Abstract: A sensor device (1) comprises a piezoelectric transducer (3) and a base member (2). The piezoelectric transducer includes a piezoelectric member with at least one excitation electrode (37, 38) connected to a first face thereof and having a thickness (h) between the first face and a second face. The piezoelectric transducer (3) is attached to a supporting face of the base member (2) 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 (21) distant from the piezoelectric member.

Abstract: Disclosed is a sensor device (1) comprising a piezoelectric transducer (3) and a base member (2). The piezoelectric transducer comprises a piezoelectric member with at least one excitation electrode (37, 38) connected to a first face thereof and having a thickness (h) between the first face and a second face. The piezoelectric transducer (3) is attached to a supporting face of the base member (2) with the second face of the piezoelectric transducer adjacent the supporting face of the base member. The base member comprises at least one acoustic wave reflecting tag (21) distant from the piezo-electric member.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a method for controlling a gas turbine, operating with an integral fuel reactivity measurement concept. In order to fast determine a safe operation range of the gas turbine with respect to flashback and blow-out, the method includes deducing the fuel composition and therefore the fuel reactivity by combined measurements of (n?1) physico-chemical properties of a fuel mixture with n>1 fuel components, for deriving the concentration of one component for each physico-chemical property of the fuel gas mixture or for determining of a ratio of the fuels with known compositions and adjusting at least one operation parameter of the gas turbine at least partially based on the determined property of the fuel gas mixture entering the combustors. With the technical solution of the present invention, by way of detecting fast changes in fuel gas, it is assured that the gas turbine may operate with varieties of fuel gas under optimized performance and in safe operation ranges.

Abstract: A method is provided for measuring the mass flow of a stream of a gaseous medium of elevated first temperature flowing through a specific pipe. The method includes providing a reference stream of the gaseous medium with a known mass flow and a second temperature being substantially lower than the first temperature. The method further includes mixing the reference stream with said stream of a gaseous medium of elevated first temperature flowing through said specific pipe. The measure resulting temperature of the mixture of the reference stream and said stream of a gaseous medium of elevated first temperature flowing through the specific pipe is measured.

Abstract: 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.

Abstract: A method can protect a gas turbine engine (10), which includes a compressor (11), a combustor (13), and a turbine (12), 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: a) measuring the pulsations of the combustor (13) with a suitable sensor (18), b) dividing the frequency spectrum of the measured pulsation signal up into pre-defined band pass sections, c) computing the rms (root mean square) of the signal for each band, d) weighting the computed frequency/frequency band rms with predetermined weighting factors, e) cumulating the weighted frequency/frequency band rms values to get a Pulsation Limit Criterion (PLC) value, f) comparing the PLC value with at least one reference value (23), and g) operating the gas turbine engine (10) according to the result of the comparison.

Abstract: 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.

Abstract: 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, good creep properties at high temperatures and.

Abstract: A method can protect a gas turbine engine (10), which includes a compressor (11), a combustor (13), and a turbine (12), 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: a) measuring the pulsations of the combustor (13) with a suitable sensor (18), b) dividing the frequency spectrum of the measured pulsation signal up into pre-defined band pass sections, c) computing the rms (root mean square) of the signal for each band, d) weighting the computed frequency/frequency band rms with predetermined weighting factors, e) cumulating the weighted frequency/frequency band rms values to get a Pulsation Limit Criterion (PLC) value, f) comparing the PLC value with at least one reference value (23), and g) operating the gas turbine engine (10) according to the result of the comparison.

Abstract: 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° C.

Abstract: 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° C. and 1250° 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.

Abstract: In a process for protection of a gas turbine (1) from damage caused by pressure pulsations (P), pressure pulsations (P) occurring during the operation of the gas turbine (1) 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 (12), 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 (16) is carried out.

Abstract: 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° C.

Abstract: Protective tubes for thermocouples exposed to oxidizing atmospheres at temperatures in the region of approximately 1100° C. are produced from a single-crystal nickel-based superalloy, preferably from an alloy having the following chemical composition (in % by weight): 7.7-8.3 Cr, 5.0-5.25 Co, 2.0-2.1 Mo, 7.8-8.3 W, 5.8-6.1 Ta, 4.9-5.1 Al, 1.3-1.4 Ti, 0.11-0.15 Si, 0.11-0.15 Hf, 200-750 ppm C, 50-400 ppm B, remainder nickel and unavoidable impurities. Protective tubes of this type exhibit good strength and good oxidation resistance under severe stress conditions.

Abstract: 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% aluminium 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° C. and 1250° C. so as to form the oxygen resistant layer on the thermocouple sheath and to thus form an oxidised sheath; and cooling the oxidised sheath so as to prepare the oxidized sheath for service.

Abstract: 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.