Abstract: A gas turbine nozzle guide vane structure includes a vane shaped as an airfoil and having a vane trailing edge, an endwall including an opening to receive an end of the vane, and an element securing the endwall and the vane to each other. Clearance remaining between the endwall and the vane defines a plenum to feed cooling air to the vane at a location adjacent the vane trailing edge. Certain arrangements may have a purge groove defined in at least one of the endwall and the vane and located between the endwall and the vane to receive cooling fluid supplied. In certain arrangements, the structure may include a cover sheet on the endwall defining a gap with the vane, the purge groove configured to receive cooling fluid that exits through the gap.

Abstract: Airfoils and methods of cooling an airfoil are provided. The airfoil may comprise a spar; a coversheet on the spar; and a dual feed circuit between the spar and the coversheet. The dual feed circuit may include a first dam, a second dam spaced apart from the first dam along the chord axis of the spar, a first inlet disposed adjacent to the first dam, a second inlet disposed adjacent to the second dam, a circuit outlet disposed between the first inlet and the second inlet, and a plurality of diamond and/or hexagonal pedestals disposed on an outer surface of the spar. The diamond and/or hexagonal pedestals may form a plurality of cooling channels between the first inlet, the second inlet, and the circuit outlet. There may be no other circuit inlets are located between the first inlet and the second inlet.

Abstract: A gas turbine nozzle guide vane structure includes a vane shaped as an airfoil and having a vane trailing edge, an endwall including an opening to receive an end of the vane, and an element securing the endwall and the vane to each other. Clearance remaining between the endwall and the vane defines a plenum to feed cooling air to the vane at a location adjacent the vane trailing edge. Certain arrangements may have a purge groove defined in at least one of the endwall and the vane and located between the endwall and the vane to receive cooling fluid supplied. In certain arrangements, the structure may include a cover sheet on the endwall defining a gap with the vane, the purge groove configured to receive cooling fluid that exits through the gap.

Abstract: A dual-wall airfoil comprises a spar including pressure and suction side walls with raised features on outer surfaces thereof. A pressure side coversheet has an inner surface in contact with the raised features on the outer surface of the pressure side wall so as to define pressure side flow pathways between the pressure side wall and the pressure side coversheet, and a suction side coversheet has an inner surface in contact with the raised features on the outer surface of the suction side wall so as to define suction side flow pathways between the suction side wall and the suction side coversheet. The raised features on the outer surface of the pressure and/or suction side wall include an arrangement of pedestals, where each pedestal comprises an aspect ratio in a range from about 1:1 to about 5:1. The aspect ratio of the pedestals is varied within the arrangement.

Abstract: Airfoils and methods of cooling an airfoil are provided. The airfoil may comprise a spar; a coversheet on the spar; and a dual feed circuit between the spar and the coversheet. The dual feed circuit may include a first dam, a second dam spaced apart from the first dam along the chord axis of the spar, a first inlet disposed adjacent to the first dam, a second inlet disposed adjacent to the second dam, a circuit outlet disposed between the first inlet and the second inlet, and a plurality of diamond and/or hexagonal pedestals disposed on an outer surface of the spar. The diamond and/or hexagonal pedestals may form a plurality of cooling channels between the first inlet, the second inlet, and the circuit outlet. There may be no other circuit inlets are located between the first inlet and the second inlet.

Abstract: An endwall may be disposed at one end of a vane assembly. The endwall may comprise an endwall spar and a coversheet on the hot surface of the endwall spar. The endwall may further comprise a cooling fluid channel between the hot surface of the endwall spar and the cold surface of the coversheet. The cooling fluid channel may include a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The cooling fluid outlet may be formed at an angle with the axis of the endwall spar. A plurality of pedestals may be disposed on the hot surface of the endwall spar extending into the cooling channel. The pedestals may be formed at an angle with the axis of the endwall spar to direct a cooling fluid.

Abstract: An endwall assembly disposed at one end of a vane assembly may comprise an endwall spar that includes an cold side, an hot side, a leading edge, a trailing edge, and an axis extending from the leading edge to the trailing edge perpendicular to the leading edge. The endwall assembly may include a coversheet on the hot side of the endwall spar and a cooling channel that includes a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The endwall assembly may include a structure protruding from the cold side of the endwall spar, wherein the structure is located between the cooling fluid inlet and the cooling fluid outlet along the axis; and a cooling fluid source cavity on the cold side of the wall, the cooling fluid source cavity in fluid communication with the cooling fluid channel via the cooling fluid inlet.

Abstract: Apparatus and systems for a cooled gas turbine engine flowpath component are disclosed. In some embodiments, the flowpath component includes a spar and a coversheet. The spar may include a suction-side wall extending from a leading edge to a trailing edge and a pressure-side wall extending from the leading edge to the trailing edge, each wall having an outer surface. The coversheet may be positioned on the spar to at least partially enclose the spar, the coversheet having an engagement surface positioned to face the outer surface of the suction-side wall and the outer surface of the pressure-side wall. The spar and the coversheet cooperate to form a number of passageways configured to cool the flowpath component.

Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique cooled gas turbine engine flowpath component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and cooled gas turbine engine flowpath components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A disposable absorbent article having a transverse partition. The transverse partition is upstanding from the topsheet and presents an abrupt discontinuity out of the plane of the disposable absorbent article and obstructs fecal material deposited in the rear portion of the disposable absorbent article from migrating to the front portion of the disposable absorbent article. This obstruction minimizes soiling of the genitalia of the wearer. The disposable absorbent article may have upstanding barrier leg cuffs. The transverse partition may connect the barrier leg cuffs to form an H-shape.

Abstract: A method and apparatus for making stretchable absorbent diaper articles. An absorbent material is provided and entangled with a stretchable material to form a stretchable network incorporating the absorbent material. In one embodiment a plurality of foam absorbent material particulates are drawn or accelerated by gravity, vacuum or forced air through a stream of a meltblown adhesive that contacts and entangles the particulates and forms a stretchable network incorporating the particulates.