Alstom Technology Limited

Asea Brown Boveri Ag

Alstom (switzerland) Ltd

Alstom

Abb Research Ltd.

Abb Management Ag

J. Eberspacher Gmbh & Co Kg

Abb Alstom Power (switzerland) Ltd.

Abb Alstrom Power (schweiz) Ag

Franz Joos

Marcel Stalder

Urs Benz

Adnan Eroglu

Wolfgang Polifke

Alexander Ni

Jaan Hellat

Peter Senior

Jakob J Keller

Michael Humburg

Rolf Althaus

Timothy Albert Griffin

Yau-Pin Chyou

Walter Blaschke

Günter Eberspach

Bettina Paikert

Felix Guethe

Jonas Hurter

Giovanni Cataldi

Manfred Wirsum

Pirmin Schiessel

Gijsbertus Oomens

Peter Novacek

Ulrich Waltke

Hans Koch

Uy-Liem Nguyen

Tino-Martin Marling

Guenter Sybon

Cristian Oliver Paschereit

Ali Cemal Benim

Marcel Schirbach

Provided is a control method for a gas turbine plant having a first and a second combustors in series, such that combustion gases produced in the first combustor flows into the second combustor. The second combustor having a fuel lance with internal partitions, for injecting at least one fuel and a gas having a mixture of inert gas and support air into the second combustor. The partitions enable the gas to carry, and/or veil, at least one of the fuels as the fuel exits the lance. A variable of the second combustor is measured and the inert gas to support air mixture varies in response to variations of the variable so as to at least partially compensate for the operational effects of the variable on the operation of the second combustor.

Operation of a gas turbine

A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (), with a combustion-chamber wall (), which is of double-walled design and, with an outer wall-surface part () and an inner wall-surface part () facing the combustion chamber (), gastightly encloses an intermediate space (), into which cooling air can be fed for purposes of convective cooling of the combustion-chamber wall (). The invention is distinguished by the fact that at least one third wall-surface part () is provided, which, with the outer wall-surface part (), encloses a gastight volume (), and that the gastight volume () is connected gastightly to the combustion chamber () by at least one connecting line ().

Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system

In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device () is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle () and heating it up to a temperature sufficient to ignite hydrocarbons by interacting with a resonance tube () arranged behind said nozzle (), and using said heated-up gas to directly or indirectly ignite a fuel/air mixture introduced into said combustion chamber.

Method for igniting the combustion chamber of a gas turbine unit and an ignition device for carrying out the method

An atomizing nozzle for a burner, especially for a vehicle heater has a flow guide element (), which provides a flow guide surface () and which has an atomizing lip () in an end area (). A fuel feed device () is provided for feeding fuel to the flow guide surface () at a spaced location from the atomizing lip (). Provisions are made for the fuel feed device () in the flow guide element () to comprise a fuel release depression (), into which opens a fuel feed channel device () in a junction area.

Atomizing nozzle for a burner

In a thermal turbomachine with a housing, a combustion chamber, an ignition device, a fuel supply, and an air supply, the ignition device includes an ignition space and an igniter arranged in the ignition space. The fuel supply and the air supply open into the ignition space. The ignition space is connected to the combustion chamber, and the ignition device is arranged outside the housing of the thermal turbomachine. A process is shown for the ignition of the thermal turbomachine outside the housing.

Thermal turbomachine and process for igniting the thermal turbomachine

In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber ( ), an ignition device ( ), a fuel supply ( ) and an air supply ( ), and the ignition device ( ) consisting of an ignition space ( ) and of an ignitor ( ) arranged in the ignition space ( ), the fuel supply ( ) and the air supply ( ) discharging into the ignition space ( ), and the ignition space ( ) being connected to the combustion chamber ( ) via a flame tube ( ), prior to the ignition of the combustion chamber ( ), an overall fuel/air mixture ratio &PHgr; &equals;1/&lgr; greater than 1, with &lgr; being the overall air ratio, is set in the flame tube ( ) of the ignition device ( ).

