Abstract: Processes for optimizing the geometry of a blade for use in a propeller are disclosed. In one exemplary process, an optimization routine that generates new blade geometries based on structural parameters and calculates performance parameters of each blade geometry, including aerodynamic performance parameters, farfield acoustic parameters, and/or electrical power requirements to operate a propeller having the blade geometry, is performed. The optimization routine receives design parameters and weightings from a user and can use one or more surrogate algorithms to map a design space of the weighted values of the design parameters to find their local minima. The optimization routine then determines an optimized blade geometry using a gradient-based algorithm to generate new blade geometries to explore the minima until the weighted values of the design parameters converge at an optimized blade geometry representing the global minima of the design space.

Abstract: A droplet heat exchange system is provided for that includes a heat exchange chamber, at least one injector, and at least one swirler. The chamber is configured to have gas flow through it. The injector can be configured to dispense liquid droplets into the chamber for thermal energy exchange with gas flowing through the chamber. The swirler can disposed within the chamber and can have a body configured to form a spiral gas flow that pushes liquid droplets from the injector, radially outward as gas flows across the body, thereby separating the liquid droplets from the gas flowing across the body and forming a liquid film along an inner wall of the chamber. The collector can be in fluid communication with the heat exchange chamber and configured to collect the liquid film after thermal energy exchange. The collector can be configured to direct at least some of the collected liquid film to the injector for subsequent use.

Abstract: Processes for optimizing the geometry of a blade for use in a propeller are disclosed. In one exemplary process, an optimization routine that generates new blade geometries based on structural parameters and calculates performance parameters of each blade geometry, including aerodynamic performance parameters, farfield acoustic parameters, and/or electrical power requirements to operate a propeller having the blade geometry, is performed. The optimization routine receives design parameters and weightings from a user and can use one or more surrogate algorithms to map a design space of the weighted values of the design parameters to find their local minima. The optimization routine then determines an optimized blade geometry using a gradient-based algorithm to generate new blade geometries to explore the minima until the weighted values of the design parameters converge at an optimized blade geometry representing the global minima of the design space.

Abstract: A droplet heat exchange system is provided for that includes a heat exchange chamber, at least one injector, and at least one swirler. The chamber is configured to have gas flow through it. The injector can be configured to dispense liquid droplets into the chamber for thermal energy exchange with gas flowing through the chamber. The swirler can disposed within the chamber and can have a body configured to form a spiral gas flow that pushes liquid droplets from the injector, radially outward as gas flows across the body, thereby separating the liquid droplets from the gas flowing across the body and forming a liquid film along an inner wall of the chamber. The collector can be in fluid communication with the heat exchange chamber and configured to collect the liquid film after thermal energy exchange. The collector can be configured to direct at least some of the collected liquid film to the injector for subsequent use.

Abstract: A droplet heat exchange system is provided for that includes a heat exchange chamber, at least one injector, and at least one swirler. The chamber is configured to have gas flow through it. The injector can be configured to dispense liquid droplets into the chamber for thermal energy exchange with gas flowing through the chamber. The swirler can disposed within the chamber and can have a body configured to form a spiral gas flow that pushes liquid droplets from the injector, radially outward as gas flows across the body, thereby separating the liquid droplets from the gas flowing across the body and forming a liquid film along an inner wall of the chamber. The collector can be in fluid communication with the heat exchange chamber and configured to collect the liquid film after thermal energy exchange. The collector can be configured to direct at least some of the collected liquid film to the injector for subsequent use.