Toyota jidosha kabushiki kaisha (20240183537). COMBUSTION NOZZLE AND COMBUSTOR simplified abstract

COMBUSTION NOZZLE AND COMBUSTOR

Organization Name

toyota jidosha kabushiki kaisha

Inventor(s)

Shunsuke Kasuga of Numazu-shi (JP)

Yasushi Tatebayashi of Fuji-shi (JP)

Shigeru Hirano of Mishima-shi (JP)

Takahiro Minami of Sunto-gun (JP)

COMBUSTION NOZZLE AND COMBUSTOR - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240183537 titled 'COMBUSTION NOZZLE AND COMBUSTOR

Simplified Explanation

The combustion nozzle in a gas turbine combustor discharges compressed air and fuel into a combustion chamber for combustion. The nozzle includes an air inlet, a nozzle orifice, an air channel, a fuel channel, and fuel outlets. The compressed air is received through the air inlet, while the fuel is received and discharged through the fuel outlets towards the flow of compressed air from the nozzle orifice. The air channel features a venturi section where the channel cross-sectional area of the compressed air becomes relatively small.

• Air and fuel are discharged into a combustion chamber for combustion in a gas turbine.
• The combustion nozzle includes an air inlet, nozzle orifice, air channel, fuel channel, and fuel outlets.
• Compressed air is received through the air inlet, while fuel is discharged through the fuel outlets towards the compressed air flow.
• The air channel has a venturi section where the compressed air's cross-sectional area becomes small.

Potential Applications

This technology can be applied in gas turbines for power generation, aircraft engines, and other combustion systems requiring efficient fuel combustion.

Problems Solved

This technology solves the problem of efficiently mixing compressed air and fuel for combustion in a gas turbine, ensuring optimal combustion efficiency and performance.

Benefits

The benefits of this technology include improved combustion efficiency, reduced emissions, increased power output, and enhanced overall performance of gas turbine systems.

Potential Commercial Applications

Potential commercial applications of this technology include gas turbine power plants, aircraft propulsion systems, industrial combustion systems, and other applications requiring efficient fuel combustion.

Possible Prior Art

One possible prior art could be the use of similar combustion nozzles in gas turbine combustors for efficient fuel combustion.

How does this technology impact fuel efficiency in gas turbines?

This technology improves fuel efficiency by ensuring optimal mixing of fuel and compressed air for combustion, leading to more efficient fuel utilization and reduced fuel consumption in gas turbines.

What are the environmental benefits of using this technology in gas turbines?

Using this technology in gas turbines can lead to reduced emissions, including lower levels of pollutants such as nitrogen oxides and particulate matter, contributing to improved air quality and environmental sustainability.

Original Abstract Submitted

a combustion nozzle discharges compressed air and fuel, to be combusted, into a combustion chamber of a combustor of a gas turbine. the combustion nozzle includes an air inlet, a nozzle orifice, an air channel, a fuel channel, and fuel outlets. the air inlet receives the compressed air. the nozzle orifice opens into the combustion chamber and discharges the compressed air. the air channel communicates between the air inlet and the nozzle orifice. the fuel channel receives the fuel, and discharges the fuel from the fuel outlets toward a flow of the compressed air discharged from the nozzle orifice. the air channel includes a venturi section in which a channel cross-sectional area of the compressed air becomes relatively small. the fuel outlets are provided in the venturi section.