Abstract: Integrated circuit structures having uniform grid metal gate and trench contact cut, and methods of fabricating integrated circuit structures having uniform grid metal gate and trench contact cut, are described. For example, an integrated circuit structure includes a vertical stack of horizontal nanowires. A gate electrode is over the vertical stack of horizontal nanowires. A conductive trench contact is adjacent to the gate electrode. A dielectric sidewall spacer is between the gate electrode and the conductive trench contact. A first dielectric cut plug structure extends through the gate electrode, through the dielectric sidewall spacer, and through the conductive trench contact. A second dielectric cut plug structure extends through the gate electrode, through the dielectric sidewall spacer, and through the conductive trench contact, the second dielectric cut plug structure laterally spaced apart from and parallel with the first dielectric cut plug structure.

Abstract: A static seal includes first and second spaced apart walls having a gap therebetween for channeling a pressurized fluid. The first wall includes a recessed seat facing the second wall defined by spaced apart first and second faces joined together at a base. A seal insert is loosely disposed in the seat and is trapped therein by the first and second faces. The first and second faces are shorter than the insert to project a top of the insert above the seat and below the second wall for initially promoting flow of the fluid over the insert top to deploy the insert in abutting contact with both the second face and the second wall to seal the gap.

Abstract: A variable area turbine nozzle includes a plurality of circumferentially adjoining nozzle segments. Each nozzle segment includes outer and inner bands, with a plurality of first vane segments fixedly joined therebetween. A plurality of second vane segments adjoin respective ones of the first vane segments to define therewith corresponding vanes which are spaced apart to define respective throats of minimum flow area for channeling therethrough combustion gas. The second vane segments are pivotable to selectively vary the throat area.

Abstract: A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with an integrally formed double shell outer wall surrounding at least one radially extending cavity. The inner and the outer shells are integrally formed of the same material together with tying elements which space apart the shells and mechanically and thermally tie the shells together. The present invention contemplates tying elements including pedestals, rods, and/or continuous or intermittent ribs. Impingement cooling means for the outer shell, in the form of impingement cooling holes, is provided on the inner shell to direct the coolant in impingement jet arrays against the outer shell, thereby, cooling the outer shell.

Abstract: Sheet Metal thermal control dampers are disposed in the cavities between turbine blades to bear against the undersides of opposed blade platforms portions of angularly adjacent blades under centrifugal loading to dampen blade vibrations and to seal the gaps between platforms against the radial flow of working fluid into the interblade cavities. The dampers are configured to cooperate with forward and aft seals to also block the axial flow of working fluid through the interblade cavities. Holes are provided in the dampers through which cooling air introduced into the interblade cavities can flow into contact with the platform undersides and cool the platforms, thereby controlling temperature rise in the blade attachment structure.

Abstract: A heat exchanger for cooling turbine components of a gas turbofan engine in which air to be cooled is directed along a first annular, radially extending path away from the engine and cooled by bypass air. The cooled air is returned to the engine along a second radially-extending path concentric to the first path. In a preferred embodiment, the heat exchanger is a standpipe extending from the compressor outlet to the bypass air duct and includes inner and outer tubular members oriented concentrically to form inner and outer counterflowing air flow paths which also are concentrically arranged. The outer member is mounted on the combustor casing and the inner member on a diffuser within the casing. Accordingly, no mechanical connection exists between the inner and outer members.