Abstract: A turbine airfoil used in a gas turbine engine, the airfoil including an internal cooling air circuit that includes two nested and parallel serpentine flow circuits that both flow in the airfoil aft direction. The first and second legs of the two nested serpentine circuits are separated by ribs so that the cooling air flows do not mix. The last leg of the two nested serpentine circuits is separated by a rib which includes a plurality of cross-over holes so that the flows can mix. The aft-most serpentine flow circuit of the two nested circuits includes a last leg that is connected to cooling slots spaced along the trailing edge of the airfoil such that cooling air from the last leg flows out the ducts. The forward-most serpentine circuit of the two nested circuits includes a blade tip channel extending along the blade tip and connecting the first leg with the second leg, the blade tip channel including a plurality of blade tip cooling holes.

Abstract: A turbine rotor blade for use in a gas turbine engine, the blade including a serpentine flow cooling circuit that includes a first leg forming a leading edge cooling channel, a second leg that includes an upper channel with trip strips and a lower portion with near wall cooling channels that split off from the upper portion of the second leg to form near wall cooling channels extending along the pressure side and the suction side of the blade, the near wall cooling channels being separated by a dead cavity, and a third leg formed along the trailing edge of the blade with a collecting cavity formed in the blade root and providing the fluid communication between the trailing edge third leg and the near wall cooling channels. The trailing edge channel is connected to a plurality of metering and diffusion holes spaced along the trailing edge. These exit holes include a metering hole, a first diffusion hole, and a diffusion slot located on the pressure side of the trailing edge of the blade.

Abstract: A method for assembling a gas or steam turbine is provided. The method includes providing an insulator and positioning the insulator between a vane support and a vane such that the insulator facilitates preventing hot gas migration into the vane, and such that during operation, hot gas is channeled from a high pressure side of the vane to a low pressure side of the vane. A vane assembly for a turbine rotor assembly is also provided. The vane assembly includes a vane support and an insulator including a projecting portion. The assembly also includes a vane. The insulator is coupled to the vane support such that the projecting portion is between the vane and a nozzle support strut to facilitate hot gas flow from a pressure side of the projecting portion to a suction side of the projecting portion.

Abstract: A blade outer air seal is provided with a plurality of distinct cooling circuit schemes. Preferably, compact heat exchanger structures are utilized, and can be individually tailored to the particular location along the blade outer air seal. As an example, a greater pressure ratio exists between the products of combustion and the cooling air at the trailing edge than would be found at the leading edge. The present invention takes advantage of this distinction by utilizing cooling schemes that have a greater pressure drop at the trailing edge than the cooling schemes utilized closer to the leading edge.

Abstract: A wind driven power system employing multiple arms adapted to rotate about a central structure, each arm having a series of panels pivotally connected thereto and adapted to open and close as the system rotates to perpetuate the rotational movement and to produce energy.

Abstract: Aspects of the invention are directed to a system for improving engine performance by reducing vane tip clearances in the compressor section of a turbine engine. According to aspects of the invention, an abrasive material can be attached to a rotor disc. Thus, if a vane tip contacts the rotor disc during engine operation, the vane tip is worn away by the abrasive material. The system can reduce the risk of substantial component damage resulting from a vane tip rubbing event. The abrasive material can be provided in the form of an insert that can be removably attached to the rotor disc. Thus, the insert can be readily removed and replaced when necessary.

Abstract: A turbine blade having a squealer tip includes a trailing edge tip rail formed as an extension of the pressure side tip rail and the suction side tip rail. Positioned along the trailing edge tip rail is a pressure side vortex pocket and a suction side vortex pocket, and a plurality of angled cooling holes opening onto the tip cap adjacent to the vortex pockets, the holes being angled away from the vortex pockets. A row of film cooling holes on the pressure side wall and angled upward forces the hot gas flow up and over the blade pressure side edge and into a tip rail channel. Vortex flow is developed in both the vortex pockets, and with the addition of the angled cooling holes and pressure side wall cooling holes the trailing edge tip rail provides improved sealing and cooling for the blade tip.

Abstract: An apparatus for a gas turbine engine includes an airfoil defining a leading edge and a trailing edge, a root located adjacent to the airfoil, a vapor cooling system, and a film cooling system for cooling the airfoil in conjunction with the vapor cooling system. The vapor cooling system includes a vaporization section located within the airfoil and a condenser section located within the root.