View source for 18130872. GAS TURBINE ENGINE WITH BYPASS TOBI COOLING/PURGE FLOW AND METHOD simplified abstract (Raytheon Technologies Corporation)

=GAS TURBINE ENGINE WITH BYPASS TOBI COOLING/PURGE FLOW AND METHOD=


==Organization Name==

[[:Category:Raytheon Technologies Corporation|Raytheon Technologies Corporation]]


[[Category:Raytheon Technologies Corporation]]

==Inventor(s)==

[[:Category:William K. Ackermann of East Hartford CT (US)|William K. Ackermann of East Hartford CT (US)]][[Category:William K. Ackermann of East Hartford CT (US)]]

[[:Category:Brian F. Hilbert of Coventry CT (US)|Brian F. Hilbert of Coventry CT (US)]][[Category:Brian F. Hilbert of Coventry CT (US)]]

[[:Category:Paul A. Sicard of East Hartford CT (US)|Paul A. Sicard of East Hartford CT (US)]][[Category:Paul A. Sicard of East Hartford CT (US)]]

[[:Category:Andrew E. Breault of Bolton CT (US)|Andrew E. Breault of Bolton CT (US)]][[Category:Andrew E. Breault of Bolton CT (US)]]

[[:Category:Rishon Saftler of Glastonbury CT (US)|Rishon Saftler of Glastonbury CT (US)]][[Category:Rishon Saftler of Glastonbury CT (US)]]

==GAS TURBINE ENGINE WITH BYPASS TOBI COOLING/PURGE FLOW AND METHOD - A simplified explanation of the abstract==


This abstract first appeared for US patent application 18130872 titled 'GAS TURBINE ENGINE WITH BYPASS TOBI COOLING/PURGE FLOW AND METHOD

'''Simplified Explanation:'''
The patent application describes a gas turbine engine with a bypass tangential on board injector (TOBI) system that allows gas to flow from the high pressure compressor (HPC) to the high pressure turbine (HPT) through different types of radial passages.

* The gas turbine engine includes a high pressure compressor, a combustor section, a high pressure turbine, and a bypass tangential on board injector (TOBI) system.
* The bypass TOBI system has multiple nozzles and radial passages that allow gas flow from the HPC to the HPT.
* The radial passages are divided into first type and second type passages with different configurations.
* The bypass TOBI system extends around the engine axial centerline to optimize gas flow efficiency.
* The design of the radial passages in the bypass TOBI system improves the overall performance of the gas turbine engine.

'''Potential Applications:'''
This technology can be applied in aircraft engines, power generation systems, and other industrial gas turbine applications where efficient gas flow is crucial.

'''Problems Solved:'''
The technology addresses the need for improved gas flow efficiency in gas turbine engines, leading to enhanced performance and fuel efficiency.

'''Benefits:'''
- Increased efficiency in gas flow
- Enhanced performance of the gas turbine engine
- Improved fuel efficiency

'''Commercial Applications:'''
This technology has potential commercial applications in the aerospace industry, power generation sector, and other industries utilizing gas turbine engines.

'''Prior Art:'''
Readers can explore prior patents related to gas turbine engine design, combustion systems, and fuel injection technologies to gain a deeper understanding of the field.

'''Frequently Updated Research:'''
Researchers may find updated studies on gas turbine engine efficiency, combustion optimization, and fuel injection systems relevant to this technology.

'''Questions about Gas Turbine Engine with Bypass TOBI System:'''
1. What are the key advantages of using a bypass tangential on board injector (TOBI) system in a gas turbine engine?
2. How does the design of radial passages in the bypass TOBI system contribute to improved gas flow efficiency?


==Original Abstract Submitted==

A gas turbine engine is provided that includes a high pressure compressor (HPC), a combustor section, a high pressure turbine (HPT), and a bypass tangential on board injector (TOBI) system. The combustor section has a combustor. A core gas path extends through the HPC, the combustor section, and the HPT. The bypass TOBI system extends circumferentially around the engine axial centerline, and has a plurality of nozzles, inner and outer radial sides, a plurality of first type and second type radial passages configured to allow the gas from the HPC to pass from the inner radial side of the bypass TOBI system to the outer radial side of the bypass TOBI system, wherein the first type radial passages are differently configured from the second type radial passages.



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[[Category:CPC_F01D5/081]]