Downstream Turbine Vane Cooling System with Dual Airflow Paths
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Solution Overview
Problem
Downstream turbine vanes in gas turbine engines face challenges in achieving adequate cooling, as existing cooling systems often rely on a single pressure source, which may not be sufficient for high-temperature conditions and can lead to inefficiencies at lower power operations.
Innovation Solution
A cooling system that utilizes two controllable valves and a cooling compressor to manage airflow pressure, allowing for multiple operating modes: high-pressure airflow delivery during high-power conditions and reduced-pressure airflow delivery during lower power conditions, optimizing cooling potential and efficiency across varying operational states.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a single pressure cooling system is used for downstream turbine vanes, then the system structure is simple, but adequate cooling cannot be achieved during high-power operations
Solution Approach 1:
The cooling system is segmented into two distinct airflow paths: a first cooling airflow path that includes a compressor and delivers high-pressure cooling air, and a second cooling airflow path that delivers lower-pressure cooling air. This segmentation allows each path to be optimized for different operating conditions, resolving the contradiction between cooling effectiveness and system simplicity.
Solution Approach 2:
The system dynamically switches between single-path and dual-path cooling modes based on engine power conditions. During high-power operations, both cooling paths operate simultaneously to provide adequate cooling; during lower-power operations, only one path operates. This dynamic adaptation resolves the contradiction by providing high cooling capacity only when necessary.
2Temperature
If high-pressure cooling air is delivered continuously to downstream turbine vanes, then cooling effectiveness is maintained, but energy consumption increases at lower power conditions
Solution Approach 1:
The system dynamically adjusts the number of active cooling paths based on engine power conditions. During high-power operations, both the first and second cooling airflow paths are activated to ensure adequate cooling. During lower-power operations, only one path remains active, reducing energy consumption while maintaining sufficient cooling effectiveness.
Solution Approach 2:
The system changes the operational parameters (number of active cooling paths, airflow pressure levels) based on engine operating conditions. This allows the cooling system to match its energy input to the actual cooling demand, resolving the contradiction between maintaining cooling effectiveness and reducing energy consumption at part power.
3Adaptability or versatility
If a single cooling airflow path is used, then the system is simple to operate, but cooling adequacy cannot be adjusted for varying power conditions
Solution Approach 1:
The cooling system is divided into segmentable cooling paths with independent control capabilities. This segmentation enables flexible combination and disconnection of cooling paths, providing adaptability for different power conditions while keeping the base structure relatively simple.
Solution Approach 2:
The cooling system is designed with multi-functionality, where the same infrastructure supports both single-path and dual-path cooling modes. This universal design allows the system to adapt to varying cooling demands without requiring completely different configurations for different 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 adequate cooling to downstream turbine components during high-power operations while minimizing energy consumption and pressure loss at lower power conditions, enhancing overall engine efficiency and fuel consumption.
Implementation Method 1
a first airflow to a cooling compressor, and means for compressing the first airflow under high power operation of the gas turbine engine, and not compressing the first airflow under lower power operation of the gas turbine engine
Implementation Method 2
passing the cooled air from the first tap and the second tap into a line leading to the downstream turbine component
Data Source
Figure 1
Figure 2A~4
AI summary
A gas turbine engine (20) includes a main compressor section (110) and a turbine section (28). The turbine section (28) has a first turbine blade and vane (102) and a downstream turbine component. A tap (112) is configured to tap air from the compressor section (110) at a location upstream of a most downstream location (114). The tap (112) is connected to a heat exchanger (116). The heat exchanger (116) is connected to a cooling compressor (120). The cooling compressor (120) is connected to the downstream turbine component. A second tap (126) is configured to tap air from a location in the main compressor section (110). The second tap (126) is connected through a check valve (128) to a line (132) leading to the downstream turbine component. A control (138) operates the cooling compressor (120) such that when the cooling compressor (120) is operating, air downstream of the cooling compressor (120) is at a pressure higher than the pressure of the second tap (126), and the control (138) is operational to selectively drive the cooling compressor (120) at high power operation of an associated gas turbine engine (20), and to stop operation of the cooling compressor (120) at lower power operations, such that air is delivered through the cooling compressor (120) to the downstream turbine component at the high power operations, and air is delivered from the second tap (126) at least some time when the cooling compressor (120) is not operational. A method is also disclosed.