17932319. FUEL NOZZLE simplified abstract (PRATT & WHITNEY CANADA CORP.)
Contents
- 1 FUEL NOZZLE
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 FUEL NOZZLE - 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 Unanswered Questions
- 1.11 Original Abstract Submitted
FUEL NOZZLE
Organization Name
Inventor(s)
FUEL NOZZLE - A simplified explanation of the abstract
This abstract first appeared for US patent application 17932319 titled 'FUEL NOZZLE
Simplified Explanation
The fuel nozzle for a turbine engine described in the patent application consists of a flange, a tip, a stem, and at least one fuel line. The stem chamber is sealed by the tip, and the fuel line extends inside the stem chamber, connecting the flange passage to the tip passage.
- Flange defining at least one flange passage
- Tip spaced from the flange, defining at least one tip passage
- Stem with a peripheral wall extending between the flange and tip, sealing the stem chamber
- Fuel line extending inside the stem chamber, fluidly connecting the flange passage to the tip passage
Potential Applications
This technology could be used in various turbine engines, such as aircraft engines, power generation turbines, and industrial gas turbines.
Problems Solved
This fuel nozzle design helps improve fuel efficiency, reduce emissions, and enhance the overall performance of turbine engines.
Benefits
The benefits of this technology include increased fuel efficiency, reduced emissions, improved engine performance, and potentially lower maintenance costs.
Potential Commercial Applications
Potential commercial applications of this technology could include aerospace companies, power generation companies, and manufacturers of industrial gas turbines.
Possible Prior Art
One possible prior art for this technology could be traditional fuel nozzles used in turbine engines, which may not have the same level of efficiency and performance as the design described in the patent application.
Unanswered Questions
How does this fuel nozzle design compare to existing fuel nozzle designs in terms of performance and efficiency?
The article does not provide a direct comparison between this fuel nozzle design and existing designs in the market.
Are there any specific turbine engine models or manufacturers that have shown interest in adopting this technology?
The article does not mention any specific turbine engine models or manufacturers that have shown interest in implementing this fuel nozzle design.
Original Abstract Submitted
A fuel nozzle for a turbine engine, comprising: a flange defining at least one flange passage; a tip spaced from the flange, the tip defining at least one tip passage; a stem having a first stem end fixedly joined to the flange and a second stem end fixedly joined to the tip, the stem having a peripheral wall extending lengthwise between the first stem end and the second stem end and peripherally around a stem chamber, the tip sealing the stem chamber at the second stem end; and at least one fuel line extending at least partially inside the stem chamber and having a first line end fluidly connected to the at least one flange passage and a second line end fluidly connected to the at least one tip passage.
