# Turbine engine burner can hole size

1. Jan 23, 2014

### iwant2beoz

Im building a turbine engine and im having trouble figuring out the hole sizes for the burner can, my problem is that im not using a compressor section but rather using an air compressor for the air intake so I cant 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.

2. Jan 25, 2014

### Baluncore

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.

3. Jan 25, 2014

### iwant2beoz

Ok, I dont know the formula for that, do you know where I can find it?

4. Jan 25, 2014

### Baluncore

Where is, or what is the standard formula?

5. Jan 27, 2014

### iwant2beoz

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,

6. Jan 27, 2014

### Baluncore

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.