Combustion chamber provided with a tubular element
A combustion chamber including a diverging portion. The combustion chamber extends along a longitudinal axis and includes a fluid injection system from which there extends in a downstream direction a wall presenting a throat and a diverging portion situated downstream from the throat. The chamber further includes a tubular element surrounding the wall at least in part and configured to take up most of forces generated during operation of the chamber on the downstream end of the wall to transfer the forces to a structure situated upstream from the chamber.
1. A combustion chamber extending along a longitudinal axis and comprising:
a fluid injection system from which there extends in a downstream direction a wall presenting a throat and a diverging portion situated downstream from the throat, the diverging portion comprising an annular flange, continuously formed with the wall, on a downstream end of the diverging portion, the combustion chamber including a cooling system embedded inside the wall; and
a tubular element, being concentric with the combustion chamber, and having a constant radius over an entire length of the tubular element relative to the longitudinal axis along a longitudinal direction surrounding the wall at least in part,
wherein the tubular element bears both against the annular flange of the downstream end of the diverging portion and on a structure located upstream from the combustion chamber, the tubular element being configured to take up most forces generated on the wall during operation of the combustion chamber on the downstream end of the diverging portion to transfer the forces to the structure located upstream from the combustion chamber, the tubular element also being configured to allow thermal expansion of the cooling system, the tubular element being independent from the cooling system in that no part of said tubular element is in contact with a liquid flowing inside said cooling system.
2. The combustion chamber according to claim 1 , wherein an outer surface of the combustion chamber is surrounded over at least a fraction of a length of the outer surface of the combustion chamber in the longitudinal direction by a sleeve, the sleeve covering the wall and fitting closely to the wall.
3. The combustion chamber according to claim 2 , wherein the sleeve is made of an organic matrix composite material.
4. The combustion chamber according to claim 2 , wherein the sleeve covers the cooling system and fits closely to the cooling system.
5. The combustion chamber according to claim 4 , wherein the cooling system is a regenerative circuit and the liquid flowing inside said cooling system is a cryogenic liquid.
6. The combustion chamber according to claim 2 , wherein the sleeve surrounds the combustion chamber over an entire length of the wall.
7. The combustion chamber according to claim 2 , wherein the sleeve is prestressed while being put into place on the combustion chamber.
8. The combustion chamber according to claim 2 , wherein the sleeve also surrounds at least a portion of the fluid injection system from which the wall extends, the fluid injection system being situated upstream from the combustion chamber.
9. A rocket engine comprising the combustion chamber according to claim 1 and a diverging bell situated downstream from the combustion chamber.
10. The combustion chamber according to claim 1 , wherein the tubular element is a tube surrounding the wall over an entire length and the entire circumference of the wall.
11. The combustion chamber according to claim 1 , wherein the structure located upstream from the combustion chamber is an injection head of the fluid injection system.
12. The rocket engine according to claim 9 , wherein the annular flange constitutes an interface between the diverging portion of the wall and the diverging bell.