Abstract: A method for cooling components of a gas turbine engine, having first and second sets of components that require cooling, includes removing thermal energy from cooling air, directing the cooling air from which thermal energy has been removed to the first set of components of the gas turbine engine, and transferring thermal energy away from the second set of components of the gas turbine engine using a vaporization cycle of a vapor cooling assembly. Use of the vaporization cycle offsets thermal energy removed from the cooling air.

Abstract: An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components.

Abstract: A method for cooling components of a gas turbine engine, having first and second sets of components that require cooling, includes removing thermal energy from cooling air, directing the cooling air from which thermal energy has been removed to the first set of components of the gas turbine engine, and transferring thermal energy away from the second set of components of the gas turbine engine using a vaporization cycle of a vapor cooling assembly. Use of the vaporization cycle offsets thermal energy removed from the cooling air.

Abstract: A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component.

Abstract: An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a plurality of compressor blades and a plurality of turbine blades attached thereto. One of the spools has a first set of fan blades attached thereto. The engine further has a variable bypass turbine fan formed by a second set of fan blades. The second set of fan blades is arranged outboard of the main core. The second set of fan blades may be decoupled from the first set of fan blades.

Abstract: An engine timing input system is described for pulse detonation engines that allows for accurate engine timing when rotary or cylindrical valves are used to distribute an air/fuel mixture for combustion. The invention uses a profile disk having a predetermined circumferential edge corresponding to valve position to provide for accurate engine timing. A frequency wheel is used in conjunction with the profile disk to provide a more accurate representation of valve position by partitioning the valve position into multiple pulses during each rotation of the rotary or cylindrical valve. The profile disk and frequency wheel when used with programmable timing circuitry signal fuel valve timing and ignition relative to the rotating valve.

Abstract: An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components.

Abstract: An engine timing input system is described for pulse detonation engines that allows for accurate engine timing when rotary or cylindrical valves are used to distribute an air/fuel mixture for combustion. The invention uses a profile disk having a predetermined circumferential edge corresponding to valve position to provide for accurate engine timing. A frequency wheel is used in conjunction with the profile disk to provide a more accurate representation of valve position by partitioning the valve position into multiple pulses during each rotation of the rotary or cylindrical valve. The profile disk and frequency wheel when used with programmable timing circuitry signal fuel valve timing and ignition relative to the rotating valve.

Abstract: An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components.

Abstract: An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a plurality of compressor blades and a plurality of turbine blades attached thereto. One of the spools has a first set of fan blades attached thereto. The engine further has a variable bypass turbine fan formed by a second set of fan blades. The second set of fan blades is arranged outboard of the main core. The second set of fan blades may be decoupled from the first set of fan blades.

Abstract: A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component.

Abstract: An integrated additive manufacturing cell (IAMC) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components.