Turbine Compressor Cooling via Upstream Fluid Injection
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The challenge is to increase the overall pressure ratio of a gas turbine engine while managing the heightened temperatures that come with it, as existing materials used in the compressor section are not designed to withstand these increased temperatures.
Innovation Solution
A cooling system is introduced that includes a fluid line assembly with an outlet positioned upstream of the high-pressure compressor, injecting cooling fluid into the airflow to reduce the temperature of the compressed air, thereby mitigating the risk of exceeding temperature limits.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the overall pressure ratio of the gas turbine engine is increased, then the efficiency of the gas turbine engine is improved, but the temperature of the compressed air increases beyond the withstand capability of existing materials
Solution Approach 1:
The cooling fluid is injected into the airflow before the air enters the compressor section, pre-cooling the air in advance. This preliminary cooling action allows the compressor to handle higher pressure ratios without the compressed air temperature exceeding material withstand limits, thereby resolving the contradiction between improved efficiency and excessive temperature.
2Temperature
If cooling fluid is injected upstream of the high pressure compressor, then the temperature of the compressed air is reduced, but the complexity of the cooling system increases
Solution Approach 1:
A cooling fluid serves as an intermediary substance to transfer heat away from the compressed air. The fluid line assembly delivers this intermediary cooling fluid to the airflow, enabling temperature reduction without requiring direct mechanical cooling of the compressor components themselves, thus managing the complexity trade-off.
3Productivity
If materials in the compressor section are designed to withstand higher temperatures, then the overall pressure ratio can be increased, but the cost and complexity of material selection and manufacturing increase
Solution Approach 1:
Instead of allowing the harmful high temperature to persist and requiring expensive heat-resistant materials, the invention converts the temperature issue into a benefit by actively cooling the air before compression. This approach uses readily available materials while achieving higher pressure ratios, transforming the temperature challenge into an opportunity for cost-effective design.
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 allows the compressor section to operate at a higher overall compressor ratio with reduced risk of temperature-related issues, ensuring efficient engine operation.
Implementation Method 1
a fluid line assembly including an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor
Data Source
AI summary
A gas turbine engine includes a compressor section having a high pressure compressor and a core casing surrounding the compressor section and defining an inlet. The gas turbine engine also includes a cooling system for cooling air in or to the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and a fluid line assembly in fluid communication with the fluid tank. The fluid line assembly includes an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor.