Abstract: The present application provides a turbine blade. The turbine blade includes a root section with a first curved section, a tip section with a second curved section, and number of mean sections positioned between the root section and the tip section. The mean sections each include a substantially prismatic shape.

Abstract: The present application provides a turbine with a flow of steam therethrough. The turbine may include a first guide blade, a second guide blade, a flow path for the flow of steam therebetween, and a fluidic flow control device. The fluidic flow control device may include a bypass line for a portion of the flow of steam and an injection port for injecting the portion of the flow of steam into the flow path.

Abstract: An apparatus for maintaining the upright position of a pot containing a plant is disclosed. The apparatus comprises a hub having attached support legs which radially extend outwards from the hub. Moveably attached to each support leg is an adjustable bracket constructively configured to grip the outer surface of the pot.

Abstract: This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extension ring (160) coupled to the diaphragm and positioned adjacent to the tip shroud (152), and a tip balance slit (200).

Abstract: The present application provides a turbine blade. The turbine blade includes a root section with a first curved section, a tip section with a second curved section, and number of mean sections positioned between the root section and the tip section. The mean sections each include a substantially prismatic shape.

Abstract: The present application provides a turbine blade. The turbine blade includes a root section with a first curved section, a tip section with a second curved section, and number of mean sections positioned between the root section and the tip section. The mean sections each include a substantially prismatic shape.

Abstract: The present application provides a control stage for a steam turbine. The control stage may include a number of guide blades and a number of runner blades. The number of runner blades may define a ratio of a pitch to a width of about 0.7 to about 1.1.

Abstract: The disclosure provides a blade with an airfoil including: a root region at a first radial end; a tip region at a second radial end opposite the first radial end; and a midspan region between the root region and the tip region and at least one endwall connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein the midspan region includes a reduced axial width relative to an axial width of the root region and an axial width of the tip region, and a reduced opening-to-pitch ratio at the midspan region relative to the root and tip regions.

Abstract: This application provides controlled flow runners (130) for use with steam turbines. Example controlled flow runners (130) may include a tip, a blade (132) adjacent to the tip, the blade (132) having a top width (134), a middle width (136), and a bottom width (138), where the middle width (136) is less than the top width (134) and the bottom width (138), and a root adjacent to the blade (132).

Abstract: This application provides a steam turbine. The steam turbine may include a number of controlled flow runners and a number of controlled flow guides. The controlled flow guides may include an upstream passage ratio (Wup/W) of 0.4 to 0.7.

Abstract: The disclosure provides a blade with an airfoil including: a root region at a first radial end; a tip region at a second radial end opposite the first radial end; and a midspan region between the root region and the tip region and at least one endwall connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein the midspan region includes a reduced axial width relative to an axial width of the root region and an axial width of the tip region, and a reduced opening-to-pitch ratio at the midspan region relative to the root and tip regions.

Abstract: The invention relates to a turbine for generating work by a stagewise expansion of a gas, such as steam wherein a downstream stage guide average height is less than an adjacent upstream stage runner average height.

Abstract: This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extension ring (160) coupled to the diaphragm and positioned adjacent to the tip shroud (152), and a tip balance slit (200).

Abstract: This application provides a steam turbine. The steam turbine may include a number of controlled flow runners and a number of controlled flow guides. The controlled flow guides may include an upstream passage ratio (Wup/W) of 0.4 to 0.7.

Abstract: The invention relates to a turbine diffuser for recovering pressure from a fluid exhausted from a last stage blade, the diffuser. In at least in a region between 10% of the longitudinal length and of the diffuser and a downstream end of the diffuser, the inner guide forms an inflectionless curve and further has a peak radial height at a point between 40%-60% of the longitudinal length.

Abstract: The invention relates to a turbine for generating work by a stagewise expansion of a gas, such as steam wherein a downstream stage guide average height is less than an adjacent upstream stage runner average height.

Abstract: Configuration of the last stage of a steam turbine where rotor blades rotate encircled by a vane carrier, such that a plurality of passages are located in the vane carrier, such that a fluid is blown through these passages forming a flow that impinges onto the rotor blades, the number of passages, the location of the passages in the vane carrier and the velocity of the flow impinging onto the rotor blades, being calculated in such a way that rotating flow instabilities in the rotor blades when the steam turbine operates at low volumetric flow conditions are avoided.

Abstract: An exemplary aerofoil blade for an axial flow turbomachine has a radially inner platform region, a radially outer tip region, an axially forward leading edge, and an axially rearward trailing edge. The aerofoil blade has a pressure surface which is convex in a radial direction, and a suction surface which is concave in the radial direction. The axial width (W) of the aerofoil blade can vary parabolically between maximum axial widths (Wmax) at the platform and tip regions, respectively and a minimum axial width (Wmin) at a position between the platform region and the tip region.

Abstract: An axial flow turbine includes in axial flow series a low pressure turbine section and a turbine exhaust system. The low pressure turbine section includes a final low pressure turbine stage having a circumferential row of static aerofoil blades followed in axial succession by a circumferential row of rotating aerofoil blades. Each aerofoil blade has a radially inner hub region and a radially outer tip region. The K value, being equal to the ratio of the throat dimension (t) to the pitch dimension (p), of each static aerofoil blade of the final low pressure turbine stage varies along the height of the static aerofoil blade, between the hub region and the tip region, according to a substantially W-shaped distribution.

Abstract: An exemplary axial flow steam turbine is disclosed which includes a motor, a turbine casing and at least first and second turbine stages, with the second turbine stage being located adjacent to and downstream from the first turbine stage. A radially outer static diaphragm ring of the second turbine stage includes an annular axial extension extending in an upstream axial direction and carrying a circumferential tip sealing device which cooperates with shrouds of a circumferential row of moving blades of the first turbine stage. An upstream end of the annular axial extension is axially spaced from a radially outer static diaphragm ring of the first turbine stage such that a circumferential passage is defined between the upstream end of the annular axial extension and the radially outer static diaphragm ring of the first turbine stage. Solid particles are diverted from steam flow by a circumferential passage during operation.