract: A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge. Each cooling hole includes in downstream serial cooling flow relationship, a curved inlet, a constant area and constant width metering section, and a spanwise diverging section leading into the trailing edge cooling slot, and a spanwise height substantially greater than a hole width through the cooling hole. A pressure sidewall surface of the pressure sidewall may be planar through the metering and diverging sections. The width may be constant through the metering and diverging sections. A raised floor may include a flat up ramp in the diverging section, a flat down ramp in the slot.

Abstract: A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to trailing edge. Each cooling hole includes an asymmetric flow cross section through one or more asymmetric intermediate sections leading into slot. Flow cross section is asymmetric with respect to a mid-plane extending axially and spanwise through intermediate sections. Different trailing edge cooling holes may include different asymmetric flow cross sections. Lands may extend between the cooling slots. A raised floor may extend away from at least one of pressure or suction sidewalls at least partially through one or more asymmetric intermediate sections and optionally at least partially through cooling slot. Raised floor may include up and down ramps and a flat transition section between ramps.

Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.

Abstract: A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge. Each cooling hole includes a plug extending downstream through at least a portion of a spanwise diverging section leading into the slot. The plug may be spanwise centered in the hole and may include a plug dome rising up from a plug base extending along a suction sidewall surface of the suction sidewall. The cooling hole may further include an inlet leading to a metering section with a constant area and constant width flow cross section upstream of spanwise diverging section. Lands may be disposed between the trailing edge cooling slots forming slot floors between lands.

Abstract: A gas turbine engine turbine airfoil having pressure and suction sidewalls extending outwardly along a span and chordwise between opposite leading and trailing edges. A spanwise row of spaced apart bifurcated trailing edge cooling holes encased in the pressure sidewall end at corresponding trailing edge cooling slots extending chordally substantially to the trailing edge. Axially extending inter-hole partitions separate the cooling holes. An inlet between adjacent pairs of the inter-hole partitions includes a divergent inlet section. An axial intra-hole partition bifurcates the cooling hole into diverging upper and lower diverging sections downstream and aft of the divergent inlet section. A forward end of the intra-hole partition divides an aft end of the divergent inlet section into upper and lower inlet flowpaths leading to the upper and lower diverging sections leading into the trailing edge cooling slots.