A unit cell (26) for use in a damping system (24) includes: an impacting structure (34); a cavity (32) encapsulating the impacting structure (34), the cavity (32) including a first hemisphere (32A) and a second hemisphere (32B), the cavity (32) disposed within a substrate (28), the substrate (28) forming an outer casing of the cavity (32); and at least one fluid (36) disposed in each of the first and second hemispheres (32A, 32B) between the impacting structure (34) and the outer casing (28).

A turbine housing includes: a scroll section configured to internally define a spiral space; a cylindrical exhaust gas introduction section having an exhaust gas introduction port and configured to internally define a connection passage connecting the exhaust gas introduction port and the spiral space; a sheet metal inner scroll member disposed in the spiral space to form a first heat-shielding space between the inner scroll member and an inner surface of the scroll section and configured to internally define a spiral flow passage through which exhaust gas entering through the exhaust gas introduction port flows; and a sheet metal inlet member separate from the inner scroll member, disposed in the connection passage to form a second heat-shielding space between the inlet member and an inner surface of the exhaust gas introduction section, and configured to internally define a connection flow passage connecting the exhaust gas introduction port and the spiral flow passage. An upstream end portion of the inner scroll member and a downstream end portion of the inlet member overlap along an axial direction of the exhaust gas introduction section.

A fan assembly in which all of the major structural components of the assembly are mechanically fastened together by non-welding means, such as mechanical fasteners, is disclosed. The disclosure also relates to a fan assembly in which the major structural components have planar segments separated by bend lines that approximate a curved shape, and that can be formed, for example, by a press brake machine. Such a construction can eliminate the necessity for rolling, welding, and painting of the structural components of the fan assembly.

A fixed vane turbocharger includes: an impeller; a housing including, inside thereof, an impeller housing space which accommodates the impeller, a scroll flow passage formed on a radially outer side of the impeller, and a communication flow passage which brings the impeller housing space and the scroll flow passage into communication; and at least one fixed vane unit disposed in the communication flow passage and fixed to a portion of the housing on an inner side of the scroll flow passage with respect to a radial direction of the impeller. Each of the at least one fixed vane unit includes at least two vane portions and a coupling portion coupling the two vane portions, and is formed of a single sheet metal member.

A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.

A turbocharger includes a turbine housing that is a cast component, a turbine scroll passage, a discharge port, and a discharge port defining member. The turbine scroll passage surrounds the circumference of a turbine chamber defined in the turbine housing and the circumference of the turbine chamber. Exhaust gas that has passed through the turbine chamber is conducted to the discharge port. The discharge port defining member constitutes a wall surface of the discharge port. The discharge port defining member includes a tubular main body wall and an outer circumferential edge. The main body wall constitutes a wall surface of the discharge port. The outer circumferential edge extends from the distal end of the main body wall and outward in the radial direction of the impeller shaft. The outer circumferential edge is fixed between the turbine housing and a downstream exhaust pipe, which is connected to the discharge port.

A rotor blade is provided for a turbine engine. This rotor blade includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise to a tip. The airfoil is configured with a plurality of projections arranged longitudinally along the tip.

A highly adaptive seal for use in advanced aircraft propulsion and missile systems is provided. The seal is capable of effectively limiting invasive thermal energy and corrosive airflow from entering the internal systems and hardware of the aircraft by managing and controlling the incoming air flow. The seal is configured to be disposed between component parts of the aircraft and create a tortuous path for air flow. The seal maintains contact with the component parts between which it seals by allowing for significant radial and axial displacement freedom of the component parts. Accordingly, hot gas intrusion may be limited in a wide variety of dynamic environments and component displacement conditions. Limiting such hot gas intrusion has a substantial impact on component survivability over the course of free flight of an aircraft.

Systems and methods for a turbo blanket. Specifically, embodiments are related to a flexible turbo blanket with an alloy layer, insulation layer, and mesh screen layer.

A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.