Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Alstom (switzerland) Ltd

Ansaldo Energia IP UK Limited

Hanspeter Zinn

Giuseppe Bandiera

Mohamed Youssef Nazmy

Bruno Schuermans

Andreas Künzler

Heinz Bollhalder

Thomas Etter

Felix Guethe

Klaus Doebbeling

Sasha Savic

Nicolas Noiray

Carlos Jimenez Haertel

Paul Muralt

Ken-Yves Haffner

Torsten Wind

Robert Baumann

Paolo Ruffino

Hugo Wetter

Ghislain Singla

Klaus Döbbeling

Piotr Siewert

Wolfgang Lang

Armin Brehm

Wolfgang Evers

Xabier Antonanzas

Joerg Rinn

Mark Clark

Michael Habermann

Danda-Raj Pahari

Rolf Rüetschi

Dejan Rajkovic

Vladimir Pashchenko

Michael Kleemann

Piotr Siewart

A sensor device () comprises a piezoelectric transducer () and a base member (). The piezoelectric transducer includes a piezoelectric member with at least one excitation electrode () connected to a first face thereof and having a thickness (h) between the first face and a second face. The piezoelectric transducer () is attached to a supporting face of the base member () with the second face of the piezoelectric transducer positioned adjacent the supporting face of the base member. The base member includes at least one acoustic wave reflecting tag () distant from the piezoelectric member.

Interrogatable passive acoustic sensor device with reflective tags

A temperature probe and method for determining a temperature in a gas flow are disclosed. The probe includes a probe body. A free flow temperature sensor a free flow temperature of the gas flow and a total temperature sensor measures a total temperature of the gas flow. The method includes measuring a flow temperature in a free gas flow, providing a static gas volume in which essentially all kinetic energy of the flowing gas is recovered and converted into thermal energy, and measuring a total temperature in the static gas volume. An accurate determination of the total temperature of a gas flow, which is representative of a specific total enthalpy, can thereby be achieved while detecting fast and transient temperature changes.

Temperature probe

A probe is provided for measuring high frequent pressure oscillations of hot gases that combines redundancy of the output signals with high quality of the output signals.

Probe for measuring pressure oscillations in the combustor of a gas turbine

A control system for at least one of steam turbines, gas turbines or power plants includes a sensor system configured to monitor predefined operating parameters, the sensor system including redundant sensors. A central processor arrangement of the control system has an input side configured to receive measurement data from the sensor system and an output side configured to communicate with operation control elements of the turbines or power plants. A sensor side processor circuit is assigned at least to the redundant sensors, the processor circuit being configured to continuously check the sensors for error-free operation, to protect or block the input side of the central processor arrangement from erroneous signals, and to only respectively forward or further process signals from a sensor that has been identified as error-free in one channel.

Control system

A method can protect a gas turbine engine (), which includes a compressor (), a combustor (), and a turbine (), against high dynamical process values, especially in combustor/flame pulsations. Effective protection against high dynamical process values, especially in combustor/flame pulsations, can be achieved by:

Method for protecting a gas turbine engine against high dynamical process values and gas turbine engine for conducting the method

The present invention relates to an oxidation resistant Nickel alloy, characterized in the following chemical composition (in % by weight): 4-7 Cr, 4-5 Si, 0.1-0.2 Y, 0.1-0.2 Mg, 0.1-0.2 Hf, remainder Ni and unavoidable impurities. A preferred embodiment has the following chemical composition (in % by weight): 6 Cr, 4.4 Si, 0.1 Y, 0.15 Mg, 0.1 Hf, remainder Ni and unavoidable impurities. This alloy has an improved oxidation resistance and good creep properties at high temperatures.

Oxidation resistant nickel alloy

An iron-based high-temperature alloy is disclosed which contains the following chemical composition: 20% by weight Cr; 5 to 6% by weight Al; 4% by weight Ta; 4% by weight Mo; 3 to 4% by weight Re; 0.2% by weight Zr; 0.05% by weight B; 0.1% by weight Y; 0.1% by weight Hf; 0 to 0.05% by weight C; and remainder Fe and unavoidable impurities. The alloy can be produced at low cost and can possess outstanding oxidation resistance and good mechanical properties at temperatures up to 1200&#xb0; C.

