Alstom Technology Limited

General Electric Technology Gmbh

Asea Brown Boveri Ag

Asea Brown Boveri Inc.

Said Havakechian

Ralf Greim

Ivan William McBean

Rolf Hunziker

Axel Pfau

Thomas Mokulys

Vishal Borikar

Timothy Stephen Rice

Benjamin Megerle

Patrick Vu

Simon-Pierre Monette

Harald Romer

Peter Szincsak

Martin Schonenberger

Nils Lannefors

Ulrich Steiger

Ivan Mcbean

A turbine blade having a root and a tip and an airfoil with a core section made of composite material and a protective sheath or layer joined to the composite core at a location or locations exposed to erosion is described with the composite core of the airfoil being continuous from a location in vicinity of the root to a location in vicinity of the tip of the blade and including a section which widens with distance from the rotational axis along the length of the airfoil and which ends at the location in vicinity of the tip of the blade. The protective sheath or layer is secured by interference fit with widening section of the core.

Turbine airfoil of composite material and method of manufacturing thereof

An axial flow turbine is described having a casing defining a flow path for a working fluid therein, a rotor co-axial to the casing, a plurality of stages, each including a stationary row of vanes circumferentially mounted on the casing a rotating row blades, circumferentially mounted on the rotor, with within a stage n vanes have an extension such that at least a part of the trailing edge of each of the n vanes reaches into the annular space defined by the trailing edges of the remaining N-n vanes and the leading edges of rotating blades of the same stage.

Static vane assembly for an axial flow turbine

An axial turbine () has a plurality of expansion stages () each defined by stator blades () and rotor blades. The expansion stages () are followed by an exhaust diffuser () for collecting the flow passing through the expansion stages () and discharging it to the outside. The expansion stages () and/or the diffuser () have at least a non-axial symmetric portion. The stator blades () define different openings () along the circumference of the turbine.

Axial turbine and method for discharging a flow from an axial turbine

A blade of a turbomachine, especially of a steam turbine, is characterized in that the chord length (s) in the middle region of the blade airfoil is shorter than the chord lengths (s, S) in the tip-side region or root-side region of the blade airfoil. As a result of this, a distribution of a Zweifel parameter over the longitudinal extent of the blade airfoil is achieved which minimizes the losses of a blade cascade of the blades.

Turbomachine blade with variable chord length

The blades of a turbomachine comprise airfoils, which are bent such that the lean angle (&#x3c6;), defined as the angle which the stacking line of the airfoil includes with the radial direction, and measured in the direction of rotation (&#x3c9;), is variable along the width of the flow channel and decreases from the hub towards the housing.

Turbomachine blade

A turbine () of a turbine installation, especially a steam turbine of a steam turbine installation, includes at least one radial or diagonal turbine stage () with radial or diagonal inflow and axial outflow, and also at least one axial turbine stage (-) with axial inflow and axial outflow. The at least one radial or diagonal turbine stage () forms the first stage of the turbine () and the at least one axial turbine stage (-) is arranged downstream of the radial or diagonal turbine stage () as an additional stage of the turbine. The at least one radial or diagonal turbine stage () has a higher temperature resistance than the at least one axial turbine stage (-). The turbine () makes it possible to significantly increase the process temperature of the steam turbine installation, wherein measures for increasing the temperature resistance need only to be adopted for components of the radial or diagonal turbine stage ().

Turbine

A turbomachine has, on its inner casing () and on its shaft, recesses into which shrouds of rotor blades and/or of guide vanes () protrude. The recesses are configured with wave-shaped contouring arrangements (), which extend over their periphery. The contouring () extends over axially extending regions of the recess and consists of periodic elevations and depressions () in the radial direction. They can also be effected on the radially extending regions of the recess and on the shrouds. The undulation-shaped contouring arrangements are used to counteract existing pressure fields and to reduce performance losses due to mixing processes between the leakage flow and the main flow.

Turbomachine

To reduce the number of stages of a turbine and, associated therewith, the overall length and the costs, blading having high stage-specific enthalpy transfer is to be used. In this case, the disadvantages of conventional highly loaded blading, such as increased secondary flow losses due to blades of large chord length and comparatively small height and the design of the turbine in the complicated chamber type of construction, are to be avoided. Resulting from these requirements is a highly loaded slim blade type of construction having considerable deflection. A turbine having blading according to the invention is characterized by a loading parameter RBL, which in the HRBL blading according to the invention, in contrast to conventional types of construction, is greater than 1.

Highly loaded turbine blading

In a turbomachine blade/vane for subsonic conditions with a convex curvature profile contour in the region of the leading edge and over the major part of the suction surface (S) and with a concave curvature profile contour in the region of the pressure surface (D), the profile contour in the suction-surface trailing edge region is designed to be concave (K). The momentum loss thickness mainly responsible for the profile loss is reduced in this region.

Growing community of inventors

Baden, Switzerland

Said Havakechian