Gas Turbine Startup Flow Control for Thermal Management
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines face interference issues due to temperature differentials between components during startup, leading to potential rub conditions and increased startup time, which can decrease operating efficiency.
Innovation Solution
A system and method where a flow control device in a gas turbine engine conveys hot gas path air in a reverse direction through a conduit during startup to heat stationary components, reducing temperature differentials and improving component clearance, thereby accelerating startup and enhancing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the transition time is increased to reduce temperature differentials and prevent interference issues, then component clearance and reliability are improved, but startup time increases and operating efficiency decreases
Solution Approach 1:
The system performs preliminary heating of the turbine casing using hot gas path air during startup before the turbine reaches full operating temperature. This preliminary thermal conditioning prevents excessive temperature differentials and potential rub conditions between turbine components, allowing faster startup without compromising reliability.
Solution Approach 2:
Hot gas path air serves as an intermediary heating medium to transfer thermal energy to the turbine casing during startup. This intermediary approach allows controlled heating of the casing without directly exposing components to extreme temperatures, achieving thermal equilibrium faster while maintaining component clearance.
2Productivity
If the transition rate is increased to improve operating efficiency and reduce startup time, then productivity is improved, but temperature differentials increase causing interference issues
Solution Approach 1:
The system performs preliminary heating of the turbine casing using hot gas path air during startup before the turbine reaches full operating temperature. This preliminary thermal conditioning prevents excessive temperature differentials and potential rub conditions between turbine components, allowing faster startup without compromising reliability.
Solution Approach 2:
The system changes the thermal parameters of the turbine casing by introducing hot gas path air during startup. This parameter change (temperature of the casing) reduces temperature differentials between components, allowing faster transition rates without causing interference issues.
3Loss of time
If hot gas path air is used to heat turbine components during startup, then startup time is reduced and operating efficiency is improved, but device complexity increases due to flow control requirements
Solution Approach 1:
The flow control device is designed to perform multiple functions: it controls compressed air flow to the turbine during normal operation and redirects hot gas path air to the turbine casing during startup. This multi-functionality reduces the need for separate dedicated heating systems, minimizing the increase in device complexity while achieving faster startup times.
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 approach reduces startup time and improves operating efficiency by heating components with hot gas path air, minimizing interference and degradation, and allowing the gas turbine engine to reach full capacity sooner.
Implementation Method 1
heating a casing of the turbine using the flow of the gas path air through the conduit
Data Source
AI summary
A system includes a gas turbine engine, which includes a compressor configured to generate compressed air and a turbine. The turbine includes a stationary component and a conduit configured to convey the compressed air from the compressor to the stationary component in a forward direction. The gas turbine engine also includes a flow control device coupled to the conduit. The conduit is configured to convey a gas path air from the stationary component in a reverse direction opposite from the forward direction when the flow control device is in a startup mode. The gas turbine engine also includes a shaft coupled to the compressor and the turbine.