High-temperature alloy

A method for forming an oxygen resistant aluminum oxide layer on an outer surface of a thermocouple sheath composed of a nickel alloy containing between 1% to 7% aluminum comprises removing a pre-formed oxide layer from the outer surface so as to create a prepared sheath; performing a controlled oxidation by subjecting the prepared sheath to atmospheric conditions at a temperature between 1000&#xb0; C. and 1250&#xb0; C. so as to form the oxygen resistant layer on the thermocouple sheath and to thus form an oxidized sheath; and cooling the oxidized sheath so as to prepare the oxidized sheath for service.

Method for oxidising a thermocouple sheath

In a process for protection of a gas turbine () from damage caused by pressure pulsations (P), pressure pulsations (P) occurring during the operation of the gas turbine () are measured, from the measured pressure pulsations (P), a pulsation-time signal (PZS) is generated, the pulsation-time signal (PZS) is transformed into a pulsation-frequency signal (PFS), from the pulsation-frequency signal (PFS), a pulsation level (PL) is determined for at least one specified monitoring frequency band (), the pulsation level (PL) is monitored for the occurrence of at least one specified trigger condition, and, when the at least one trigger condition occurs, a specified protective action () is carried out.

Protection process and control system for a gas turbine

An apparatus for a rapid measurement of temperatures in a hot gas flow, in particular in a gas turbine. The apparatus includes a sensor having two two-dimensional, electrically conductive heating elements, which are attached to the surface of a common, electrically insulating sensor body.

Apparatus for the rapid measurement of temperatures in a hot gas flow

A method for operating a gas turbine installation () includes sucking in a gaseous medium () by the compressor () and compressed in the compressor space, a liquid medium () being injected into the gaseous medium (), so that a two-phase flow comprising a gaseous phase and a liquid phase is formed at least in a subregion of the compressor (). The gaseous medium () is then burnt with fuel () in a combustion chamber () to form hot gases (), and the hot gases () are expanded in a turbine (), the hot components of the gas turbine installation () being cooled by cooling air () of a cooling air system. A measurement is carried out to determine whether a liquid phase is present in a region of the compressor () and/or of the cooling air system.

Method for operating a gas turbine installation, and gas turbine installation

Relevant fuel-gas properties (X) are measured on an ongoing basis while a gas turbine group is operating. The Calkane content of the fuel gas is of particular interest in this context, since it has a significant influence on the ignitability of the fuel gas in the combustion chamber. The operating parameters of the gas turbine group are acted on directly as a function of the measured fuel-gas properties. In particular, in the case of the example of a gas turbine group with sequential combustion, the distribution of the fuel mass flows ({dot over (m)}, {dot over (m)}) between the combustion chambers () of the gas turbine group is varied. Furthermore, if there is provision for inert media, such as water or steam, to be introduced, it is possible for the mass flow of inert media ({dot over (m)}) to be controlled as a function of the measured fuel properties.

Method for operating a turbine group

A probe for measuring pressure oscillations includes an inner tube functioning as a measuring tube, an outer tube positioned so as to envelop the measuring tube, a toroidal space open to one side being defined between an outer wall of the measuring tube and an inner wall of the outer tube, a pressure transmitter, which is in connection with the interior of the measuring tube in the area of a transmitter end of the measuring tube, and a semi-infinite tube, which is connected at a first end to the transmitter end of the measuring tube, and which is connected at a second end to the toroidal space. The semi-infinite tube is constructed as a winding positioned around at least one of the measuring tube and the outer tube, thereby providing a compact and robust construction of a probe module, which is suitable especially for continuous use in the measuring of combustor pulsations in gas turbines.

Probe for measuring pressure oscillations

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Baden-Rütihof, Switzerland

Hanspeter Zinn