Gas Turbine Nozzle Adjustment for Component Life Extension
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines experience a decrease in durability and efficiency due to increased exhaust gas temperatures as they age, leading to a faster deterioration rate and the need for premature repairs, as the high pressure turbine components' service life is significantly reduced by temperature increases.
Innovation Solution
A method and system that adjust the first stage turbine nozzle assembly and inlet guide vanes using a controller to maintain a consistent firing temperature by increasing the mass flow of air through the engine, thereby maintaining rated power output without increasing the firing temperature, thus reducing the degradation rate of turbine components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the engine controller increases the firing temperature to generate the desired output power, then the output power is maintained, but the exhaust gas temperature increases and component life decreases
Solution Approach 1:
The system changes operational parameters by adjusting the turbine nozzle area and inlet guide vane angle to modify mass flow and firing temperature, allowing the engine to maintain power output while operating at lower temperatures that extend component life
Solution Approach 2:
The system dynamically adjusts turbine nozzle area and inlet guide vane position based on real-time monitoring of exhaust gas temperature and engine performance, enabling continuous optimization of the trade-off between power output and component durability
2Device complexity
If the engine operates with fixed turbine nozzle area, then the device complexity is reduced, but the ability to maintain consistent firing temperature deteriorates
Solution Approach 1:
The turbine nozzle assembly incorporates adjustable elements that allow dynamic modification of the nozzle area during operation, enabling the system to maintain consistent firing temperature by adapting to changing engine conditions and component deterioration
Solution Approach 2:
The system uses feedback from exhaust gas temperature sensors and performance monitoring to automatically adjust turbine nozzle area and inlet guide vane position, creating a closed-loop control system that maintains optimal firing temperature despite component aging
Data Source
AI summary
A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position. A firing temperature of the gas turbine engine is determined based on the exhaust gas temperature. The firing temperature is compared to a threshold value and a difference value is determined therefrom. If the difference value exceeds a threshold value, the first stage turbine nozzle assembly is adjusted to a second position such that the firing temperature is substantially equal to the threshold value.