Abstract: An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

Abstract: An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

Abstract: A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body includes a ceramic material. A shape of the extension includes a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis includes an ellipse. The extension is connected to the investment core body by the connection portion.

Abstract: An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

Abstract: A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

Abstract: A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

Abstract: An induction furnace assembly comprising a chamber having a mold; a primary inductive coil coupled to the chamber; a layered susceptor comprising at least two layers of magnetic field attenuating material surrounding the chamber between the primary inductive coil and the mold to nullify the electromagnetic field in the hot zone of the furnace chamber.

Abstract: A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; energizing a primary inductive coil within the chamber to heat the mold via radiation from a susceptor, wherein the resultant electromagnetic field partially leaks through the susceptor coupled to the chamber between the primary inductive coil and the mold; determining a magnetic flux profile of the electromagnetic field; sensing a magnetic flux leakage past the susceptor within the chamber; generating a control field from a secondary compensation coil coupled to the chamber, wherein the control field controls the magnetic flux experienced by the cast part; and casting the material within the mold under the controlled degree of flux leakage.

Abstract: A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; generating an electromagnetic field with the primary inductive coil within the chamber, wherein said electromagnetic field is partially attenuated by a susceptor coupled to said chamber between said primary inductive coil and said mold; determining a magnetic flux profile of the electromagnetic field after it passes through the susceptor; sensing a component of the magnetic flux in the interior of the susceptor proximate the mold; positioning a mobile secondary compensation coil within the chamber; generating a control field from a secondary compensation coil, wherein said control field controls said magnetic flux; and casting the material within the mold.

Abstract: A method for manufacturing a solid propellant includes: forming a tool of layers of a first material wherein cuts in the layers form a first interior chamber in the tool; using the tool to mold a second material in the first interior chamber; removing the molded second material from the tool; using the molded second material to mold an interior chamber in a rocket propellant grain; and removing the molded second material from the rocket propellant grain.

Abstract: A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; energizing a primary inductive coil within the chamber to heat the mold via radiation from a susceptor, wherein the resultant electromagnetic field partially leaks through the susceptor coupled to the chamber between the primary inductive coil and the mold; determining a magnetic flux profile of the electromagnetic field; sensing a magnetic flux leakage past the susceptor within the chamber; generating a control field from a secondary compensation coil coupled to the chamber, wherein the control field controls the magnetic flux experienced by the cast part; and casting the material within the mold under the controlled degree of flux leakage.

Abstract: An induction furnace assembly comprising a chamber having a mold; a primary inductive coil coupled to the chamber; a layered susceptor comprising at least two layers of magnetic field attenuating material surrounding the chamber between the primary inductive coil and the mold to nullify the electromagnetic field in the hot zone of the furnace chamber.

Abstract: A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; energizing a primary inductive coil within the chamber to heat the mold via radiation from a susceptor, wherein the resultant electromagnetic field partially leaks through the susceptor coupled to the chamber between the primary inductive coil and the mold; determining a magnetic flux profile of the electromagnetic field; sensing a magnetic flux leakage past the susceptor within the chamber; generating a control field from a secondary compensation coil coupled to the chamber, wherein the control field controls the magnetic flux experienced by the cast part; and casting the material within the mold under the controlled degree of flux leakage.

Abstract: A method of removing a core of a cast component includes providing a casting that includes a silica based ceramic core in a temperature controlled closed volume; cycling temperature between a first temperature and a second temperature within the temperature controlled closed volume that repeatedly subjects the silica based ceramic core to a beta-to-alpha cristobalite transition that induces microfractures in the silica based ceramic core; and after the cycling temperature, chemically dissolving the silica based ceramic core from the casting.

Abstract: An induction furnace assembly comprising a chamber having a mold; a primary inductive coil coupled to the chamber; a layered susceptor comprising at least two layers of magnetic field attenuating material surrounding the chamber between the primary inductive coil and the mold to nullify the electromagnetic field in the hot zone of the furnace chamber.

Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

Abstract: A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; generating an electromagnetic field with the primary inductive coil within the chamber, wherein said electromagnetic field is partially attenuated by a susceptor coupled to said chamber between said primary inductive coil and said mold; determining a magnetic flux profile of the electromagnetic field after it passes through the susceptor; sensing a component of the magnetic flux in the interior of the susceptor proximate the mold; positioning a mobile secondary compensation coil within the chamber; generating a control field from a secondary compensation coil, wherein said control field controls said magnetic flux; and casting the material within the mold.

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.