Active Core Cooling Via Valves for Uniform HPC Thermal Expansion
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Solution Overview
Problem
Gas turbine engines experience thermal inequality leading to unequal thermal expansion, causing physical deformation and potential blade deflection in the high pressure compressor, which can result in tip strikes during engine startup.
Innovation Solution
An active core cooling system is implemented, utilizing a valve system to supply cooling air from an aircraft auxiliary power unit or ground cart to evenly cool the high pressure compressor and core flow-path components, including blades, vanes, and rotor, through a plenum and core flow-path.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the gas turbine engine operates at high temperature, then power output is improved, but thermal inequality and physical deformation occur causing blade deflection and tip strikes
Solution Approach 1:
The system performs preliminary cooling action during engine shutdown by redirecting cooling air through the high pressure compressor to equalize temperatures before startup. This preventive measure eliminates thermal inequality that would otherwise cause blade deflection and tip strikes during subsequent operation.
Solution Approach 2:
The system changes the temperature parameter distribution within the engine by introducing cooling air to specific zones. By adjusting the thermal state of the high pressure compressor components, the system prevents thermal expansion inequality that leads to blade deflection while maintaining power output capability.
2Reliability
If the engine undergoes extended idle run times to stabilize temperatures, then blade deflection is prevented, but maintenance time and operational efficiency decrease
Solution Approach 1:
The system performs the temperature stabilization action during the shutdown period rather than requiring extended idle runtime after startup. By cooling the engine during shutdown, the system achieves thermal equality before the next operation, eliminating the need for prolonged idle periods and reducing overall maintenance time.
3Manufacturing precision
If cooling air is supplied to the high pressure compressor during shutdown, then uniform cooling is achieved, but system complexity increases
Solution Approach 1:
The system uses a multi-functional valve arrangement that redirects existing cooling air for different purposes at different times. The same valve system that manages cooling during operation is repurposed to distribute cooling air uniformly during shutdown, achieving uniform cooling without adding dedicated complex cooling infrastructure.
Solution Approach 2:
The system uses its own cooling air resources to cool the high pressure compressor during shutdown. By self-regulating the distribution of cooling air through controllable valves, the system achieves uniform cooling without requiring external cooling systems or additional complex infrastructure.
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
The system ensures uniform cooling of the high pressure compressor components, reducing engine maintenance time and preventing blade deflection by maintaining uniform thermal expansion, thus enhancing engine reliability and safety.
Implementation Method 1
core cooling air may be supplied to a core flow-path of the compressor section
Implementation Method 2
evenly cool the high pressure compressor and core flow-path components
Implementation Method 3
compressor section temperatures may increase. Gas turbine engines may undergo extended idle run times following engine operation to stabilize high pressure compressor (HPC) temperatures and to prevent excessive thermal gradients
Data Source
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Figure 3~4
AI summary
Systems and methods for cooling a core flow-path of a compressor section of a gas turbine engine (210) are provided. In various embodiments, a cooling system (100) for a gas turbine engine may comprise a valve system (110) located radially outward from an engine case (130), the valve system (110) being coupled between an air duct (120) and the engine case (130), the valve system (110) having an actuation device (115) configured to at least one of open or close a valve in response to a command from an electronic engine controller (140), wherein cooling air (122) from the air duct (120) can pass through the valve system (110) and enter the engine case (130) into a high pressure compressor plenum (132) when the valve system (110) is in an open position.