METHOD OF LFRE CHAMBER GEOMETRICAL AXIS INSTALLATION AND COMPENSATING CLOSING DEVICE FOR ITS IMPLEMENTATION

FIELD: transport.SUBSTANCE: invention relates to aerospace engineering and can be used in gas-hydraulic lines of liquid-fuel rocket engines. In the method of liquid-fuel rocket engine chamber geometrical axis installation in rated position based on excluding influence of process tolerances during manufacturing aggregates, parts and assembling units, as well as influence of material shrinkage in joint welds of gas lines between auxiliary pump-drive assembly and chamber heads for angular deviation of chamber geometrical axes from rated position. According to invention, measurement of compensating closing device actual parameters, its manufacturing, adjustment and welding are performed at the final stage of line assembling after executing all welds of jointed aggregates, parts and assembling units. The method is implemented by gas line compensating closing device containing equalising sub with cavities at its butt ends for backing rings installation. According to invention, in the device, cavities for backing rings installation are made of length equal to length of backing rings, and above cavities, through holes are drilled where fixtures for moving backing rings to the area of parts and assembling units joint welds; cavities in fixtures for screw-driver are turned perpendicular to chamfer projection plane; fixtures are installed along perimeter at every 120°; in holes of equalising sub and fixture heads bevels are made to exclude poor penetrations in weld roots.EFFECT: invention provides higher accuracy of its installation and lowering thrust vector losses of engine working in flight or on stand.5 cl, 12 dwg Изобретение относится к ракетно-космической технике и может быть использовано в газогидравлических магистралях жидкостных ракетных двигателей. В способе установки геометрической оси камер жидкостного ракетного двигателя в номинальном положении, основанном на исключении влияния технологических отклонений при изготовлении агрегатов, деталей и сборочных единиц, а также усадки материала в сварных швах стыков газовых магистралей между турбонасосным агрегатом и головками камер на угловое отклонение геометрических осей камер от номинального положения, согласно изобретению измерение фактических параметров замыкающего компенсирующего устройства, его изготовление, подгонка и сварка выполняются на заключительной стадии сборки магистралей после выполнения всех сварных швов стыкуемых агрегатов деталей и сборочных единиц. Способ реализуется компенсирующим замыкающим