Gas Turbine Vane Ring Cooling via Intermediate Air Extraction
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Solution Overview
Problem
Existing gas turbine systems face inefficiencies due to high equipment costs and ineffective use of compressed air with high temperature and pressure, as they require cooling systems that divert valuable energy resources.
Innovation Solution
A gas turbine design that extracts compressed air from an intermediate compression stage to cool specific components of the turbine casing, allowing for effective use of high-temperature air for combustion while minimizing equipment costs by avoiding the need for external cooling systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If compressed air is cooled by a cooler and boosted by a booster to cool vane rings, then the tip clearance can be adjusted, but the equipment cost increases
Solution Approach 1:
The patent extracts compressed air from an intermediate compression stage of the compressor and uses it directly for cooling the vane rings, eliminating the need for a separate cooler and booster system. This extraction approach maintains the cooling function while removing unnecessary equipment.
Solution Approach 2:
The compressor's own compressed air is used to cool the vane rings, making the system self-sufficient. The high-temperature compressed air from the intermediate stage serves dual purposes: it can be used for combustion or directly for cooling, eliminating the need for external cooling systems.
2Temperature
If high-temperature and high-pressure compressed air is cooled for vane ring cooling, then the vane rings can be temperature-controlled, but the effective use of compressed air for combustion is reduced
Solution Approach 1:
The patent applies local quality by using high-temperature compressed air specifically for cooling the vane rings where it is needed, rather than uniformly cooling all compressed air. The extraction line delivers compressed air directly to the vane rings that require temperature control, maintaining optimal conditions for both cooling and combustion.
Solution Approach 2:
The patent changes the parameters of the compressed air by extracting it at an intermediate compression stage where it has moderate temperature and pressure, rather than cooling it further. This parameter optimization allows the air to be effectively used for both cooling the vane rings and subsequent combustion processes.
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 approach enhances gas turbine performance by reducing steady clearance, preventing thermal expansion, and effectively utilizing high-temperature compressed air for combustion, thereby decreasing equipment costs and improving operational efficiency.
Implementation Method 1
an extraction line through which the compressed air from an intermediate compression stage among the plurality of compression stages is extracted as an extraction air and the extraction air is introduced to a first component configuring a portion of the turbine casing
Data Source
AI summary
A gas turbine includes a compressor, a turbine, an extraction line, and a component introduction line. A compressed air from an intermediate compression stage of the compressor, as an extraction air, is extracted through the extraction line and is introduced to a first component configuring a portion of the turbine casing through the extraction line. The extraction air, which has passed through the first component, is introduced to a second component serving as a component configuring the turbine through the component introduction line. The second component is a low-pressure component, which is disposed under a pressure environment lower than a pressure of the compressed air at an outlet of the intermediate compression stage.