| Patent application number | Description | Published |
|---|
| 20080232971 | Coated turbine blade - The invention refers to a coated turbine blade for a gas turbine, having blade walls divided into sections with locally adapted material temperatures. The cooler material temperatures of the blade walls are at the points where the support ribs merge into the blade walls. The regions with higher material temperatures of the blade walls are at the positions where cavities are arranged inside the blade walls. This is achieved via a ceramic thermal barrier coating having different layer thicknesses that allow different material temperatures. The region of the surface of the blade wall which faces the working medium and lies opposite an internal rib has a thicker thermal barrier coating than a region of the surface of the blade wall which is cooled via a cooling medium that flows in the cavities. This results in homogenization of the material temperature in the connecting regions, which results in prolonged blade life. | 09-25-2008 |
| 20090185913 | Method of Producing a Turbine or Compressor Component, and Turbine or Compressor Component - Disclosed is a turbine or compressor component with an integrated cooling channel, in particular a turbine blade, and a method for producing the same. The aim of the invention is to ensure an improved estimation of the service life of the component and furthermore, if possible, also increased safety during operation and increased service life, even in the presence of constantly variable thermal and mechanical stress. To achieve this, the cooling channel of the component is subjected to internal pressure during a pressure impingement phase, said internal pressure being at a level sufficiently high that it causes the at least semiplastic deformation of the wall regions delimiting the cooling channel. | 07-23-2009 |
| 20090252612 | Blade and gas turbine - The invention relates to a turbomachine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbomachine. The aim of said invention is to develop a device and a method for the turbomachine making it possible to reduce the size of a radial split of the turbomachine in order to obtain greater degree of efficiency. The inventive turbomachine comprises a rotor rotationally mounted in the case of the turbomachine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbomachine rotor by heating fluid flowing therethrough are also disclosed. | 10-08-2009 |
| 20110033305 | Turbine vane for a stationary gas turbine - A turbine vane for a stationary gas turbine is provided. The turbine vane includes a hollow vane blade, wherein a rib is provided inside the vane blade to allow a pressure side wall and a suction side wall to support one another. The rib has an opening penetrating the rib near a wall at a height of an external fillet between a side wall, and a platform surface for extending a life of the turbine vane. By the opening, material accumulations in a transition region are avoided or the accumulation is reduced, whereby increases in stiffness and higher temperature gradients associated therewith are avoided. | 02-10-2011 |
