Abstract:
An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
Abstract:
A system including a magnet configured to move in response to a movement of a wear pin indicator of a brake assembly of a vehicle. A sensor is configured to generate position data corresponding to the magnet. The position data is indicative of a position and/or movement of the wear pin indicator. The system includes a thermoelectric generator configured to generate an electrical signal based on an operation of the brake assembly. The thermoelectric generator is configured to deliver at least a portion of the electrical signal to the sensor. The system includes a mounting bracket configured to mechanically couple a sensor housing to an actuator housing of the brake assembly. The mounting bracket is configured to provide heat to the thermoelectric generator when the mounting bracket mechanically couples the sensor housing and the actuator housing.
Abstract:
An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
Abstract:
An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.
Abstract:
A compressor comprising: a first compressor wheel comprising a first chamber configured to retain a medium, a first impeller disposed within the first chamber and configured to revolve around a longitudinal axis of the compressor, and a first diffuser coupled to the first chamber; and a second compressor wheel comprising a second chamber disposed radially outwards of the first chamber relative to the longitudinal axis, wherein the second chamber is configured to receive the outputted medium from the first chamber, a second impeller disposed within the second chamber and configured to revolve around the longitudinal axis of the compressor within the second chamber, and a second diffuser coupled to the second chamber, wherein each blade of the first impeller defines a fillet extending along an outer edge of the blade, and wherein a width of the fillet along a surface of the respective blade varies along the longitudinal axis.
Abstract:
An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.