TURBINE ENGINE SHROUD WITH NEAR WALL COOLING

Organization Name

Inventor(s)

Kirk D. Gallier of Liberty Township OH (US)

Robert Charles Groves, Ii of West Chester OH (US)

TURBINE ENGINE SHROUD WITH NEAR WALL COOLING - A simplified explanation of the abstract

This abstract first appeared for US patent application 18676779 titled 'TURBINE ENGINE SHROUD WITH NEAR WALL COOLING

The patent application describes an apparatus for a shroud assembly for a turbine engine, including one or more shroud segments with an inner face arranged around a rotating blade assembly. A near wall cooling passage is provided in the shroud assembly to cool the inner face, with the passage exhausting to a purge cavity, split line, or the inner face itself.

Shroud assembly for turbine engine
Shroud segments with inner face around rotating blade assembly
Near wall cooling passage to cool inner face
Passage exhausts to purge cavity, split line, or inner face

Potential Applications: - Aerospace industry for turbine engines - Power generation for gas turbines - Automotive industry for high-performance engines

Problems Solved: - Preventing overheating of shroud assembly - Enhancing efficiency and durability of turbine engines

Benefits: - Improved cooling capabilities - Increased performance and longevity of turbine engines - Enhanced safety and reliability in operation

Commercial Applications: Title: Advanced Shroud Assembly for Turbine Engines This technology can be utilized in commercial aircraft, power plants, and high-performance vehicles to enhance engine efficiency and reliability, leading to cost savings and improved performance in various industries.

Questions about Shroud Assembly for Turbine Engines: 1. How does the near wall cooling passage contribute to the overall performance of the turbine engine?

  The near wall cooling passage helps to prevent overheating of the shroud assembly, enhancing the efficiency and durability of the turbine engine.

2. What are the potential applications of this shroud assembly technology beyond turbine engines?

  This technology can also be applied in power generation for gas turbines and high-performance engines in the automotive industry.

Original Abstract Submitted

An apparatus for a shroud assembly for a turbine engine and a method of manufacturing such can include the shroud assembly having one or more shroud segments having an inner face in a circumferential organization around a rotating blade assembly. A near wall cooling passage can be provided in the shroud assembly to cool the inner face of the shroud. The near wall cooling passage can exhaust to a purge cavity, a split line, or at the inner face.