18152904. COMPRESSOR BLEED PRESSURE RECOVERY simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
COMPRESSOR BLEED PRESSURE RECOVERY
Organization Name
Inventor(s)
Kudum Shinde of Bengaluru (IN)
Yashpal Patel of Bengaluru (IN)
Sesha Subramanian of Bengaluru (IN)
Brandon C. Clarke of Milford OH (US)
COMPRESSOR BLEED PRESSURE RECOVERY - A simplified explanation of the abstract
This abstract first appeared for US patent application 18152904 titled 'COMPRESSOR BLEED PRESSURE RECOVERY
Simplified Explanation: The patent application describes a gas turbine engine with a compressor section that includes a compressor rotor shaft assembly and a stator shroud assembly. The compressor flow passage is defined between the compressor rotor shaft assembly and the stator shroud casing. The compressor bleed air system includes a compressor bleed air duct with a sloped inlet portion in the stator shroud casing.
Key Features and Innovation:
- Gas turbine engine with a unique compressor section design
- Compressor flow passage defined between rotor shaft assembly and stator shroud casing
- Compressor bleed air system with a sloped inlet portion for improved airflow
- Alternative design with stator vanes having a NACA inlet scoop for bleed air passage
Potential Applications: This technology can be applied in gas turbine engines for various industries such as aviation, power generation, and marine propulsion.
Problems Solved: This innovation addresses the need for efficient compressor flow and bleed air systems in gas turbine engines, improving overall performance and reliability.
Benefits:
- Enhanced airflow efficiency
- Improved compressor performance
- Increased engine reliability
Commercial Applications: Gas turbine manufacturers and operators can benefit from this technology by improving engine efficiency, reducing maintenance costs, and enhancing overall performance in various applications.
Prior Art: Readers interested in prior art related to this technology can explore patents and research papers on gas turbine engine compressor design and bleed air systems.
Frequently Updated Research: Stay updated on the latest advancements in gas turbine engine technology, compressor design, and bleed air systems to enhance your understanding of this innovative technology.
Questions about Gas Turbine Engine Compressor Design: 1. How does the sloped inlet portion in the stator shroud casing improve airflow efficiency? 2. What are the potential challenges in implementing this compressor design in different gas turbine engine applications?
Original Abstract Submitted
A gas turbine engine includes a compressor section having rotor shaft assembly and a stator shroud assembly including a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A compressor bleed air system includes a compressor bleed air duct that includes a sloped inlet portion, such as a NACA submerged inlet portion, in the stator shroud casing. Alternatively, stator vanes at a compressor bleed air passage may have a NACA inlet scoop and an airflow passage through the stator vane providing a bleed airflow to a cavity, which has airflow passages providing bleed air to an upstream side of the bleed air passage.