Method for igniting a thermal turbomachine

In a combustion device ( ), particularly for driving gas turbines, comprising a plurality of burners ( ) of identical thermal power output, which work parallel to an axis ( ) into a common combustion chamber ( ), an effective suppression of thermoacoustic combustion instabilities is achieved in a simple way in that the burners ( ) are designed differently from one another in such a way that the flames ( ) or flame fronts generated by them are positioned so as to be distributed along the axis ( ).

Combustion device for generating hot gases

In a combustion apparatus ( ), in particular for driving gas turbines, in which combustion apparatus ( ) a gaseous fuel in a burner ( ) is sprayed through a plurality of separate fuel-injection devices ( ) into a gas flow containing combustion air, and the resulting mixture flows into a combustion chamber ( ) for combustion and burns there, the acoustic impedance or stiffness of the fuel-injection devices ( ) is selected to be different in order to avoid thermoacoustic combustion instabilities.

Burner with damper for attenuating thermo acoustic instabilities

In a fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, which fuel lance is part of a secondary or tertiary burner, around which a hot-gas jet flows in a main flow direction, and comprises a liquid-fuel passage for supplying liquid fuel and first means for spraying the liquid fuel from the liquid-fuel passage into the combustion chamber, operation characterized by reduced addition of water is made possible owing to the fact that the first means comprise a liquid-fuel nozzle, which sprays the liquid fuel essentially parallel to the main flow direction as a plain jet into the combustion chamber.

Fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, and method of operating such a fuel lance

A multistage turbocompressor is equipped with a tapping point between two compressor stages. The guide-blade cascade of the stage arranged directly upstream or downstream of the tapping point is designed with adjustable geometry. The pressure at the tapping point can be set within wide limits, irrespective of the compressor operating point, by an adjustment of this guide-blade cascade.

Multistage turbocompressor

A damping device for reducing the vibration amplitude of acoustic waves and a burner for operating an internal combustion engine, the burner having a mixing region, in which an air flow and a fuel flow are mixed with one another to form an air/fuel mixture, and a combustion chamber, which in the direction of flow of the fuel/air mixture is arranged downstream of the mixing region, in which the fuel/air mixture can be ignited. A Helmholtz resonator directly connected to the mixing region of the burner such that acoustic waves formed in the burner are suppressed in the Helmholtz resonator and are not reflected back into the burner.

Damping device for reducing the vibration amplitude of acoustic waves for a burner

A fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, which fuel lance is provided with first means for the radial spraying of the liquid fuel from the liquid-fuel passage into the combustion chamber. The first means comprise a first guide tube, which, in the radial direction starting from the liquid-fuel passage, runs outward through a gas passage and an air passage. In addition, second means are provided, which comprise a second guide tube, which, in the radial direction starting from the gas passage, runs outward through the air passage and concentrically surrounds the first guide tube at a distance. Both guide tubes open in the region of a shell opening in the lance shell in such a way that the liquid-fuel jet discharging from the first guide tube discharges as a plain jet into the combustion chamber, and the fuel jets discharging from the guide tubes are surrounded in a sheath-like manner by the air flowing out of the air passage through the shell opening.

Fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber

In heat generators and burners, it is frequently necessary to realize discontinuous cross-sectional expansions of a flow duct. When the flow (U) passes over the step (,) formed in the wall (,) of the flow duct, coherent lateral separation vortices form which are propagated almost undamped downstream of the step and frequently represent the cause of thermo-acoustic vibrations of high amplitude. In accordance with the invention, vortex-generating elements (,) with a lateral pitch dimension (t) are arranged on a line transverse to the main flow (U) a distance (s) upstream of the step (,). Given an expedient selection of the pitch dimension (t), the lateral coherence of the separation vortex is enduringly destroyed.

Flow duct with cross-sectional step

The invention is directed to a method of operating a burner. The method includes feeding an auxiliary gas into a liquid fuel upstream of an injection orifice during the ignition and during part load of the burner, and interrupting the feeding of the auxiliary gases within high load ranges of the burner.

Growing community of inventors

Hamburg, Germany

Franz Joos