18071060. MACHINABLE COATING FOR CMC AND METAL INTERFACE IN A TURBINE SECTION simplified abstract (Raytheon Technologies Corporation)
Contents
- 1 MACHINABLE COATING FOR CMC AND METAL INTERFACE IN A TURBINE SECTION
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 MACHINABLE COATING FOR CMC AND METAL INTERFACE IN A TURBINE SECTION - 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
MACHINABLE COATING FOR CMC AND METAL INTERFACE IN A TURBINE SECTION
Organization Name
Raytheon Technologies Corporation
Inventor(s)
Daniel S. Rogers of Lyman ME (US)
Robert A. White, Iii of Meriden CT (US)
MACHINABLE COATING FOR CMC AND METAL INTERFACE IN A TURBINE SECTION - A simplified explanation of the abstract
This abstract first appeared for US patent application 18071060 titled 'MACHINABLE COATING FOR CMC AND METAL INTERFACE IN A TURBINE SECTION
Simplified Explanation
The gas turbine engine turbine blade described in the patent application includes a turbine blade body with an inner platform and an airfoil extending radially outwardly. The airfoil has a leading edge, a trailing edge, a suction wall, and a pressure wall. The turbine blade body has mount structure with at least one circumferentially outwardly extending mount portion on both the suction wall side and the pressure wall side, each with a radially outer face. The turbine blade body is made of a polymer, metal, or ceramic matrix composite, and there is a protective coating on the radially outer faces of the mount portions.
- The turbine blade body includes an inner platform and an airfoil with leading and trailing edges, suction and pressure walls.
- Mount structure on both sides of the turbine blade body includes outwardly extending mount portions with protective coatings.
- The turbine blade body is made of a polymer, metal, or ceramic matrix composite.
Potential Applications
This technology could be applied in the aerospace industry for gas turbine engines, specifically in improving the performance and durability of turbine blades.
Problems Solved
1. Enhanced durability and performance of gas turbine engine turbine blades. 2. Protection against wear and tear in high-temperature environments.
Benefits
1. Increased efficiency and reliability of gas turbine engines. 2. Extended lifespan of turbine blades. 3. Improved overall performance of gas turbine engines.
Potential Commercial Applications
Optimizing Gas Turbine Engine Turbine Blades for Enhanced Performance and Durability
Possible Prior Art
Prior art related to protective coatings on turbine blade mount portions and the use of polymer, metal, or ceramic matrix composites in turbine blade bodies may exist in the field of aerospace engineering and materials science.
Unanswered Questions
How does the protective coating on the mount portions affect the overall performance of the turbine blade?
The article does not delve into the specific impact of the protective coating on the mount portions on the turbine blade's performance and durability.
What are the specific advantages of using a polymer, metal, or ceramic matrix composite in the turbine blade body?
The article mentions the materials used in the turbine blade body but does not elaborate on the unique benefits of each type of composite material.
Original Abstract Submitted
A gas turbine engine turbine blade includes a turbine blade body including an inner platform. An airfoil extends radially outwardly of the inner platform. The airfoil has a leading edge and a trailing edge, and a suction wall and a pressure wall. The turbine blade body has mount structure including at least one circumferentially outwardly extending mount portion on a suction wall side and a pressure wall side each having a radially outer face. The turbine blade body is formed of one of a polymer, metal or ceramic matrix composite. There is a protective coating on the radially outer faces of the at least one enlarged mount portions. A gas turbine engine is also disclosed.
