17956881. GAS TURBINE ENGINE INCLUDING FLOW PATH FLEX SEAL AND HEAT SHIELD simplified abstract (Raytheon Technologies Corporation)
Contents
- 1 GAS TURBINE ENGINE INCLUDING FLOW PATH FLEX SEAL AND HEAT SHIELD
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 GAS TURBINE ENGINE INCLUDING FLOW PATH FLEX SEAL AND HEAT SHIELD - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Unanswered Questions
- 1.11 Original Abstract Submitted
GAS TURBINE ENGINE INCLUDING FLOW PATH FLEX SEAL AND HEAT SHIELD
Organization Name
Raytheon Technologies Corporation
Inventor(s)
Thomas E. Clark of Wells ME (US)
Marc J. Muldoon of Marlborough CT (US)
GAS TURBINE ENGINE INCLUDING FLOW PATH FLEX SEAL AND HEAT SHIELD - A simplified explanation of the abstract
This abstract first appeared for US patent application 17956881 titled 'GAS TURBINE ENGINE INCLUDING FLOW PATH FLEX SEAL AND HEAT SHIELD
Simplified Explanation
The patent application describes a gas turbine engine with a unique seal and cooling system design to improve efficiency and performance.
- The first seal in the engine spans the cooling air flowpath and includes axial convolutions and pass-through features for purge airflow.
- A heat shield positioned downstream of the first seal creates a mixing plenum for the purge airflow, enhancing cooling efficiency.
Potential Applications
The technology described in the patent application could be applied in various gas turbine engines used in power generation, aviation, and industrial applications.
Problems Solved
1. Improved cooling efficiency in gas turbine engines. 2. Enhanced performance and reliability by preventing hot gas leakage.
Benefits
1. Increased efficiency and performance. 2. Extended engine lifespan. 3. Reduced maintenance costs.
Potential Commercial Applications
"Enhancing Cooling Efficiency in Gas Turbine Engines: Applications and Benefits"
Possible Prior Art
No prior art information is provided.
Unanswered Questions
How does the design of the first seal impact overall engine efficiency?
The design of the first seal, with axial convolutions and pass-through features, helps regulate purge airflow and prevent hot gas leakage, ultimately improving engine efficiency.
What are the potential challenges in implementing this technology in existing gas turbine engines?
Some potential challenges in implementing this technology could include retrofitting older engine models and ensuring compatibility with different engine configurations.
Original Abstract Submitted
A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is disposed radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features defining a purge airflow. A heat shield is positioned immediately downstream of the first seal and is configured in relation to the first seal such that the purge airflow enters a mixing plenum defined between the heat shield and the first seal.
