Abstract: A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be used to form a leading edge cooling circuit (102) in a gas turbine engine airfoil (100). The leading edge cooling circuit (102) includes a cooling fluid passage (104) having a leading edge portion (106) formed by the first core element leading edge section (30), a tip portion (108) formed by the first core element tip section (32), and a turn portion (110) formed by the first core element turn section (34). Each of the leading edge portion (106), the tip portion (108), and the turn portion (110) of the cooling fluid passage (104) are formed concurrently in the airfoil (100) by the first core element (16).

Abstract: An electronic device includes a housing and a corner structure. The housing is provided with a corner portion and two side edges adjacent to the corner portion. The housing includes an outer surface, an inner surface parallel to the outer surface, and a side surface located at the corner portion and respectively connected to the outer surface and the inner surface, wherein the side surface is a hierarchical curved surface. The corner structure is embedded in the corner portion. The corner structure is provided with an arc-shaped side edge that is aligned with the adjacent two side edges, one side of the corner structure, which is opposite to the arc-shaped side edge, is fitted to the side surface of the housing, and the corner structure is a reinforced material structure.

Abstract: A panel light-on apparatus, panel light-on testing system and panel light-on testing method are provided. Wherein, the panel light-on apparatus comprises a supporting member; a workbench provided on the supporting member to hold and secure a tested panel; and a display panel located at bottom of the workbench to provide a backlight to the tested panel and display a predetermined image, wherein the predetermined image is projected to the tested panel and overlapped with an image displayed by the tested panel. Through adding the display panel, not only a backlight for the tested panel, but also real-time displaying defect images are provided to assist in determining the cause of the defect; and the display range of the display panel can be adjusted in accordance with the sizes of different tested panels to achieve the purpose of light-proofing of other non-test panel areas on the workbench.

Abstract: A blade (10) for a turbine engine that includes an internal cooling system (56) formed from at least one cavity (58) positioned within a generally elongated airfoil (12). A squealer tip (36) and at least one densified oxide dispersion strengthened layer (38) extend radially from a radially outer tip cap (70) of the blade (10), the tip cap (70) having a tip cap upper surface (50).

Abstract: A processor-implemented method for generating a test suite within a time requirement is provided. The processor-implemented method includes executing a rule selection operation to determine candidate test cases utilizing attributes corresponding to each of the candidate test cases to produce selected test cases. The processor-implemented method includes determining whether an estimated testing execution time of the selected test cases is equal to or less than the time requirement. The processor-implemented method includes generating the test suite based on the selected test cases when the estimated testing execution time is equal to or less than the time requirement.

Abstract: A processor-implemented method for generating a test suite within a time requirement is provided. The processor-implemented method includes executing a rule selection operation to determine candidate test cases utilizing attributes corresponding to each of the candidate test cases to produce selected test cases. The processor-implemented method includes determining whether an estimated testing execution time of the selected test cases is equal to or less than the time requirement. The processor-implemented method includes generating the test suite based on the selected test cases when the estimated testing execution time is equal to or less than the time requirement.

Abstract: An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined at least partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radially outboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50), before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c).

Abstract: A bladed rotor system (10) for a turbomachine includes a row of blades (14) mounted on a rotor disc (12). Each blade (14) includes an airfoil (16) with a mid-span snubber (30). The row of blades (14) includes first (H) and second (L) sets of blades (14). The blades (14) of the second set (L) are distinguished from the blades (14) of the first set (H) by a geometry of the snubber (30) that is unique to the respective set (H, L). In particular, the snubbers (30) of the second set (L) are attached to the respective airfoils (16) at a different span-wise height than that of the snubbers (30) of the first set (H). Thereby the natural frequency of a blade (14) in the second set (L) differs from the natural frequency of a blade (14) in the first set (H) by a predetermined amount. Blades (14) of the first set (H) and the second set (L) are positioned alternately in the row of blades (14), to provide a frequency mistuning to stabilize flutter of the blades (14).

Abstract: Disclosed LTS strong password by convention systems include a password designation system, a portable password devices and other systems. Disclosed portable device include age-sensitive display systems to ensure that passwords and their replicas do not get forgotten or otherwise become stale. Portable devices include sophisticated electronics to commutate with a pet owner, including means of communication not requiring the use of a smart phone. Portable devices may include a base collar containing a microprocessor and other computer related components. Password rule engine support flexible password definition by means of pseudorandom expressions and may be adjusted as needed by an owner or subject systems. Disclosed device functions are executed by the disclosed portable devices and facilitate long-term password replication and policy-driven password maintenance.

Abstract: A turbine component including a shrouded airfoil with a flow conditioner configured to direct leakage flow and coolant to be aligned with main hot gas flow is provided. The flow conditioner is positioned on a shroud base radially adjacent to the tip of the airfoil and includes a ramped radially outer surface positioned further radially inward than a radially outer surface of the shroud base. The ramped radially outer surface extends from a first edge to a second edge in a direction generally from the suction side to the pressure side of the airfoil, such that the first edge is positioned further radially inward than the second edge. Multiple coolant ejection holes are positioned on the ramped radially outer surface. The coolant ejection holes are connected fluidically to an interior of the airfoil.

