Gas turbine temperature measurement
AssigneeAnsaldo Energia Switzerland AG
InventorsWolfgang Lang, Jürgen Hoffmann
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Abstract
The disclosure relates to a method for determining a temperature in a pressurized flow path of a gas turbine comprising the steps of sending an acoustic signal from an acoustic signal emitting transducer across a section of the pressurized flow path, detecting the acoustic signal with a receiving transducer, measuring the time needed by the acoustic signal to travel from the acoustic signal emitting transducer to the receiving transducer, calculating the speed of sound, and calculating the temperature as a function of the speed of sound, the heat capacity ratio (□) and a specific gas constant (Rspec) of the gas flowing in the pressurized flow path. Besides the method, a gas turbine with a processor and transducers arranged to carry out such a method is disclosed.
Claims17
A method for determining a temperature in a pressurized flow path of a gas turbine downstream of a compressor and upstream of a turbine, comprising:
- sending an acoustic signal from an acoustic signal emitting transducer arranged to send an acoustic signal across at least a section of a cross section of the pressurized flow path;
- detecting the acoustic signal with a receiving transducer arranged to receive the acoustic signal after the acoustic signal crossed the section;
- measuring the time needed by the acoustic signal to travel from the acoustic signal emitting transducer to the receiving transducer;
- calculating the speed of sound based on the measured traveling time and distance between acoustic signal emitting transducer and the receiving transducer;
- providing a heat capacity ratio (κ) and a specific gas constant (Rspec) of a gas flowing in the pressurized flow path;
- and
- calculating the temperature of the gas in the section of the pressurized flow path as a function of the speed of sound, the heat capacity ratio (κ) and the specific gas constant (Rspec) of the gas flowing in the pressurized flow path, wherein a combustion pulsation pressure is measured over frequency, a maximum pulsation pressure is determined, and a frequency of the acoustic signal emitting transducer is tuned to a frequency, with a combustion pulsation pressure, which is less than 20% of the maximum pulsation pressure.
A method for determining a temperature in a pressurized flow path of a gas turbine downstream of a compressor and upstream of a turbine, comprising:
- sending an acoustic signal from an acoustic signal emitting transducer arranged to send an acoustic signal across at least a section of a cross section of the pressurized flow path;
- detecting the acoustic signal with a receiving transducer arranged to receive the acoustic signal after the acoustic signal crossed the section;
- measuring the time needed by the acoustic signal to travel from the acoustic signal emitting transducer to the receiving transducer;
- calculating the speed of sound based on the measured traveling time and distance between acoustic signal emitting transducer and the receiving transducer;
- providing a heat capacity ratio (κ) and a specific gas constant (Rspec) of the gas flowing in the pressurized flow path;
- and
- calculating the temperature of the gas in the section of the pressurized flow path as a function of the speed of sound, the heat capacity ratio (κ) and the specific gas constant (Rspec) of the gas flowing in the pressurized flow path, wherein a combustion pulsation pressure is measured as a function of a frequency of the acoustic signal emitting transducer and the frequency of the acoustic signal emitting transducer is tuned to a frequency, which is free of pulsations and/or engine noise.
Dependencies are inferred from the claim text.