Abstract: In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater.

Abstract: A machining process includes providing a cutting tool having a rake face and a flank face; bringing the cutting tool into contact with a metal alloy work piece to form a chip by penetrating the cutting tool into the workpiece; and introducing a nanofluid into a vicinity of the penetration to remove heat and, in some instances, customize the finished surface. The nanofluid includes a mixture of a cryo-liquid and nanoparticles having a maximum size of approximately 0.1 nanometers to approximately 100 nanometers.

Abstract: A multilayer structure for deicing an aircraft airfoil component includes an electrically and thermally insulating bottom layer formed in a defined pattern directly on the aircraft airfoil component, an electrothermal middle layer of electrically resistant heater element arrays formed in the defined pattern on the electrically and thermally insulating bottom layer, and a thermally conductive and electrically insulating top layer encapsulating the electrically and thermally insulating bottom layer and the electrothermal middle layer of electrically resistant heater element arrays. The multilayer structure may be directly applied to the airfoil component by direct writing/additive manufacturing, and may be done with the assistance of a multi-axis robot.

Abstract: An elevator car (20) comprises: a cab (24) having a top, a bottom, a left side, a right side, a front, and a back, the front having a door (50); and a frame (22) supporting the cab. The cab comprises a perimeter shroud (120; 320; 420; 620) protruding above a surface of the top and leaving a well (130) exposing a central portion of an upper surface (60) of the top; the perimeter shroud protrudes above the upper surface; and the perimeter shroud has, in vertical section, a curved portion.

Abstract: A machining process includes providing a cutting tool having a rake face and a flank face; bringing the cutting tool into contact with a metal alloy work piece to form a chip by penetrating the cutting tool into the workpiece; and introducing a nanofluid into a vicinity of the penetration to remove heat and, in some instances, customize the finished surface. The nanofluid includes a mixture of a cryo-liquid and nanoparticles having a maximum size of approximately 0.1 nanometers to approximately 100 nanometers.

Abstract: A multilayer structure for deicing an aircraft airfoil component includes an electrically and thermally insulating bottom layer formed in a defined pattern directly on the aircraft airfoil component, an electrothermal middle layer of electrically resistant heater element arrays formed in the defined pattern on the electrically and thermally insulating bottom layer, and a thermally conductive and electrically insulating top layer encapsulating the electrically and thermally insulating bottom layer and the electrothermal middle layer of electrically resistant heater element arrays. The multilayer structure may be directly applied to the airfoil component by direct writing/additive manufacturing, and may be done with the assistance of a multi-axis robot.

Abstract: An elevator car (20) comprises: a cab (24) having a top, a bottom, a left side, a right side, a front, and a back, the front having a door (50); and a frame (22) supporting the cab. The cab comprises a perimeter shroud (120; 320; 420; 620) protruding above a surface of the top and leaving a well (130) exposing a central portion of an upper surface (60) of the top; the perimeter shroud protrudes above the upper surface; and the perimeter shroud has, in vertical section, curved portion.

Abstract: A boundary layer control assembly for an aircraft airfoil includes a leading edge and a trailing edge spaced from the leading edge to form a chord length. The boundary layer control assembly also includes a heating element disposed proximate the leading edge to heat a boundary layer formed along the surface of the aircraft airfoil.

Abstract: In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater.

Abstract: A system for reducing compressor noise includes a rotor having a plurality of blades. The blades have a nominal geometry characterized by a blade parameter. At least some of the blades are mistuned, such that they differ from the nominal geometry by greater than a manufacturing tolerance in the blade parameter. The blades produce shock waves at a blade passing frequency, and the mistuned blades shift acoustic energy away from the blade passing frequency to multiple lower amplitude tones at other frequencies. The system is configurable to be deployed with an inlet silencer that preferentially absorbs acoustic energy at some of the shifted frequencies.

Abstract: A system for reducing compressor noise includes a rotor having a plurality of blades. The blades have a nominal geometry characterized by a blade parameter. At least some of the blades are mistuned, such that they differ from the nominal geometry by greater than a manufacturing tolerance in the blade parameter. The blades produce shock waves at a blade passing frequency, and the mistuned blades shift acoustic energy away from the blade passing frequency to multiple lower amplitude tones at other frequencies. The system is configurable to be deployed with an inlet silencer that preferentially absorbs acoustic energy at some of the shifted frequencies.

Abstract: A leading edge slat for multi-element rotor blade applications which provide multiple benefits and provide design direction which has heretofore been unexplored.