Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Alstom (switzerland) Ltd

General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

Jaroslaw Leszek Szwedowicz

Andreas Hohl

Wolfgang Kappis

Alexander Stankowski

Ken Yves Haffner

Piero-Daniele Grasso

Stefan Irmisch

Alexey Mozharov

Sebastian Marc Schwarzendahl

Marcus Neubauer

Pierre-Alain Masserey

Daniel Beckel

Jörg Wallaschek

Jonas Boettcher

Andreas Bauer

Simone Hoevel

Lars Panning

Dariusz Szwedowicz

Lukas Emanuel Rickenbacher

Florian Schiedeck

George Kirilov Drensky

Peter Helmut Breuhaus

The application relates to a method and a device for suppressing ice formation on intake structures of a compressor, particularly the compressor of a gas turbine. The technical aim of the present invention is to provide a method and a device for suppressing the formation of ice on said structures, which avoid the disadvantages of known solutions, such as a reduction of the performance of the gas turbine, and have a simple and broad applicability. According to the present invention the mechanical vibratory energy of said structures during operation is converted into electrical energy by a piezoelectric element, firmly applied to said structure, and in a connected electrical circuit the generated electrical energy is then converted into thermal energy by an ohmic resistor and this thermal energy is conducted to at least a portion of the structure for suppressing ice formation. Excess energy may be transmitted by a transmitter to other circuits in adjacent structures.

Method and device for suppressing the formation of ice on structures at the air intake of a turbomachine

A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

Rotating machine

A sealing arrangement for sealing a gap () between two adjacent, thermally loaded components (') of a thermal machine, especially a turbomachine or gas turbine, includes a seal () which is supported in a recess () which extends transversely to the gap () and traverses said gap (). An efficient and simple improvement of the sealing arrangement is made by the seal () being formed at least partially of a shape memory alloy in such a way that, when a pre-specified temperature limit is exceeded, the seal changes its sealing behavior.

Sealing arrangement for a thermal machine

A turbomachine which operates at enhanced operating temperatures includes a stationary component. A rotating component includes a clearance to avoid a rubbing contact between the stationary component and the rotating component, the clearance including a first value in a stationary state of the turbomachine and a second value in a steady-state operation of the machine, wherein during a transient operating phase between the stationary state and the steady-state operation, the clearance includes a value which traverses a curve having an extreme value on account of a different time variation of a rotational speed and a thermal expansion of different components. A compensating device includes a non-linear compensation mechanism configured to reduce or compensate the extreme value during the transient operating phase.

Turbomachine clearance control configuration using a shape memory alloy or a bimetal

A thermally loaded, cooled component thermally coupled to a cooling system configured to receive a gaseous cooling introduced in a forced manner from outside that flows through the cooling system so as to absorb and transport heat away from the component as a result of thermal contact with the component. The component includes at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the component.

Thermally loaded, cooled component

In a method for influencing, in particular damping or suppressing, mechanical vibrations occurring during operation in a turbomachine blade (), the mechanical vibratory energy of the turbomachine blade () is first converted into electrical energy and the electrical energy generated is then converted into heat loss. Effective damping which can be used especially simply and in a versatile way is achieved in that the piezoelectric effect is used in order to convert mechanical vibratory energy into electrical energy.

Method for influencing, damping, or suppressing mechanical vibrations occurring during operation in a turbomachine blade, a turbomachine blade useful for carrying out the method, and a piezoelectric damping element

A damping arrangement for a blade () of an axial turbine, in particular a gas turbine, includes a damping element () which is arranged in a recess () in the blade aerofoil () of the blade () and frictionally dampens the vibrations of the blade (). In such a damping arrangement, simplified manufacture and assembly and a reliable and effective function are achieved by the recess being configured as a cavity () extending in the radial direction through the inside of the blade aerofoil (), the damping element () being inserted in the radial direction into said cavity ().

Damping arrangement for a blade of an axial turbine

Blade assembly with damping elements

Growing community of inventors

Bad Zurzach, Switzerland

Jaroslaw Leszek Szwedowicz