Adjustable Bypass Flow Channel for Gas Turbine Partial Load
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Solution Overview
Problem
Gas turbines face limitations in partial load operation due to increasing CO emissions when primary zone temperature decreases, restricting power reduction and requiring periodic shutdowns or operation above minimum power levels to comply with CO emission limits.
Innovation Solution
A method for operating a gas turbine with an adjustable bypass flow channel to maintain constant relative combustion chamber pressure loss or material temperature, ensuring constant primary zone temperature and CO emission compliance, by adjusting the opening cross section of the bypass flow channel to manage compressor air flow and cooling power.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the gas turbine operates at lower partial load ranges, then power output is reduced, but CO emission increases exponentially due to decreased primary zone temperature
Solution Approach 1:
The invention changes the operating parameters by adjusting the bypass flow channel opening cross section to maintain primary zone temperature above the critical threshold even at lower power outputs. This parameter adjustment allows the turbine to operate at reduced power levels while keeping CO emissions within acceptable limits through temperature control.
Solution Approach 2:
The bypass flow channel acts as an intermediary element that introduces cooler compressor air into the combustion chamber to modulate the primary zone temperature. By controlling the amount of bypass air mixed with the hot combustion gases, the system can maintain adequate combustion temperatures at partial load conditions, preventing exponential CO emission increases.
2Object-generated harmful factors
If the primary zone temperature is maintained constant by adjusting bypass flow channel, then CO emission is controlled, but the control relies on predetermined assumptions since primary zone temperature cannot be measured directly
Solution Approach 1:
The invention replaces direct thermal measurement in the high-temperature combustion zone with indirect measurement using a cooled probe that can withstand the thermal environment. The probe measures temperature downstream where conditions are more manageable, and this information is used to control the bypass flow channel opening, substituting direct measurement with an indirect but controllable measurement approach.
Solution Approach 2:
The system implements feedback control by continuously measuring the primary zone temperature (or a related parameter) and adjusting the bypass flow channel opening cross section accordingly. The measured temperature information feeds back to the control mechanism, allowing dynamic adjustment of the bypass air flow to maintain the desired temperature range and control CO emissions in real-time.
3Object-generated harmful factors
If the opening cross section of bypass flow channel is adjusted to maintain constant primary zone temperature, then CO emission limit compliance is achieved, but the variation rate of opening cross section must be controlled to avoid thermal damage
Solution Approach 1:
The invention employs dynamic control of the bypass flow channel opening cross section, allowing it to vary in response to changing operating conditions while maintaining the primary zone temperature within acceptable limits. The opening cross section is adjusted dynamically based on real-time temperature measurements and power demand, enabling the system to adapt to varying load conditions without causing thermal damage to combustion chamber components.
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
Enables extended partial load range operation without exceeding CO emission limits, ensuring reliable and efficient gas turbine operation even at low power levels while preventing thermal damage to combustion chamber components.
Implementation Method 1
a bypass flow channel furthermore being provided, which is configured in order to deliver compressor air past the burner and to a hot gas flow generated in the combustion chamber
Implementation Method 2
a combustion chamber provided with a burner
Data Source
AI summary
A gas turbine has a compressor providing compressed air, a combustion chamber provided with a burner, and an expansion turbine, wherein a bypass flow channel is also provided designed to supply compressed air past the burner and to supply a hot gas flow generated in the combustion chamber during operation of the gas turbine. The opening cross section of the bypass flow channel can be adjusted, and an adjustment unit is designed to adjust the opening cross section of the bypass flow channel such that the modification speed of the opening cross section is selected such that the relative combustion chamber pressure drop or a material temperature of the combustion chamber is substantially constant, in particular that the relative combustion chamber pressure drop or the material temperature of the combustion chamber does not vary by more than 10%.