An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

A rotational device which finds application as a kinetic sculpture, a record stabilizer, an air agitator or an impeller comprises a helical curved member having a first elongate helical portion defining a first helix of first radius about a first axis and a second elongate helical portion of opposing handedness defining a second helix of a second radius, smaller than the first radius, about a second axis, and a proximal intermediate portion linking a first or lower end of the first helical portion and a proximal first or lower end of the second helical portion, wherein the second helical portion defines an internal cylindrical volume that is unoccupied and absent any central shafts or struts, a rotational support base or apparatus for facilitating rotation of the helical curved member and a mounting arrangement for mounting the helical curved member to the rotational support base or apparatus.

The subject matter of this specification can be embodied in, among other things, an actuator that includes a worm drive assembly having a worm shaft, and a worm wheel configured as a ring having a radially outer perimeter comprising a first collection of gear teeth extending radially outward from the radially outer perimeter and at least partly engaged with the worm shaft, and a coaxial radially inner perimeter comprising a second collection of gear teeth extending radially inward from the inner perimeter, and an epicyclic gear assembly having a sun gear and a planet gear engaged with the sun gear and the second collection of gear teeth.

An alternating clockwise and counterclockwise helicoid cell structure for use in acoustic panels. The cell structure geometry may be easily replicated and tiled using additive manufacturing. The cell structure has at least an outer cavity and an inner cavity. The cavities are coaxial, share the same height, same entrance side, and same cell structure floor. The inner cavity includes a number of equal-volume inner chambers rotated uniformly in a first direction around the shared central axis; and the outer cavity includes a second number of equal-volume outer chambers rotated uniformly in an opposite direction to the first direction around the shared central axis. In various embodiments, one or more perforated baffles may extend, internally, across a chamber, perpendicular to direction of sound waves at the location of the perforated baffle. In various embodiments, one or more port openings from the outer cavity to the inner cavity may be present.

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

A pneumatic engine, comprising: a rotating outer ring (1), an intermediate shaft (2), a direct drive power core (3), and left and right baffles (4) and (5) where the rotating outer ring (1), the direct drive power core (3), and the left and right baffles (4) and (5) are coaxially provided on the intermediate shaft (2), the rotating outer ring (1) is integrally connected to the left and right baffles (4) and (5) to engage with the intermediate shaft (2) via a bearing, and a closed space is formed, the intermediate shaft (2) is provided with a master air inlet (21) and a master air outlet (22), the direct drive power core (3) is provided with a logarithmic spiral line runner, multiple drive grooves (11) are provided on an inner ring surface of the rotating outer ring (1). The pneumatic engine has a simple structure, high transmission efficiency and strong endurance.

A fan cover is configured to be mounted on a housing of a fan module. The fan cover includes a frame having an opening formed therein, a central hub positioned within the opening of the frame, and a plurality of spiral-shaped air guidance members that extend from the central hub to the frame. Gaps between the spiral-shaped air guidance members of the plurality of spiral-shaped air guidance members enable air to flow from the fan module through the fan cover. Each spiral-shaped air guidance member is configured to extend perpendicularly from the central hub and curve towards the frame at an angle with respect to the opening of the frame. Each spiral-shaped air guidance member further has a plurality of openings formed therein to facilitate air flow.

Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L), wherein a proximal surface of the outer axially extending member comprising a plurality of helical grooves. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.