Abstract: Systems and methods for transformer cooling by vertical airflow are described. One embodiment of an air transfer unit includes an assembly frame that includes an interior portion and defines a lateral side, an upper side, and a lower side, where the assembly frame includes a length that is substantially the same as a width of a plurality of cooling fins on a transformer. Some embodiments include a plurality of air directing apparatuses that are positioned in the interior portion and are aligned along the length of the assembly frame, where the plurality of air directing apparatuses receive airflow from the lateral side and direct the airflow vertically through the upper side to further cool the plurality of cooling fins. Similarly, some embodiments include an exhaust screen that is coupled to the upper side, wherein the exhaust screen further consolidates the airflow vertically toward the plurality of cooling fins.

Abstract: Systems and methods for liquid heat exchange for transformers are described. One embodiment of a fluid heat exchanger includes a transformer inlet port that is coupled to a transformer chamber and receives a dielectric fluid from the transformer chamber. Also included are a cooling fluid inlet for receiving a cooling fluid and a finned heat sink that includes a fluid communicator. The fluid communicator may receive, at a first chamber, the dielectric fluid from the transformer inlet port and directs the dielectric fluid across a first plurality of cooling fins. The fluid communicator may receive, at a second chamber, the cooling fluid from the cooling fluid inlet and may direct the cooling fluid across a second plurality of fins, where the fluid communicator separates the first chamber from the second chamber with a solid divider.

Abstract: Systems and methods for transformer cooling by vertical airflow are described. One embodiment of an air transfer unit includes an assembly frame that includes an interior portion and defines a lateral side, an upper side, and a lower side, where the assembly frame includes a length that is substantially the same as a width of a plurality of cooling fins on a transformer. Some embodiments include a plurality of air directing apparatuses that are positioned in the interior portion and are aligned along the length of the assembly frame, where the plurality of air directing apparatuses receive airflow from the lateral side and direct the airflow vertically through the upper side to further cool the plurality of cooling fins. Similarly, some embodiments include an exhaust screen that is coupled to the upper side, wherein the exhaust screen further consolidates the airflow vertically toward the plurality of cooling fins.

Abstract: Systems and methods for liquid heat exchange for transformers are described. One embodiment of a fluid heat exchanger includes a transformer inlet port that is coupled to a transformer chamber and receives a dielectric fluid from the transformer chamber. Also included are a cooling fluid inlet for receiving a cooling fluid and a finned heat sink that includes a fluid communicator. The fluid communicator may receive, at a first chamber, the dielectric fluid from the transformer inlet port and directs the dielectric fluid across a first plurality of cooling fins. The fluid communicator may receive, at a second chamber, the cooling fluid from the cooling fluid inlet and may direct the cooling fluid across a second plurality of fins, where the fluid communicator separates the first chamber from the second chamber with a solid divider.

Abstract: A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.

Abstract: A method for orienting cooling holes of a nozzle singlet for a turbine engine is provided. The method includes providing a nozzle singlet having an inner band, an outer band, and at least one airfoil extending therebetween. The method also includes orienting at least one first row of cooling holes an angle with respect to at least one second row of cooling holes. The orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in the airfoil angle without reorienting the cooling hole pattern.

Abstract: A method for assembling a gas turbine engine is provided. The method includes providing a turbine nozzle including an outer band and an inner band, wherein each band includes a leading edge, a trailing edge, and a body extending therebetween. At least one of the outer band and the inner band has at least one radial tab extending outward therefrom. The method also includes coupling at least one seal between at least one of the radial tabs extending from the outer band and the inner band and a respective leading edge of the outer and inner band. The method also includes positioning at least one non-planar seal support against at least one portion of the seal.

Abstract: A method for orienting cooling holes of a nozzle singlet for a turbine engine is provided. The method includes providing a nozzle singlet having an inner band, an outer band, and at least one airfoil extending therebetween. The method also includes orienting at least one first row of cooling holes an angle with respect to at least one second row of cooling holes. The orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in the airfoil angle without reorienting the cooling hole pattern.