General Electric Company

Alstom Technology Limited

Alstom (Switzerland) Ltd

Alstom Power N.v.

General Electric Technology Gmbh

Brian Robert Haller

David Paul Blatchford

Philip David Hemsley

Adrian Clifford Lord

Bryan Roy Palmer

Timothy Stephen Rice

Ivan William Mcbean

Gursharanjit Singh

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.

Controlled flow turbine blades

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

Tip balance slits for turbines

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.

Blade structure for turbomachine

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 (W/W) of 0.4 to 0.7.

Controlled flow guides for turbines

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.

Turbine arrangement

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 (W) at the platform and tip regions, respectively and a minimum axial width (W) at a position between the platform region and the tip region.

Aerofoil blade for an axial flow turbomachine

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.

Axial flow turbine

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.

Solid particle diversion in an axial flow steam turbine

An axial flow gas turbine comprises a turbine and a turbine exhaust section. The turbine comprises a turbine nozzle containing a low pressure turbine stage having an annular row of stator vanes (V ) followed in axial succession by an annular row of rotor blades (B ). The low pressure turbine stage is characterized by the following parameters: the ratio of vane airfoil pitch to vane airfoil axial width (P/W) at the root end of the vane airfoil (V ) is in the region of 1.0 to 1.2, preferably about 1.12; the ratio of blade airfoil pitch to blade airfoil axial width (P/W)at the root end of the blade airfoil (B ) is in the region of 0.6; the ratio of blade diameter at the tip end of the blade airfoil to blade diameter at the root end of the blade airfoil (blade tip/hub diameter ratio) is in the region of 1.6-1.8, preferably about 1.72; and the ratio of the axial length of the exhaust section to the blade airfoil height (L/H) is no greater than a value in the region of 4:1, preferably 3:1. These parameters are subject to a permitted variation of up to &plusmn;10%, preferably up to &plusmn;5%. Dimensions of example airfoils are given and are scaleable to produce turbines of any chosen power.

Turbines and their components

A turbine stator vane for use in an axial flow gas turbine. The vane has an aerofoil, the pressure face of which is convex between platform and tip regions in a plane which extends both radially of the turbine and transversely of the general working fluid flow direction between the vanes. The trailing edge of the aerofoil is straight from platform to tip, and the spanwise convex and concave curvatures of the aerofoil pressure and suction surfaces respectively are achieved by rotational displacement of the aerofoil sections about the straight trailing edge. However, the axial width of the aerofoil is substantially constant over substantially all of the aerofoil radial height and the chord line at mid-height aerofoil sections is shorter than the chord lines in aerofoil sections at platform or tip regions. Reducing chord length at the mid-height region in this way lowers aerodynamic profile losses without unduly affecting vane performance. Also disclosed is a turbine rotor blade designed to form a stage pair with the stator vane.

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Market Rasen, United Kingdom

Brian Robert Haller