Asea Brown Boveri Ag

Ulf Christian M&uuml;ller

Dirk Wunderwald

Joachim Bremer

J&uuml;rg Greber

Helmut Gieszauf

Michajlo Bothien

Jakob Keller

Frank Reiss

Pirmin Schiessel

Mihajlo Bothien

Jochem Fischer

A method for cooling the flow in radial gaps formed between rotors and stators of turbomachines, which method is improved with regard to its cooling effect. In addition, a simple, cost-effective and robust arrangement for realizing the method is to be specified. According to the invention, this is achieved in that a first cooling fluid is admitted to a stator part adjacent to the radial gap and a second, gaseous cooling fluid is introduced into the radial gap. To this end, either at least one recess is formed in the interior of the stator part adjacent to the radial gap or at least one cavity is arranged at the stator part. The recess or the cavity is connected to both a feed line and a discharge line for the first cooling fluid. In addition, at least one feed passage as well as a discharge device for the second cooling fluid are arranged at the radial gap.

Method and arrangement for cooling the flow in radial gaps formed between rotors and stators of turbomachines

A method of cooling the flow in radial gaps formed between rotors and stators turbo machines is provided. The method includes the step of using water as a cooling fluid for the stator part adjacent to the radial gap. To this end, either at least one recess is formed in the interior of the stator part adjacent to the radial gap or at least one cavity is arranged at the stator part. The recess or the cavity is connected to both a feed line and a discharge line for the cooling fluid.

Method and arrangement for the indirect cooling of the flow in radial gaps formed between rotors and stators of turbomachines

The object of the invention is to create a centrifugal compressor with a cooling appliance which is simpler but more effective. This is achieved by the feed device (,) for the gaseous cooling medium (,) opening into the separating gap upstream of the mainly radially extending gap region (,) of the separating gap (,).

Centrifugal compressor

A burner arrangement (,) for a gas turbine comprises an interior space (,) enclosed by a casing (,), in which interior space (,) at least one burner (,) is arranged, and into which interior space (,) in each case a jet (,) of a gaseous medium, in particular air, is sprayed through at least two nozzle openings (,) against the direction of flow of the burner (,) and along the inner wall (,) of the casing (,) which jets (,), guided by the inner wall (,), meet one another from opposite directions and combine to form a secondary flow (,) flowing off perpendicularly from the inner wall (,). In such a burner arrangement, the flow is stabilized and evened out by virtue of the fact that, to establish the impingement point of the jets (,), a dividing plate (,) arranged in the flow path of the jets (,) and disposed essentially perpendicularly to the inner wall (,) is provided.

Burner arrangement for a gas turbine including an inlet-air impingement plate

Growing community of inventors

Kirchdorf, Switzerland

Ulf Christian Müller

Growing community of inventors

Kirchdorf, Switzerland

Ulf Christian M&uuml;ller

Ulf Christian Müller