GAS DUCT OF LIQUID-PROPELLANT ROCKET ENGINE WITH AFTER-BURNING Russian patent published in 2008 - IPC F02K9/42 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket-propelled vehicles, particularly, to the gas duct of liquid-propellant rocket engines with after-burning. The aforesaid gas duct comprises the outlet manifold of the main turbo-pump unit, a bent pipeline and a swinging assembly. The aforesaid bent pipeline is coupled with the outlet manifold and the said swinging assembly is linked with the engine chamber. Note here that the aforesaid swinging assembly is furnished with a bi-degree universal joint and the joint of the swinging assembly with the engine chamber and bent pipeline represents a flange coupling incorporating a metal T-shape gasket furnished with a load-bearing ring with two flexible springs provided with mountain-like ledges. Note also that the aforesaid one-piece bent pipeline is made from a heat-resistant nickel-alloy, while the bent pipeline flange represents a load-bearing belt with a developed end face surface for the engine frame support to be attached thereto. The aforesaid T-shape taper gasket springs feature the thickness varying over their length, while their length L-to-mean thickness δ ratio makes L/δ ˜8 to 10 and the angle α of the spring taper surface inclination to the flange coupling axis makes 1.5 to 2.5 degrees. The flexible spring OD including the aforesaid mountain-like ledges exceeds the ID of the flange coupling sealing surfaces by 0.1 to 0.2 mm. All parts of the gas duct are made from the EK-61 heat-resistant nickel alloy. The propose invention allows a higher tightness of the fixed joints and pipelines carrying high-temperature high-pressure oxidising medium.

EFFECT: improved performances due to ease of uncoupling gas duct from engine chamber and bent pipeline.

7 cl, 4 dwg