ROCKET ENGINE WITH A VERSATILE IGNITION TORCH
A rocket engine having a rocket engine combustion chamber ( 116 ) and an ignition torch ( 10 ). The rocket engine combustion chamber ( 116 ) is a main combustion chamber, or a combustion chamber of a gas generator, or a combustion chamber of a preburner of the rocket engine. The ignition torch ( 10 ) comprises a body ( 20 ) in which a combustion chamber ( 21 ) is arranged and an ejection tube ( 40 ) for discharging combustion gas leaving the combustion chamber. The body ( 20 ) of the torch is configured to enable the combustion chamber to be fed with fuel and oxidizer via respective fuel and oxidizer feed ducts. The ignition torch ( 10 ) also has an oxidizer reinjection duct ( 60 ) configured to enable oxidizer to be injected substantially at the outlet of the ejection tube ( 40 ).
1 . A rocket engine comprising a rocket engine combustion chamber and an ignition torch for initiating combustion in the rocket engine combustion chamber;
the rocket engine combustion chamber being a main combustion chamber of the rocket engine, or a combustion chamber of a gas generator of the rocket engine, or a combustion chamber of a preburner of the rocket engine; wherein
the ignition torch comprises:
a body in which a torch combustion chamber is arranged; and
an ejection tube for discharging the combustion gas leaving the torch combustion chamber;
the ejection tube has a first end whereby it is connected to the body and a second end arranged in the rocket engine combustion chamber;
the body is configured to allow the torch combustion chamber to be fed with fuel and oxidizer respectively via a fuel feed duct and an oxidizer feed duct; and
the ignition torch further comprises an oxygen reinjection duct configured to enable oxygen to be injected substantially at the outlet of the ejection tube.
2 . A rocket engine according to claim 1 , further including a fuel feed regulator valve and/or an oxidizer feed regulator valve for feeding the combustion chamber and/or an oxidizer reinjection regulator valve, which valve(s) is/are adapted to regulate respectively fuel feed to the torch combustion chamber, oxidizer feed to the torch combustion chamber, and/or an oxidizer injection flow into the oxidizer reinjection duct.
3 . A rocket engine according to claim 1 , further comprising a fuel feed plate of calibrated flow section arranged in the fuel feed duct, and/or an oxidizer feed plate of calibrated flow section arranged in the oxidizer feed duct, and/or an oxidizer reinjection plate of calibrated section arranged in the oxidizer reinjection duct.
4 . A rocket engine according to claim 3 , wherein said plate or at least one of said plates is removable.
5 . A rocket engine according to claim 3 , wherein the oxidizer feed plate and the oxidizer reinjection plate form a single plate.
6 . A rocket engine according to claim 1 , wherein the oxidizer reinjection duct is arranged at least in part in the thickness of a wall of the ejection tube.
7 . A rocket engine according to claim 1 , wherein the fuel feed duct and/or the oxidizer feed duct present(s) a respective baffle formed in the body of the ignition torch.
8 . A rocket engine according to claim 1 , wherein the fuel feed duct and/or the oxidizer feed duct, and/or the oxidizer rejection duct include(s) a respective thermal shock absorber portion extending within the wall of the body of the torch in a direction that makes an angle greater than 45° relative to a radial direction with respect to a center of the torch combustion chamber.
9 . A rocket engine according to claim 1 , presenting a fastener flange arranged around the ejection tube, and a thermal insulation passage arranged radially between an internal duct of the ejection tube and the flange, and in fluid flow isolation from the oxidizer reinjection duct.
10 . A rocket engine according to claim 1 , characterized in that it is configured so that the ignition torch can operate with a normalized mixture ratio greater than 5 .
11 . A rocket engine according to claim 1 , wherein a minimum distance between each wall of the rocket engine combustion chamber and the second end of the ejection tube is greater than kD, where D is the inside diameter at the outlet of the ejection tube, and k is a coefficient equal to 3.