Gas Turbine Compressor Icing Sensor Placement
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Solution Overview
Problem
Existing gas turbine operations face challenges in accurately predicting and preventing icing events in the compressor, leading to potential machine damage and inefficiency, especially during part-load operations due to fluctuations in measurement conditions.
Innovation Solution
A gas turbine equipped with an icing sensor unit comprising air humidity, pressure, and temperature sensors strategically positioned between the first compressor rotor and guide blade rows in the compressor flow duct allows for precise determination of icing risks, enabling adjustments to the inlet guide blades to mitigate icing by reducing air flow acceleration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If variable compressor inlet guide blades are set to adapt compressor intake air mass flow in part-load operation, then maximum efficiency with given maximum exhaust gas temperature is achieved, but cooling of intake air in the region of inlet guide blade row and first compressor rotor blade row may lead to icing in the compressor
Solution Approach 1:
The patent applies preliminary action by measuring temperature, air humidity, and pressure in advance (before icing occurs) and using these measurements to predict the icing point. The control system proactively adjusts the inlet guide blade position to prevent icing before it happens, rather than reacting after icing occurs. This is achieved through the measurement device that continuously monitors conditions and the control system that predicts icing risk and takes preventive action.
Solution Approach 2:
The patent implements feedback by using measurement devices to continuously monitor temperature, air humidity, and pressure in the compressor flow duct, feeding this information back to the control system. The control system uses this feedback to determine the actual icing point and adjust the inlet guide blade position accordingly, creating a closed-loop control system that adapts to changing conditions and prevents icing while maintaining efficiency.
2Ease of operation
If measurements are performed upstream of the compressor inlet guide blade cascade to determine intake air conditions, then basis for controlling the gas turbine is obtained, but the measurements are subject to severe fluctuations in measurement conditions resulting in insufficient accuracy for predicting icing events
Solution Approach 1:
The patent applies dimensionality change by moving the measurement location from upstream (before the inlet guide blades) to a downstream position in the compressor flow duct where the flow conditions are more stable. This spatial relocation to a different dimension in the flow path allows measurements to be taken in a region less susceptible to severe fluctuations, thereby improving measurement accuracy for predicting the icing point.
3Reliability
If the minimum position of the variable compressor inlet guide blades is limited by cooling of intake air and associated risk of icing, then machine integrity is protected, but the operational range and efficiency are reduced
Solution Approach 1:
The patent applies parameter changes by using the measurement data (temperature, air humidity, pressure) to dynamically determine the actual icing point under different operating conditions. The control system adjusts the inlet guide blade position based on these changing parameters, allowing the gas turbine to operate closer to the true icing limit rather than using a conservative fixed minimum position. This expands the operational range while maintaining machine integrity through accurate, condition-based control.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution provides a more accurate and reliable prediction of icing events, allowing for effective countermeasures and a wider operational range for the gas turbine, leading to more efficient operation and reduced risk of damage.
Implementation Method 1
the acceleration of the flow downstream of the inlet guide blade row, which leads to cooling of the flow
Implementation Method 2
an icing sensor unit comprising at least one sensor arranged between a first compressor rotor blade row and a first compressor guide blade row
Implementation Method 3
at least one pressure sensor and one temperature sensor, which are both arranged between the first compressor rotor blade row and the first compressor guide blade row
Implementation Method 4
The icing sensor unit furthermore has at least one air humidity sensor
Data Source
AI summary
A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.