Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

Abstract: An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.

Abstract: A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.

Abstract: A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

Abstract: An attritable gas turbine engine casing unitary charging volume comprising a casing having an interior wall and an exterior wall opposite the interior wall; a unitary charging volume formed between the exterior wall and the interior wall.

Abstract: A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.

Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

Abstract: A propulsion system according to an example of the present disclosure, includes a core engine and an outer casing surrounding the core engine. The outer casing includes an integral injector assembly. The injector assembly includes a wall that defines a cavity, the wall being integral with the outer casing. A method of operating a propulsion system and method of making a component of a propulsion system are also disclosed.

Abstract: An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.

Abstract: A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

Abstract: An apparatus for testing a subsystem of a plurality of subsystems capable of being assembled to form an integrated system may include an integration stand for testing the subsystem without actual physical assembly of the plurality of subsystems which form the integrated system. The integration stand may include an interface to connect the subsystem to the integration stand for testing. The integration stand may also include a network device for connecting the integration stand to a communications network for communications between the subsystem and any other subsystems of the plurality of subsystems available via the network. In this way, the subsystem and the other subsystems may be virtually assembled and integrated to virtually form the integrated system for interoperability of the subsystems and testing without actual physical assembly of the plurality of subsystems.

Abstract: A method for generating an electronic quality record of a manufacturing operation that may involve generating inputs from a plurality of information sources located within a manufacturing environment. The plurality of information sources may provide information pertaining to at least a tool being used, an individual using the tool, and an operation that the tool is being used by the individual to perform. A locating system may be used that is in communication with the plurality of information sources to monitor a location and an operation of the tool. A processor may be in communication with the locating system to receive the generated inputs and to generate an electronic record upon completion of the operation that the tool is being used by the individual to perform. The electronic record may identify that the operation has been performed by the individual using the tool in accordance with a predefined standard.

Abstract: A drill template includes a vacuum housing with a skirt having a CAD-formed contact surface formed to an exact fit with a mold line surface of a structure. The drill template includes at least one drill guide bushing extending through the vacuum housing from a top surface to an interior surface of the vacuum housing; a vacuum port integral to the vacuum housing; and at least one index hole for positioning and aligning the vacuum housing on the structure. Index holes extend from the top surface through to the CAD-formed contact surface of the vacuum housing. A CAD-formed edge of part locator is formed according to a CAD solid model of the aircraft fuselage and fits to a precise location of the structure for precisely positioning the template on the structure. A vacuum port provides vacuum to the interior of the vacuum housing for removing drilling debris and dust.

Abstract: A method of forming titanium structures, and more specifically, a method of superplastically continuous roll forming titanium structures are disclosed herein. In one embodiment, a method of forming a shape in an article comprising titanium, the method including, among other things, providing first and second rolling members, the first rolling members being conductive and the second rolling members being continuous roll shaping members; contacting the article with the first rolling members to transfer a current to the article to heat the article to a temperature suitable for superplastic forming; and with the article being in a superplastic state, contacting the article with the second rolling members to form the shape in the article.

Abstract: An apparatus for testing a subsystem of a plurality of subsystems capable of being assembled to form an integrated system may include an integration stand for testing the subsystem without actual physical assembly of the plurality of subsystems which form the integrated system. The integration stand may include an interface to connect the subsystem to the integration stand for testing. The integration stand may also include a network device for connecting the integration stand to a communications network for communications between the subsystem and any other subsystems of the plurality of subsystems available via the network. In this way, the subsystem and the other subsystems may be virtually assembled and integrated to virtually form the integrated system for interoperability of the subsystems and testing without actual physical assembly of the plurality of subsystems.

Abstract: A system and method for generating a real time electronic quality record of an assembly, test, and repair or maintenance operation. The method involves generating inputs from a plurality of information sources located within a manufacturing environment, the information sources providing information pertaining to at least a tool being used, an individual using the tool, and an operation that the tool is being used by the individual to perform. A locating system is in communication with the information sources to monitor a location and an operation of the tool. A processor is in communication with the locating system to receive the generated inputs, and to generate a real time electronic record upon completion of the operation that the tool is being used to perform. The electronic record shows that the operation has been performed by a given individual using the tool in accordance with a predefined standard.

Abstract: An adjustable drill template has a base plate and a plurality of drill blocks. The drill blocks are movably coupled to the base plate. The drill blocks can move along the length of the base plate so that the drill blocks can be configured to conform to a desired hole pattern. A locking device coupled to each drill block will hold each drill block in a desired position.

Abstract: A drill template includes a vacuum housing with a skirt having a CAD-formed contact surface formed to an exact fit with a mold line surface of a structure. The drill template includes at least one drill guide bushing extending through the vacuum housing from a top surface to an interior surface of the vacuum housing; a vacuum port integral to the vacuum housing; and at least one index hole for positioning and aligning the vacuum housing on the structure. Index holes extend from the top surface through to the CAD-formed contact surface of the vacuum housing. A CAD-formed edge of part locator is formed according to a CAD solid model of the aircraft fuselage and fits to a precise location of the structure for precisely positioning the template on the structure. A vacuum port provides vacuum to the interior of the vacuum housing for removing drilling debris and dust.