Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: Described embodiments establish at least one secure connection for a session. An intermediary device may intercept a domain name service (DNS) request from a client. The device may determine, according to the intercepted DNS request and configuration data of the device, that the client is preparing to establish a session with a server. The device may send a client hello message of the device to the server for establishing a first secure connection between the device and the server for the session, prior to the client sending a client hello message of the client for establishing a second secure connection between the client and the device for the session. The second secure connection may be established between the client and the device using a specified value for a session identifier received from the server in response to the client hello message of the device.

Abstract: A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path is defined between the inner and outer walls. The diffuser further includes a plurality of circumferentially-spaced struts extending from the inner wall to the outer wall across the gas path. At least one of the struts has a flap.

Abstract: A rotor blade includes an airfoil. The airfoil includes a leading edge and a trailing edge downstream of the leading edge. The airfoil also includes a radially outer tip with a pressure side tip rail and a suction side tip rail. A slot is formed in an aft portion of the suction side tip rail and an opening is positioned between the suction side tip rail and the pressure side tip rail at the trailing edge. Gas flows from the tip via the slot and the opening to inhibit formation of a vortex flow proximate to the suction side of the airfoil.

Abstract: A system for a turbomachine includes a rotor blade configured to rotate along a circumferential direction within a casing of the turbomachine and a shroud positioned outward of the rotor blade along a radial direction. The rotor blade includes a root, a tip spaced radially outward from the root, a pressure side tip rail that extends around the tip of the rotor blade along a pressure side wall, and a suction side tip rail that extends around the tip of the rotor blade along a suction side wall. The shroud includes a radially inner surface facing the pressure side tip rail and the suction side tip rail of the rotor blade and spaced from the pressure side tip rail and the suction side tip rail of the rotor blade by a clearance gap. The shroud also includes a plurality of grooves extending continuously along the circumferential direction.

Abstract: Stator vanes including curved trailing edges are disclosed. The stator vanes may include a body including a central section, a tip section positioned radially above the central section, and a root section positioned radially below the central section. The body of the stator vanes may also include a leading edge extending radially adjacent the root section, central section, and tip section, respectively, and a trailing edge positioned opposite and aft to the leading edge. The trailing edge may include a concave contour including a first portion radially aligned with the central section of the body. The first portion may be axially offset and forward of a reference line that may be perpendicular to an axial direction and intersects the concave contour at the tip section and the root section. A concavity of the first portion of the concave contour may be formed radially aft of the central section.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A turbine bucket includes an entry dovetail; an airfoil portion extending from the entry dovetail, the airfoil portion having a leading edge, a trailing edge, a pressure side and a suction side. Radially inner- and outer-span shrouds are provided on each of the pressure side and the suction side, the part-span shrouds each having hard faces adapted to engage and slide relative to corresponding part-span shrouds on adjacent buckets.

Abstract: A gas or steam turbine is disclosed herein. The turbine may include a throat area formed between adjacent buckets. The turbine also may include a variable throat device associated with at least one of the adjacent buckets. The variable throat device may be configured to vary the throat area between the adjacent buckets for improved part load performance.

Abstract: Various embodiments include a turbomachine bucket having a flow interrupter, as well as related turbomachines. Various embodiments include a turbomachine bucket having: a base section sized to couple with a turbomachine rotor, the base section having a leading edge and a trailing edge opposing the leading edge; a blade section coupled to the base section and aligned to extend radially from the base section; a shroud coupled to the blade section and aligned to extend radially from the blade section; and a flow interrupter coupled to the leading edge of the base section.

Abstract: A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products and a turbine section having one or more turbine stages between an upstream end and a downstream end. The one or more turbine stages are driven by the combustion products. The gas turbine engine also includes an exhaust section disposed downstream from the downstream end of the turbine section. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The gas turbine engine also includes a mixing device disposed in the exhaust section. The mixing device is configured to divide the exhaust gas into a first exhaust gas and a second exhaust gas, and to combine the first and second exhaust gases in a mixing region to produce a mixed exhaust gas.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation.

Abstract: A turbomachine diffuser includes a body having an inner surface defining a diffuser flow path, a plurality of stationary struts extending from the inner surface, and a plurality of flow mixing lobes arranged in an annular array on the inner surface. The plurality of flow mixing lobes is configured and disposed to guide a substantially high momentum flow toward the inner surface of the body.

Abstract: A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path is defined between the inner and outer walls. The diffuser further includes a plurality of circumferentially-spaced struts extending from the inner wall to the outer wall across the gas path. At least one of the struts has a flap.

Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.

Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.