18081217. SYSTEM AND METHOD FOR PROVIDING COOLING IN A COMPRESSOR SECTION OF A GAS TURBINE ENGINE simplified abstract (General Electric Company)
SYSTEM AND METHOD FOR PROVIDING COOLING IN A COMPRESSOR SECTION OF A GAS TURBINE ENGINE
Organization Name
Inventor(s)
Pankaj Dhaka of Bengaluru (IN)
Kudum Shinde of Bengaluru (IN)
Vidyashankar Ramasastry Buravalla of Bengaluru (IN)
SYSTEM AND METHOD FOR PROVIDING COOLING IN A COMPRESSOR SECTION OF A GAS TURBINE ENGINE - A simplified explanation of the abstract
This abstract first appeared for US patent application 18081217 titled 'SYSTEM AND METHOD FOR PROVIDING COOLING IN A COMPRESSOR SECTION OF A GAS TURBINE ENGINE
Simplified Explanation
The patent application describes a method for cooling the compressor section of a gas turbine engine.
- The method involves using temperature sensors to measure the temperature at two different locations on a stationary assembly of the compressor section.
- The temperature difference between the two locations is then calculated by a controller.
- If the temperature difference exceeds a predetermined threshold, the controller activates cooling elements located at the first location of the compressor section.
Potential applications of this technology:
- Gas turbine engines used in aircraft, power plants, and other industrial applications could benefit from this cooling method.
Problems solved by this technology:
- Gas turbine engines generate a significant amount of heat, and excessive temperatures in the compressor section can lead to reduced efficiency and potential damage. This cooling method helps to prevent overheating and maintain optimal operating conditions.
Benefits of this technology:
- Improved efficiency: By preventing overheating, the cooling method helps to maintain the optimal performance of the gas turbine engine.
- Increased lifespan: By controlling the temperature in the compressor section, the cooling method can help extend the lifespan of the engine components.
- Enhanced safety: By preventing excessive temperatures, the cooling method reduces the risk of engine failure and potential safety hazards.
Original Abstract Submitted
A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.
