View source for 17835250. SYSTEM INCLUDING A THERMO-STRUCTURAL SPACER FOR AIR INLET AND COMPRESSOR INTERFACE simplified abstract (GM Global Technology Operations LLC)

=SYSTEM INCLUDING A THERMO-STRUCTURAL SPACER FOR AIR INLET AND COMPRESSOR INTERFACE=


==Organization Name==

[[:Category:GM Global Technology Operations LLC|GM Global Technology Operations LLC]]


[[Category:GM Global Technology Operations LLC]]

==Inventor(s)==

[[:Category:Abhishek Kumar Sahu of Bengaluru (IN)|Abhishek Kumar Sahu of Bengaluru (IN)]][[Category:Abhishek Kumar Sahu of Bengaluru (IN)]]

[[:Category:Saurabh Kumar Verma of Bengaluru (IN)|Saurabh Kumar Verma of Bengaluru (IN)]][[Category:Saurabh Kumar Verma of Bengaluru (IN)]]

[[:Category:Ronald Miller of Bloomfield Hills MI (US)|Ronald Miller of Bloomfield Hills MI (US)]][[Category:Ronald Miller of Bloomfield Hills MI (US)]]

==SYSTEM INCLUDING A THERMO-STRUCTURAL SPACER FOR AIR INLET AND COMPRESSOR INTERFACE - A simplified explanation of the abstract==


This abstract first appeared for US patent application 17835250 titled 'SYSTEM INCLUDING A THERMO-STRUCTURAL SPACER FOR AIR INLET AND COMPRESSOR INTERFACE

==Simplified Explanation==

The abstract describes a thermo-structural spacer that is designed to restrict heat transfer between two flanges. The spacer consists of a cylindrical center portion, a first flange connected to one end of the center portion, and a second flange connected to the other end. The spacer also includes an annular inner wall with a through hole. The center portion is narrower than both flanges.

* The thermo-structural spacer is cylindrical in shape with two flanges on either end.
* It has an annular inner wall with a through hole running through its longitudinal axis.
* The center portion of the spacer is narrower than both flanges.
* The purpose of the spacer is to restrict heat transfer between the two flanges.

Potential applications of this technology:

* Industrial machinery and equipment where heat transfer needs to be controlled.
* Automotive industry for thermal insulation between engine components.
* Aerospace industry for thermal management in aircraft structures.

Problems solved by this technology:

* Minimizes heat transfer between two flanges, preventing thermal damage or inefficiency.
* Provides a structural component that can withstand high temperatures while maintaining thermal insulation.

Benefits of this technology:

* Improved efficiency and performance of machinery and equipment.
* Enhanced thermal management and protection of sensitive components.
* Increased lifespan of equipment by reducing thermal stress.


==Original Abstract Submitted==

A thermo-structural spacer is provided. The spacer includes a cylindrical center portion, a first flange connected to a first end of the cylindrical center portion, a second flange connected to a second end of the cylindrical center portion. The second end is distal from the first end. The spacer further includes an annular inner wall configured for providing a through hole extending through a longitudinal axis of the thermo-structural spacer. The cylindrical center portion is narrower than the first flange. The cylindrical center portion is narrower than the second flange. The thermo-structural spacer is configured for restricting heat transfer between the first flange and the second flange.



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