An airfoil for a turbine engine includes an array of pins positioned in an internal cavity of the airfoil, such that cooling channels are defined in the interspaces between adjacent pins. Each pin extends lengthwise from a first airfoil wall to a second airfoil wall and is connected thereto at a first intersection and at a second intersection respectively. The pin has a first cross-sectional shape at a respective intersection and a second cross-sectional shape at an intermediate plane located between the first and second intersections. The first cross-sectional shape includes a closed shape defined by relatively sharp corners and the second cross-sectional shape includes a closed shape defined by relatively rounded corners. A cross-sectional area of the pin at the intermediate plane is greater than a cross-sectional area of the pin at the respective intersection.

A face skin for an acoustic panel may comprise a sheet defining a first surface and a second surface. A plurality of slots may be formed through the face skin using abrasive blasting. Each slot of the plurality of slots may comprise a first semi-circular wall and a second semi-circular wall opposite the first semi-circular wall.

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a gas turbine engine component that has a first interface portion, and a support that has a mounting portion and a second interface portion, the mounting portion attachable to an engine static structure, a first retention feature that releasably secures the first interface portion to the support in a first installed position of the gas turbine engine component, and a second retention feature dimensioned to secure the first interface portion to the second interface portion in a second installed position of the gas turbine engine component. The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine is also disclosed.

A rotor blade of a turbomachine includes an airfoil. The airfoil includes a root and a tip which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The pressure side surface and the suction side surface are continuous about the trailing edge and collectively define an arc centered on the trailing edge. The arc has a semi-major axis and a semi-minor axis. The semi-major axis and the semi-minor axis of the arc define an axis ratio, and the axis ratio varies over the span of the airfoil.

A pogo effect corrector system for a liquid propellant feed system of a rocket engine includes a liquid propellant feed pipe portion, and a hydraulic accumulator including a tank connected firstly to the feed pipe portion firstly via at least one take-off passage opening out into a take-off segment of the feed pipe portion, and secondly via at least one rejection passage opening out into the tank at an intermediate level lying between the at least one take-off passage and the top of the tank, wherein the feed pipe portion possesses a constriction segment where the flow section of the feed pipeline portion is less than the flow section of the take-off segment, and wherein at least one rejection passage opens out into the feed pipeline portion in the constriction segment.

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

A compressor rotor of a turbomachine includes a rotor disk; a rotor hub forming or connected to a radially outer edge of the rotor disk; and a plurality of rotor blades on the rotor hub extending radially outwards. The rotor hub includes an axially frontal leading edge, an axially rear trailing edge, a top side, a frontal bottom side extending on a bottom side of the rotor hub from the leading edge in a direction of the rotor disk and transitioning into same, and a rear bottom side extending on the bottom side from the trailing edge in the direction of the rotor disk and transitioning into same. The frontal bottom side and/or the rear bottom side of the hub is contoured in a circumferential direction of the rotor hub to form respectively one indentation in an area below a rotor blade.

A centrifugal compressor includes: an impeller; a compressor inlet tube configured to guide air to the impeller; a scroll flow passage disposed on a radially outer side of the impeller; a bypass flow passage branching from the scroll flow passage via a branch port, the bypass flow passage connecting to the compressor inlet tube not via the impeller; and a bypass valve capable of opening and closing a valve port disposed in the bypass flow passage. The branch port has a non-circular shape when viewed along a normal N1 of the branch port passing through a center of the branch port.

A turbine vane of a multi-stage arrangement of turbine vanes cooled by compressed air supplied from a compressor of a gas turbine has an improved structure capable of preventing an unintended removal of cooling holes along with the intended removal of an excess portion of a shroud. The turbine vane includes an airfoil configured to be installed on an inner peripheral surface of a turbine casing in which combustion gas supplied from a combustor flows and to guide combustion gas from a front-stage blade to a rear-stage blade; and a pair of shrouds coupled to the airfoil, at least one of the shrouds having a plurality of cooling holes formed toward the airfoil, wherein the plurality of cooling holes are formed along an imaginary line that is spaced apart from and surrounds the airfoil.

A ceiling fan or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The blade can include a body having an outer surface with a flat top surface and a flat bottom surface, and a side edge. A curved transition can extend between one of the flat top surface or the flat bottom surface, and the side edge. The curved transition can include an elliptical curvature.