Fluid Injector for Gas Turbine Compressor Cooling
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Solution Overview
Problem
Gas turbine engine compressor sections, particularly high-pressure compressors, face reduced service lifetime due to prolonged exposure to high temperatures, limiting their ability to generate high pressures and efficiency.
Innovation Solution
A fluid injector system with an annular rim and cascading nozzles is used to direct a thermal management flow that is cooled by a heat exchanger, ensuring efficient mixing and temperature reduction within the compressor section, minimizing turbulence and pressure losses, and featuring a tangential on-board injector design with radial guides and balanced static pressures to prevent air leakage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If cooling arrangements are employed to reduce temperatures of compressor components, then service lifetime is extended, but device complexity increases
Solution Approach 1:
The system uses a portion of the compressor's own compressed air flow as the cooling fluid, eliminating the need for external cooling systems. The cooling air is bled from the compressor discharge and redirected through injectors to cool critical components, allowing the system to cool itself using its own operational resources.
Solution Approach 2:
The compressed air serves multiple functions: it performs the primary compression function and simultaneously serves as the cooling medium. The same air that is compressed to generate pressure is also used to cool the compressor components, reducing the need for separate cooling systems and simplifying the overall design.
2Temperature
If cooling fluid is introduced into the compressor section, then temperature gradients are reduced, but pressure losses increase
Solution Approach 1:
The cooling injectors are positioned to deliver cooling fluid specifically to critical high-temperature zones such as the compressor housing and bearing areas. The cooling is applied locally where heat generation is highest rather than uniformly throughout the compressor section, minimizing interference with the main compression flow and reducing pressure losses.
Solution Approach 2:
The cooling air acts as an intermediary medium that absorbs heat from critical components through the injector system. By introducing this intermediate cooling flow in controlled amounts and locations, heat is removed from the compressor section without directly interfering with the main compression process, thus limiting pressure losses.
3Productivity
If high operating pressures are maintained to improve efficiency, then engine efficiency increases, but component temperatures increase reducing service lifetime
Solution Approach 1:
Cooling air is prepared in advance by bleeding it from the compressor discharge where it is hot and high-pressure, then it is routed through the injector system before being introduced to cool critical components. This preliminary preparation of the cooling fluid ensures it is ready to immediately counteract heat generation in high-stress areas, allowing the compressor to maintain high operating pressures without compromising component life.
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 reduces temperature gradients and extends component lifetimes while maintaining high-pressure generation capabilities, improving overall engine efficiency with a compact and lightweight design.
Implementation Method 1
the flow to the fluid injector is supplied by an aftmost compressor stage of a high pressure compressor
Implementation Method 2
A fluid injector system with an annular rim and cascading nozzles is used to direct a thermal management flow that is cooled by a heat exchanger
Implementation Method 3
ensuring efficient mixing and temperature reduction within the compressor section
Data Source
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AI summary
An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.