18379433. TURBINE BLADE TIP SHROUD WITH AXIALLY OFFSET CUTTER TEETH, AND RELATED SURFACE PROFILES AND METHOD simplified abstract (General Electric Company)
Contents
- 1 TURBINE BLADE TIP SHROUD WITH AXIALLY OFFSET CUTTER TEETH, AND RELATED SURFACE PROFILES AND METHOD
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 TURBINE BLADE TIP SHROUD WITH AXIALLY OFFSET CUTTER TEETH, AND RELATED SURFACE PROFILES AND METHOD - 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 Original Abstract Submitted
TURBINE BLADE TIP SHROUD WITH AXIALLY OFFSET CUTTER TEETH, AND RELATED SURFACE PROFILES AND METHOD
Organization Name
Inventor(s)
Srinivasa Govardhan Jayana of Bangalore (IN)
Richard Ryan Pilson of Greer SC (US)
William Scott Zemitis of Simpsonville SC (US)
TURBINE BLADE TIP SHROUD WITH AXIALLY OFFSET CUTTER TEETH, AND RELATED SURFACE PROFILES AND METHOD - A simplified explanation of the abstract
This abstract first appeared for US patent application 18379433 titled 'TURBINE BLADE TIP SHROUD WITH AXIALLY OFFSET CUTTER TEETH, AND RELATED SURFACE PROFILES AND METHOD
Simplified Explanation
The patent application describes a turbine blade tip shroud with two cutter teeth axially offset from each other, one on each side of the tip rail near the leading edge of the body.
- The turbine blade tip shroud has a first cutter tooth and a second cutter tooth axially offset from each other.
- The cutter teeth are positioned on opposite sides of the tip rail near the leading edge of the body.
- The tip shroud can be manufactured with this design or modified from a used tip shroud with opposing cutter teeth near the leading edge.
Potential Applications
This technology could be applied in the aerospace industry for improving the efficiency and performance of turbine blades in aircraft engines.
Problems Solved
This innovation helps reduce wear and tear on turbine blade tip shrouds, leading to longer lifespan and improved overall performance of the turbine blades.
Benefits
- Increased durability and longevity of turbine blade tip shrouds - Enhanced efficiency and performance of turbine blades - Potential cost savings from reduced maintenance and replacement needs
Potential Commercial Applications
Optimizing turbine blade tip shrouds for aircraft engines
Possible Prior Art
There may be prior art related to turbine blade tip shrouds with cutter teeth, but specific examples are not provided in the patent application.
Unanswered Questions
How does this technology compare to existing turbine blade tip shroud designs in terms of performance and durability?
This article does not provide a direct comparison with existing designs, making it difficult to assess the advantages of this innovation over current technologies.
What are the specific manufacturing processes involved in creating or modifying the turbine blade tip shroud with axially offset cutter teeth?
The patent application does not detail the manufacturing methods used to produce or modify the turbine blade tip shroud, leaving a gap in understanding the practical implementation of this technology.
Original Abstract Submitted
A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.