Abstract: A panel light-on apparatus, panel light-on testing system and panel light-on testing method are provided. Wherein, the panel light-on apparatus comprises a supporting member; a workbench provided on the supporting member to hold and secure a tested panel; and a display panel located at bottom of the workbench to provide a backlight to the tested panel and display a predetermined image, wherein the predetermined image is projected to the tested panel and overlapped with an image displayed by the tested panel. Through adding the display panel, not only a backlight for the tested panel, but also real-time displaying defect images are provided to assist in determining the cause of the defect; and the display range of the display panel can be adjusted in accordance with the sizes of different tested panels to achieve the purpose of light-proofing of other non-test panel areas on the workbench.

Abstract: A compressor (10) configured for use in a gas turbine engine (12) and having a rotor assembly (14) with a pumping system (16) positioned on a rotor drum (18) to counteract reverse leakage flow at a gap (20) formed between one or more stator vane tips (22) and a radially outer surface (24) of the rotor drum (18). The pumping system (16) may be from pumping components (26) positioned radially inward of one or more stator vane tips (22) to reduce, if not completely eliminate, reverse leakage flow at the stator vane tips (22). In at least one embodiment, the pumping component (26) may be formed from one or more cutouts (28) in the outer surface (24) of the rotor drum (18). In another embodiment, the pumping component (26) may be formed from at least one pumping fin (30) extending from the radially outer surface (24) of the rotor drum (18). In at least one embodiment, rows (32) of pumping components (26) may be aligned with rows (34) of stator vanes (36) within the compressor (10).

Abstract: The present disclosure provides an integrated design building block with turnable modules inside, the building block comprising: a lower housing, an upper housing, and a plurality of turnable modules mechanism, the lower housing and the upper housing being fitted to form a plurality of receiving spaces, the plurality of turnable modules being disposed within the plurality of receiving spaces, respectively, wherein the turnable modules may be partially or completely received in the receiving spaces, the turnable modules each having a turnable module connection portion; the lower housing and the upper housing are fitted to form a body structure of the building block; a plurality of connection portions are provided on surfaces of the body structure; the turnable module connection portions are fitted to the plurality of connection portions on the surfaces of the body structure. The building block provided by the present disclosure has advantages of a simple mechanical structure and a low cost.

Abstract: A system and method for identifying a phishing website is disclosed. Content associated with a website that a user is attempting to access is retrieved and translated into a format that a classifier can process. The classifier is trained to identify phishing attempts for a particular website or family of websites. The classifier processes the website to determine if the website is a phishing website. A scorer can determine the likelihood that the classifier classified the website correctly. If the website is determined to be a phishing website a protection component can deny access to the website. Otherwise the user can be permitted to access the website.

Abstract: Turbine and compressor casing/housing abradable component embodiments for turbine engines, have abradable surfaces with ridges projecting from the abradable surface, separated by grooves. The ridges have one or both sidewalls inclined against the opposing turbine blade tip rotational direction for redirecting and/or dissipating blade tip gap leakage airflow energy. In some embodiments the ridge tip and/or groove base have inclined profiles for redirecting airflow leakage away from the blade tip gap. In some embodiments, the inclined ridge tip profile provides a progressive wear zone that increases abradable surface area as the inclined ridge is abraded by the rotating blade tip.

Abstract: A processor-implemented method for generating a test suite within a time requirement is provided. The processor-implemented method includes executing a rule selection operation to determine candidate test cases utilizing attributes corresponding to each of the candidate test cases to produce selected test cases. The processor-implemented method includes determining whether an estimated testing execution time of the selected test cases is equal to or less than the time requirement. The processor-implemented method includes generating the test suite based on the selected test cases when the estimated testing execution time is equal to or less than the time requirement.

Abstract: A processor-implemented method for generating a test suite within a time requirement is provided. The processor-implemented method includes executing a rule selection operation to determine candidate test cases utilizing attributes corresponding to each of the candidate test cases to produce selected test cases. The processor-implemented method includes determining whether an estimated testing execution time of the selected test cases is equal to or less than the time requirement. The processor-implemented method includes generating the test suite based on the selected test cases when the estimated testing execution time is equal to or less than the time requirement.

Abstract: A turbine blade including a pressure sidewall (24) and a suction sidewall (26), and at least one partition rib (34) extends between the pressure and suction sidewalls (24, 26) to define a serpentine cooling path (35) having adjacent cooling channels (36a, 36b, 36c) extending in the spanwise direction (S) within the airfoil (12). A flow turning guide structure (50) extends around an end of the at least one partition rib (34) and includes a first element (52) extending from the pressure sidewall (24) to a lateral location in the cooling path between the pressure and suction sidewalls (24, 26), a second element (54) extending from the suction sidewall (26) to the lateral location in the cooling path between the pressure and suction sidewalls (24, 26). The first and second elements (52, 54) include respective distal edges (52d, 54d) that laterally overlap each other at the lateral location.

Abstract: Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

Abstract: Turbine and compressor casing abradable component embodiments for turbine engines vary localized porosity or abradability through use of holes or dimple depressions of desired polygonal profiles that are formed into the surface of otherwise monolithic abradable surfaces or rib structures. Abradable porosity within a rib is varied locally by changing any one or more of hole/depression depth, diameter, array pitch density, and/or volume. In various embodiments, localized porosity increases and corresponding abradability increases axially from the upstream or forward axial end of the abradable surface to the downstream or aft end of the surface. In this way, the forward axial end of the abradable surface has less porosity to counter hot working gas erosion of the surface, while the more aft portions of the abradable surface accommodate blade cutting and incursion with lower likelihood of blade tip wear.