Gas Turbine Flow Injection for Cooling and Thrust
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Solution Overview
Problem
Gas turbine engines with multiple flow paths face challenges in efficiently routing and controlling flow between bypass and core flow paths to optimize propulsive efficiency and thermal management.
Innovation Solution
The implementation of a flow injection device that selectively communicates different amounts of flow from a bypass flow path to the exhaust section of a gas turbine engine, utilizing an array of vanes distributed annularly to introduce bypass flow radially across the fan discharge bypass flow path, enhancing cooling and thrust augmentation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If bypass flow is selectively injected into the exhaust section, then cooling efficiency and thrust augmentation are improved, but device complexity increases due to the flow injection device
Solution Approach 1:
The flow injection device is segmented into multiple independently controllable flow passages, each with its own actuator. This allows selective injection of bypass flow into different regions of the exhaust section, enabling targeted cooling of specific hot spots while maintaining overall system manageability despite the added complexity
Solution Approach 2:
The flow injection device serves multiple functions simultaneously: it provides cooling to the exhaust section, augments thrust by injecting bypass flow into the core exhaust, and enables adaptive flow control based on operating conditions. This multi-functionality justifies the added device complexity by delivering multiple performance benefits from a single system
2Power
If bypass flow is selectively injected into the exhaust section, then thrust augmentation is improved, but device complexity increases due to the flow injection device
Solution Approach 1:
The flow injection device incorporates dynamically controllable flow passages with actuators that can adjust the amount of bypass flow injected into the exhaust section in real-time. This dynamic control enables thrust augmentation to be optimized across varying flight conditions, from takeoff to cruise, making the added complexity worthwhile by delivering adaptive performance enhancement
Solution Approach 2:
The system changes operational parameters by varying the degree of bypass flow injection into the exhaust section based on flight conditions. During takeoff, maximum injection provides thrust augmentation, while during cruise, reduced or zero injection optimizes fuel efficiency. This parameter adjustment capability justifies the complex device structure
3Adaptability or versatility
If multiple bypass flow paths are implemented, then flow control flexibility is improved, but device complexity increases due to multiple ducts and routing
Solution Approach 1:
The bypass system is segmented into multiple distinct flow paths: a primary bypass duct for high-bypass ratio operation and a secondary bypass duct with flow injection capability for thrust augmentation and cooling. Each duct serves specific operational regimes, providing flexibility while maintaining clear functional separation that manages overall system complexity
Solution Approach 2:
The flow injection device acts as an intermediary between the secondary bypass duct and the exhaust section, mediating the injection of bypass flow into the core exhaust. This intermediary structure enables controlled interaction between bypass and core flows, providing adaptability for different operating modes without requiring direct complex routing between all 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
This solution allows for adaptive control of flow to optimize engine performance by enhancing cooling and thrust generation, improving power density and efficiency by selectively directing bypass flow into the core flow path, thereby addressing the inefficiencies in existing gas turbine engine architectures.
Implementation Method 1
a flow injection device to selectively communicate a first amount of flow or a second amount of flow from the bypass flow path to the exhaust section
Data Source
AI summary
A method of communicating flow through a gas turbine engine having multiple flow paths according to an exemplary embodiment of the present disclosure includes moving core flow along a core flow path from a compressor section to an exhaust section, selectively communicating a first amount of bypass flow from a bypass flow path defined by a bypass duct to the exhaust section or a second amount of bypass flow from the bypass flow path to the exhaust section, the first amount different than the second amount.