Turbine engine burner can hole size

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Discussion Overview

The discussion revolves around determining the appropriate hole sizes for a turbine engine burner can, particularly in the context of using an air compressor for air intake instead of a compressor section. Participants explore various approaches to calculating burner dimensions based on airflow and pressure considerations.

Discussion Character

  • Technical explanation
  • Debate/contested
  • Exploratory

Main Points Raised

  • One participant expresses uncertainty about using standard formulas for burner dimensions due to the use of an air compressor instead of a compressor section.
  • Another participant suggests that the source of compressed air is irrelevant, emphasizing the importance of the surrounding air pressure in determining hole size.
  • A request for the specific formula to calculate hole sizes is made, indicating a lack of clarity on the standard approach.
  • One participant proposes a specific design guideline for the flame tube diameter and hole area distribution across multiple rows, claiming it is the only formula they could find.
  • Another participant warns about the complexity of combustor design, indicating that it may evolve from an artistic style to a more formulaic science, depending on compressor specifications and combustion requirements.
  • It is noted that the size and number of holes depend on the differential pressure across the burner wall and the flow rate of the compressed air.
  • Participants are encouraged to consider factors such as cooling air, fuel injection, and ignition points when determining hole placement.

Areas of Agreement / Disagreement

Participants do not reach a consensus on the best approach to determine hole sizes, with multiple competing views and uncertainties expressed regarding the application of formulas and design principles.

Contextual Notes

Limitations include the lack of specific compressor characteristics and the absence of a universally accepted formula for the discussed scenario. The discussion reflects a blend of empirical and theoretical considerations without definitive resolutions.

iwant2beoz
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Im building a turbine engine and I am having trouble figuring out the hole sizes for the burner can, my problem is that I am not using a compressor section but rather using an air compressor for the air intake so I can't use the standard formula, can I? If I know my blad diameter and the flow rate of the compressor can I work out the burner dimensions from that or will I have to use trial and error? That you in advance.
 
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The source of the compressed air does not matter.
What matters is the pressure of the air surrounding the combustion chamber.
Use a hole size determined by the air pressure and flow available.
 
Ok, I don't know the formula for that, do you know where I can find it?
 
iwant2beoz said:
my problem is that I am not using a compressor section but rather using an air compressor for the air intake so I can't use the standard formula, can I?
Where is, or what is the standard formula?
 
Make the diameter of the flame tube 2x the diameter of the intake, the length 6x the diameter of the intake. Make 3 rows of holes, the first 20% the area of the intake, the second 30% and the third 50%. This is the only formula can find. This is for an engine with only one burner,
 
You have not identified the scale of your implementation, such as your compressor characteristics.
Combustor design for you is now a black art, it will becomes an artistic style before it matures into a formulaic science.

You are going to have to apply a scientific approach to this engineering question.
The combustor design will be determined by the compressor operating specifications.
For clean combustion, you will require 15 times the mass of air as fuel.
Plus you need cooling air to protect the combustor from the flame.

The size of the holes will be dependent on the differential pressure across the burner wall.
The number of holes will be proportional to the flow rate of the compressed air.
The position of the holes will be dependent on the cooling, the fuel injection and ignition points.

Start with; http://en.wikipedia.org/wiki/Combustor#Air_flow_paths
It is then time to google “turbine combustor”.
 

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