Abstract: A monolithic combustion liner for use in a gas turbine engine includes fuel channels integrated into the wall of the combustion liner. The integrated fuel channels can have an aerodynamic shape to reduce flow losses of cooling air flowing around the exterior of the combustion liner. The monolithic combustion liner allows more cooling air to flow around the combustion liner, increasing the cooling of the combustor region of the gas-turbine engine.

Abstract: During a formation method, a build plate is arranged within a build space. A first object is built onto the build plate within the build space using an additive manufacturing process. The object is fused to the build plate during the additive manufacturing process. At least the build plate is machined to form a component that includes a portion of the build plate and at least a portion of the first object.

Abstract: An assembly is provided for an aerial vehicle. This assembly includes an airframe and a fluid circuit. The airframe includes a body and an airfoil projecting out from the body. The airfoil includes a first surface and a first aperture in the first surface. The fluid circuit is configured to bleed gas from a gas turbine engine mounted to the airframe to provide control gas. The fluid circuit is configured to selectively direct the control gas to the first aperture.

Abstract: An assembly is provided for a gas turbine engine. This assembly includes a compressor rotor, a turbine rotor and a cooling circuit. The compressor rotor includes a gas path surface. The turbine rotor is rotatable with the compressor rotor about a rotational axis. The cooling circuit includes an inlet in the gas path surface. The cooling circuit extends from the inlet, through the compressor rotor and into the turbine rotor.

Abstract: An engine system is provided that includes a gas turbine engine and an actuation system. The gas turbine engine includes a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The actuation system includes a fluid reservoir, a flow regulator and a flow circuit. The flow regulator is configured as or otherwise includes a barrier between the fluid reservoir and the flow circuit. The flow regulator is configured to fluidly decouple the fluid reservoir from the flow circuit when the barrier is intact. The flow regulator is configured to fluidly couple the fluid reservoir with the flow circuit when the barrier breaks. The flow circuit is configured to direct gas from the fluid reservoir into the flowpath when the barrier breaks.

Abstract: A manufacturing method is provided during which a body is additively manufactured. The body includes an engine case for a gas turbine engine, a support structure and an aperture. The support structure projects out from the engine case. The support structure includes a lattice, a wall and an internal volume. The wall surrounds the lattice. The internal volume is within the support structure along the lattice. The internal volume is filled with powder. The aperture is at an intersection between the engine case and the support structure. The powder is extracted from the internal volume through the aperture.

Abstract: A system is provided for an aerial vehicle. This system includes a splash plate, a fuel nozzle and a gas circuit. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface. The gas circuit includes a gas passage and a gas outlet. At least a portion of the gas passage is formed by and embedded within the splash plate. The gas passage extends through the splash plate to the gas outlet.

Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

Abstract: An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector receptacle. The injector receptacle extends longitudinally through the engine structure along a centerline. The fuel injector is received by the injector receptacle. The fuel injector includes a fuel nozzle and a splash plate. The fuel nozzle is configured to direct fuel out of the fuel injector to impinge against the splash plate.

Abstract: An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector aperture and a fuel supply passage. The injector aperture extends longitudinally through the engine structure along a centerline. The fuel supply passage extends laterally within the engine structure to the injector aperture. The fuel injector is mated with the injector aperture. The fuel injector includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along the centerline within the fuel injector to the nozzle orifice. The nozzle passage is fluidly coupled with the fuel supply passage.

Abstract: A system is provided for an aerial vehicle. This system includes a splash plate, a fuel nozzle and a gas circuit. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface. The gas circuit includes a gas passage and a gas outlet. At least a portion of the gas passage is formed by and embedded within the splash plate. The gas passage extends through the splash plate to the gas outlet.

Abstract: A manufacturing method is provided during which a body is additively manufactured. The body includes an engine case for a gas turbine engine, a support structure and an aperture. The support structure projects out from the engine case. The support structure includes a lattice, a wall and an internal volume. The wall surrounds the lattice. The internal volume is within the support structure along the lattice. The internal volume is filled with powder. The aperture is at an intersection between the engine case and the support structure. The powder is extracted from the internal volume through the aperture.

Abstract: A gas turbine engine with a lubrication system includes a ball bearing assembly and a rotor circumscribing a rotational axis and journaled within the ball bearing assembly. The gas turbine engine also includes a lubrication system located radially outward from a rotational axis and radially outward and adjacent to the ball bearing assembly, which includes a lubrication channel having an inlet and an outlet and a dispersion cone adjacent to the outlet of the lubrication channel.

Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

Abstract: A manufacturing method is provided during which a body is additively manufactured. The body includes an engine case for a gas turbine engine, a support structure and an aperture. The support structure projects out from the engine case. The support structure includes a lattice, a wall and an internal volume. The wall surrounds the lattice. The internal volume is within the support structure along the lattice. The internal volume is filled with powder. The aperture is at an intersection between the engine case and the support structure. The powder is extracted from the internal volume through the aperture.

Abstract: An engine system is provided that includes a gas turbine engine and an actuation system. The gas turbine engine includes a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The actuation system includes a fluid reservoir, a flow regulator and a flow circuit. The flow regulator is configured as or otherwise includes a barrier between the fluid reservoir and the flow circuit. The flow regulator is configured to fluidly decouple the fluid reservoir from the flow circuit when the barrier is intact. The flow regulator is configured to fluidly couple the fluid reservoir with the flow circuit when the barrier breaks. The flow circuit is configured to direct gas from the fluid reservoir into the flowpath when the barrier breaks.

Abstract: An assembly is provided that includes a regulator manifold and a regulator element. The regulator manifold includes an inlet passage, a first outlet passage and a second outlet passage. The inlet passage is configured to receive bleed gas from a core flowpath. The regulator element is within the regulator manifold and configured to pivot to a first position, a second position and an intermediate position between the first position and the second position. The regulator element is configured to fluidly couple the inlet passage with the first outlet passage in the first position. The regulator element is configured to fluidly couple the inlet passage with the second outlet passage in the second position. The regulator element is configured to fluidly decouple the inlet passage from the first outlet passage and the second outlet passage in the intermediate position.

Abstract: An assembly is provided for an aerial vehicle. This assembly includes a vehicle body, a gas turbine engine and a support structure. The vehicle body includes a body section. The gas turbine engine includes a stationary structure. The gas turbine engine is housed within the vehicle body. The support structure extends between and is connected to the body section and the stationary structure. The support structure supports the gas turbine engine within the vehicle body. The body section, the stationary structure and the support structure are included in a monolithic body.

Abstract: An assembly is provided for an aerial vehicle. This assembly includes an airframe and a fluid circuit. The airframe includes a body and an airfoil projecting out from the body. The airfoil includes a first surface and a first aperture in the first surface. The fluid circuit is configured to bleed gas from a gas turbine engine mounted to the airframe to provide control gas. The fluid circuit is configured to selectively direct the control gas to the first aperture.

Abstract: A gas turbine engine with a lubrication system includes a ball bearing assembly and a rotor circumscribing a rotational axis and journaled within the ball bearing assembly. The gas turbine engine also includes a lubrication system located radially outward from a rotational axis and radially outward and adjacent to the ball bearing assembly, which includes a lubrication channel having an inlet and an outlet and a dispersion cone adjacent to the outlet of the lubrication channel.