Turbine Engine Auxiliary Coolant Injection for Transient Heat Control
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Solution Overview
Problem
Gas turbine engines face challenges in maintaining operational life and performance due to excessive air temperatures in main and cooling flows, which can limit operational ranges and speeds.
Innovation Solution
The proposed solution involves an aircraft propulsion system with a core engine that includes a coolant chamber and at least one coolant flow regulator. The coolant is distributed into the core flow path to maintain operating temperatures within defined limits, allowing for increased power output during transient cooling demands.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If coolant is continuously distributed into the core flow path, then operating temperatures are maintained within limits, but engine performance and power output are reduced
Solution Approach 1:
The system implements periodic coolant injection by controlling the coolant flow regulator to distribute coolant during specific operating periods (e.g., transient high-temperature conditions) and halt injection during other periods, thereby maintaining temperature control while minimizing impact on power output
2Temperature
If coolant flow is increased to meet transient cooling demands, then temperature control is improved, but operational range and speed are limited
Solution Approach 1:
The system dynamically adjusts coolant flow rate in response to real-time operating conditions through the coolant flow regulator, enabling the engine to adapt to varying temperature demands across different operational ranges and speeds without being constrained by fixed cooling capacity
3Duration of action of stationary object
If coolant is injected into the core flow path, then component operational life is extended, but system complexity increases
Solution Approach 1:
The system utilizes the engine's own operational parameters (temperature, pressure, flow conditions) to control coolant injection timing and rate, allowing the system to self-regulate cooling requirements without external intervention or complex control systems
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 effectively extends the operational life of engine components, enhances performance, and increases operational ranges and speeds by managing temperatures and power output efficiently.
Implementation Method 1
a coolant chamber where a quantity of coolant is stored, and at least one coolant flow regulator for distributing coolant from the coolant chamber to a location within the core flow path of the engine
Data Source
AI summary
An aircraft propulsion system includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with fuel, and ignited to generate a gas flow that is expanded through a turbine section. A coolant is stored in a coolant chamber and is distributed to a location within the core flow path of the engine through a coolant flow regulator during engine operation.