Gas Turbine Compressor Rim Cooling via Tangential Fluid Injection
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Solution Overview
Problem
Gas turbine engine compressors face challenges in thermal management due to increasing compressor exit discharge pressures and temperatures, which approach the limits of material capabilities, necessitating effective cooling solutions to maintain performance and efficiency.
Innovation Solution
A thermal management system is implemented for the rim section of a high-pressure compressor rotor, utilizing a tangential onboard injector system with component cooling fluid transfer tubes and a plenum cooling fluid source, where the cooling fluid is disposed within the core flow or bypass flow, and extends through exhaust guide vanes to efficiently cool the rim section without generating excessive turbulence or pressure losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If compressor exit discharge pressures and temperatures are increased to improve performance and efficiency, then engine performance is improved, but material capability limits are approached
Solution Approach 1:
The rim section is divided into multiple cooling zones with separate cooling fluid passages, allowing different temperature and pressure conditions to be applied to different segments. This enables the component to handle higher overall temperatures while protecting critical areas through localized cooling.
Solution Approach 2:
A cooling fluid acts as an intermediary substance, absorbing thermal energy from the rim section through heat exchange surfaces and transporting it away. This mediator enables the rim to operate at higher temperatures without exceeding material limits by continuously removing excess heat.
2Temperature
If conventional cooling methods are used, then cooling is provided, but excessive turbulence and pressure losses are generated
Solution Approach 1:
The cooling system optimizes fluid parameters including velocity, pressure, and temperature profiles through carefully designed passage geometries. By controlling these parameters, the system achieves effective cooling while minimizing turbulence and pressure losses that would otherwise reduce compressor efficiency.
Solution Approach 2:
The cooling fluid passages incorporate curved and streamlined geometries rather than sharp angles or straight transitions. These curved paths reduce flow separation and turbulence, allowing cooling fluid to move efficiently through the rim section with minimal pressure loss.
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 manages thermal energy by directing cooling fluid in a tangential manner relative to the rotating rim section, facilitating efficient mixing and reducing thermal stress, thereby enhancing the operational efficiency and longevity of the compressor components.
Implementation Method 1
The system effectively manages thermal energy by directing cooling fluid in a tangential manner relative to the rotating rim section
Implementation Method 2
facilitating efficient mixing and reducing thermal stress
Data Source
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Figure 2A
Figure 2B
AI summary
A thermal management system (230) for a component of a gas turbine engine (20) is disclosed. In various embodiments, the thermal management system (230) includes a manifold (238) extending circumferentially about a longitudinal axis (A) and defining a plenum (240); a cooling fluid transfer tube (236) disposed within the plenum (240) and configured to transfer a component cooling fluid from a component cooling fluid source to the component; and a cooling fluid passageway (244) connected to the manifold (238) and configured to transfer a plenum cooling fluid from a plenum cooling fluid source to the plenum (240).