Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.

Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.

Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400±10% Hz; a second mode resonance frequency is 4950±10% Hz; a third mode resonance frequency is 7800±10% Hz; a fourth mode resonance frequency is 8700±10% Hz; and a fifth mode resonance frequency is 12500±10% Hz.

Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

Abstract: A turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes are located in an airfoil of the turbine blade according to the coordinates of Table 1.

Abstract: A turbine blade for a gas turbine engine having an airfoil to platform fillet, wherein the fillet is contoured in accordance with the coordinates of Table 1.

Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.

Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

Abstract: An exemplary fuel cell device includes a cell stack assembly having a plurality of fuel cells. A vapor barrier tape is wrapped around at least a portion of an exterior of the cell stack assembly. An exemplary method of managing moisture within a fuel cell stack assembly includes covering at least a portion of an exterior of the cell stack assembly with a vapor barrier tape to thereby maintain moisture within the cell stack assembly.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and at least one rib that protrudes from the wall and extends to a rib end, the rib end having a curved transition portion near a location where the at least one rib meets the wall.

Abstract: A method of manufacturing a porous structure for a fuel cell is disclosed. The method includes providing the porous structure, and processing the porous structure to selectively produce a non-porous region on the porous structure. In one example, the non-porous region is provided at the perimeter of the porous structure, an edge of an internal manifold and/or a surface or recess that supports a seal or gasket. The non-porous region has a porosity that is less than the porosity of the porous structure. The non-porous region prevents undesired leakage of fluid from the porous structure and prevents migration of adhesive associated with the seals.

Abstract: Aspects of the disclosure are directed to a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face, where an aspect ratio between the first face and the second face ensures that the damper is installed in the cavity in accordance with a predetermined orientation.

Abstract: The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.

Abstract: A gas turbine engine blade includes a platform that has an inner side and an outer side, a root that extends outwardly from the inner side, and an airfoil that extends outwardly from a base at the outer side to a tip end. The airfoil includes a leading edge and a trailing edge and a first side wall and a second side wall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define one or more cavities in the airfoil. The airfoil has a span from the base to the tip end, with the base being at 0% of the span and the tip end being at 100% of the span. The first side wall includes an axial row of cooling holes at 90% or greater of the span.

Abstract: A fuel cell plate is provided that includes a flow field having a plurality of channels each with an inlet end, and a header in fluid communication with the inlet ends. The header has at least one restricted flow region in which fluid flow is restricted to the inlet ends of a set of channels of the flow field and at least some of the plurality of channels include a pressure drop feature that is configured to increase fluid flow to the set of channels.

Abstract: Aspects of the disclosure are directed to a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face, where an aspect ratio between the first face and the second face ensures that the damper is installed in the cavity in accordance with a predetermined orientation.

Abstract: The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and at least one rib that protrudes from the wall and extends to a rib end, the rib end having a curved transition portion near a location where the at least one rib meets the wall.

Abstract: Fuel cell systems (10) and related methods for limiting fuel cell slippage are provided. A stacked plurality of adjacent fuel cells (14) collectively forming a fuel cell stack (12). The fuel cells each include a pair of first and second plates (30, 30?, 30?; 32, 32?, 32?) at respective opposite ends thereof. A first fuel cell has a first plate (30, 30?, 30?) in engagement with a second plate (32, 32?, 32?) of a second fuel cell adjacent to the first fuel cell. A slip mitigation arrangement (50, 50?, 50?) between at least one of the pairs of the first and second fuel cells comprises first and second seats (62, 62?, 62?; 64, 64?, 64?) recessed in the engagement surfaces of the first and second conductive plates respectively, and a key member (60, 60?, 60?) having opposite ends seated in the first and the second recessed seats such that relative movement between the first and the second fuel cells is limited.

Abstract: A fuel cell plate is provided that includes a flow field having a plurality of channels each with an inlet end, and a header in fluid communication with the inlet ends. The header has at least one restricted flow region in which fluid flow is restricted to the inlet ends of a set of channels of the flow field and at least some of the plurality of channels include a pressure drop feature that is configured to increase fluid flow to the set of channels.