Compressed Air Bleed Supply for Gas Turbine Buffer System
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing buffer systems for gas turbine engines face challenges in efficiently providing cooled pressurized air to multiple remote areas, including bearing compartments, with existing systems either relying on a single compressor stage or separate centrifugal compressors, which may not effectively manage airflow pressures and temperatures across different components.
Innovation Solution
A buffer system incorporating a heat exchanger with multiple air sources, where the first and second air sources are selectively coupled to the heat exchanger's inlets, and a third air source is used to provide cooled pressurized air to multiple fluid-supplied areas, including bearing compartments, with a valve regulating airflow from these sources to optimize pressure and temperature states.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single compressor stage is used to provide buffer air, then the system structure is simple, but it cannot effectively manage airflow pressures and temperatures across different remote components
Solution Approach 1:
The buffer system is segmented into multiple independent air sources (first air source from high compressor stage, second air source from low compressor stage, third air source from dedicated centrifugal compressor), each capable of providing air at different pressure and temperature levels to different remote components. This segmentation allows effective management of airflow to multiple bearing compartments and other remote areas while maintaining system reliability.
2Reliability
If a dedicated centrifugal compressor is used to provide pressurized air to multiple bearing compartments, then airflow pressure and temperature management is improved, but the device complexity increases
Solution Approach 1:
The system merges multiple air source options into a single integrated buffer system architecture. The first air source (high compressor stage), second air source (low compressor stage), and third air source (dedicated centrifugal compressor) are all integrated into the same heat exchanger and distribution network, allowing flexible selection and combination of air sources based on operational requirements without requiring separate independent systems.
Solution Approach 2:
The buffer system is designed with multi-functionality to serve multiple remote components (bearing compartments, shafts, rotors) using a single integrated system. The heat exchanger can process air from any of the three air sources, and the regulated air can be distributed to any combination of remote fluid-supplied areas, making the system universally applicable to various engine configurations and operational conditions.
3Reliability
If air is provided to multiple remote fluid-supplied areas, then comprehensive thermal conditioning is achieved, but the system complexity and valve regulation requirements increase
Solution Approach 1:
The valve system is designed to be dynamic and adaptable, allowing regulation of air flow from multiple air sources to multiple remote components based on real-time operational requirements. The valve can selectively control which air source supplies which remote area, enabling flexible adjustment of pressure and temperature conditions for different bearing compartments and components during various engine operating conditions.
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 effectively provides cooled pressurized air to remote areas within the gas turbine engine, enhancing airflow management and thermal conditioning for components like rotors and shafts, improving the engine's operational efficiency and reliability.
Implementation Method 1
a heat exchanger having a first inlet, a first outlet, a second inlet, and a second outlet. The first outlet is configured to provide a cooled pressurized fluid
Data Source
AI summary
A method of designing a buffer system for a gas turbine engine according to an example of the present disclosure includes, among other things, configuring a heat exchanger to define a first inlet and a first outlet fluidly coupled to each other and a second inlet and a second outlet fluidly coupled to each other, configuring the first inlet to receive air from first and second air sources that are selectively fluidly coupled to the first inlet, configuring the second inlet to receive air from a third air source fluidly that is coupled to the second inlet, and configuring the first outlet to provide cooled pressurized air to multiple fluid-supplied areas that are located remotely from one another and that are fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment of a gas turbine engine.