Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Brandenburger Liner Gmbh & Co. Kg

Ansaldo Energia IP UK Limited

Johannes Buss

Adnan Eroglu

Andrea Ciani

Michael Düsing

Urs Benz

Michael Hutapea

Douglas Pennell

Richard Smith

A lining tube for restoring a defective sewer shaft has an inner film tube and a radially expandable tubular layer of fiber material impregnated with a curable reaction resin. The inner film tube has a connecting portion that connects two circumferential portions, to a circumferentially closed inner film tube with a defined nominal diameter. The connecting portion has a predetermined breaking point that can be separated in the circumferential direction by introducing a pressure medium into the inner film tube in order to radially expand the inner film tube and the layer of fibrous material beyond the nominal diameter. The tubular layer of fiber material is closed by a seam at a first end that can be introduced into a channel of the sewer shaft. The seam extends orthogonally to the longitudinal axis of the tubular layer of fiber material of the lining tube.

Lining tube for restoring defective sewer shafts including a berm and a channel, and method for producing same, and method for lining a defective sewer shaft

The burner () of a gas turbine includes a duct () which houses four vortex generators () and a lance () that carries one or more nozzles () for injecting a fuel within the duct (). The lance () extends from one of the vortex generators ().

Burner of a gas turbine

A reheat burner () includes a channel () with a lance () protruding thereinto to inject a fuel over an injection plane () perpendicular to a channel longitudinal axis (). The channel () and lance () define a vortex generation zone () upstream of the injection plane () and a mixing zone () downstream of the injection plane () in the hot gas (G) direction. The mixing zone () includes a high speed area () with a constant cross section, and a diffusion area () with a flared cross section downstream of the high speed area () in the hot gas (G) direction.

Reheat burner

A reheat burner includes a channel with a lance projecting thereinto to inject a fuel over an injection plane perpendicular to a channel longitudinal axis. The channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas direction. The mixing zone has a cross section with diverging side walls in the hot gas direction. The diverging side walls define curved surfaces in the hot gas direction having a constant radius.

The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles.

Lance of a burner

An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052.

The burner () for a gas turbine includes a duct () housing a plurality of tetrahedron shaped vortex generators () and a lance () to inject a fuel to be combusted. Within the duct (), a plurality of vortex generators () are provided with a plurality of holes () for injecting cooling air. The cooling holes () define passing through areas that are non-uniformly distributed on a top wall () of the vortex generators (). A method for locally cooling a hot gases flow passing through a burner includes non-uniformly injecting cooling air from a vortex generator into the hot gas flow in the duct, which can reduce the occurrence of flashback in the burner.

Burner including non-uniformly cooled tetrahedron vortex generators and method for cooling

A burner () for a gas turbine includes a duct () enclosing a plurality of vortex generators () and, downstream of them, a lance () provided with nozzles () for injecting a gaseous fuel. The burner () also includes a mixer () for diluting and mixing the gaseous fuel with air to form a mixture. The mixer () is connected to the nozzles () for feeding them with the mixture. A method includes feeding the gaseous fuel in the burner ().

Growing community of inventors

Hohberg, Germany

Johannes Buss