20240026820. SUMP ARRANGEMENT FOR A GAS TURBINE ENGINE simplified abstract (General Electric Company)
Contents
SUMP ARRANGEMENT FOR A GAS TURBINE ENGINE
Organization Name
Inventor(s)
Vaishnav Raghuvaran of Bengaluru (IN)
Rajesh Kumar of Bengaluru (IN)
Scott Alan Schimmels of Miamisburg OH (US)
SUMP ARRANGEMENT FOR A GAS TURBINE ENGINE - A simplified explanation of the abstract
This abstract first appeared for US patent application 20240026820 titled 'SUMP ARRANGEMENT FOR A GAS TURBINE ENGINE
Simplified Explanation
The abstract describes a gas turbine engine that consists of a compressor section and a turbine section. The turbine section includes a high pressure turbine, a low pressure turbine, and a sump positioned between them. There is also a rotating cross flow arrangement that connects the compressor to the sump through multiple guiding passages.
- The gas turbine engine includes a compressor section and a turbine section.
- The turbine section consists of a high pressure turbine and a low pressure turbine.
- A sump is located between the high pressure turbine and the low pressure turbine.
- The compressor is fluidly coupled to the sump through a rotating cross flow arrangement.
- The rotating cross flow arrangement includes multiple guiding passages.
Potential applications of this technology:
- Gas turbine engines are commonly used in aircraft propulsion systems, so this innovation could be applied to improve the efficiency and performance of aircraft engines.
- Gas turbine engines are also used in power generation, so this technology could be utilized to enhance the efficiency and reliability of power plants.
Problems solved by this technology:
- The rotating cross flow arrangement and guiding passages help to optimize the flow of air between the compressor and the sump, improving the overall efficiency of the gas turbine engine.
- The sump positioned between the high pressure turbine and the low pressure turbine helps to regulate the flow of air and prevent any disruptions or inefficiencies in the turbine section.
Benefits of this technology:
- Improved efficiency: The optimized flow of air between the compressor and the sump helps to maximize the energy conversion in the gas turbine engine, resulting in improved fuel efficiency.
- Enhanced performance: The design of the turbine section, including the high pressure turbine, low pressure turbine, and sump, allows for better control and regulation of the airflow, leading to improved overall performance of the gas turbine engine.
- Increased reliability: The rotating cross flow arrangement and guiding passages help to ensure a smooth and consistent flow of air, reducing the risk of disruptions or failures in the gas turbine engine.
Original Abstract Submitted
a gas turbine engine including a compressor section including a compressor and a turbine section located downstream of the compressor section. the turbine section including a high pressure turbine, a low pressure turbine, a sump positioned between the high pressure turbine and the low pressure turbine, and a rotating cross flow arrangement defining a plurality of guiding passages fluidly coupling the compressor to the sump.
