When I've been started to design thrust chamber one question appeared.
As you know tubular wall has different cross-sections along the chamber length. So how I can calculate tube dims at any section of chamber?
In the beginning we have some parameters:
number of tubes - 166;
outside tube diameter (at combustion chamber) - 5.00 mm;
tube wall thickness - 0.5 mm;
Combustion chamber dia - 260 mm;
Throat dia - 135 mm;
Nozzle exit dia - 530 mm.
Here's a little sketches for easier understanding what i mean:
1. basic thrust chamber internal layout with all dims:
2. Cross-sections of the tube (A-A - combustion chamber, B-B - Throat, C-C - Nozzle exit):
So X and Y dims are problem.
I know they depends on chamber radius, but what formula?
Appreciate any help!
PS all dimensions are in MM
As you know tubular wall has different cross-sections along the chamber length. So how I can calculate tube dims at any section of chamber?
In the beginning we have some parameters:
number of tubes - 166;
outside tube diameter (at combustion chamber) - 5.00 mm;
tube wall thickness - 0.5 mm;
Combustion chamber dia - 260 mm;
Throat dia - 135 mm;
Nozzle exit dia - 530 mm.
Here's a little sketches for easier understanding what i mean:
1. basic thrust chamber internal layout with all dims:
2. Cross-sections of the tube (A-A - combustion chamber, B-B - Throat, C-C - Nozzle exit):
So X and Y dims are problem.
I know they depends on chamber radius, but what formula?
Appreciate any help!
PS all dimensions are in MM
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