Injector and dome studs, nozzle extension bolts, turbopump, duct and valve flange bolting, gimbal block and thrust frame bolts. We manufacture studs, bolts, nuts and machined parts in Houston to your drawings and specifications.
A generic 750,000 lbf class pump-fed engine burning liquid oxygen and kerosene on a gas-generator cycle, with a 24.9-inch throat and a 93.4-inch nozzle exit, taken apart joint by joint: the gimbal actuators come off, the hot-gas and discharge ducts unbolt and clear, the main valves and inlet ducts follow, the turbopumps come off their mounts, the nozzle extension drops, the dome and injector lift off the chamber, and the gimbal block comes off the thrust frame. The bolting is in colour. Press Solid view for a steel model, or Cutaway to see the chamber, throat, injector and dome and the inside of both turbopumps.
One ring of studs clamps the oxidiser dome and the injector plate to the top flange of the thrust chamber. Forty-eight 5/8 in. studs here; the count and size are typical.
Many small bolts and nuts on thin flanges join the nozzle extension to the main nozzle. Ninety-six 3/8 in. bolts here, typical.
Hold each pump's volute housing and its turbine housing to the bearing housing between them: cryogenic at the oxidiser pump, hot at the turbines.
Hold each turbopump's pad to its bracket on the thrust chamber.
Bolt the low-pressure inlet ducts from the vehicle to the pump inlets.
Bolt the high-pressure discharge ducts to the dome and the fuel manifold. The oxidiser joint follows the textbook example: twenty-six 5/16-24 A-286 bolts on a 9 in. bolt circle, in a 9.62 in. Alloy 718 flange 0.48 in. thick.
Clamp each main butterfly valve between the pump discharge flange and the discharge duct.
Join the gas generator, the crossover duct and the turbine exhaust duct to the turbines, in a heat-resistant alloy.
Hold the gimbal bearing block to the dome below it and to the thrust frame above it. The engine's thrust passes through both joints.
A bolt and nut through the clevis at each end of the thrust frame struts.
Clevis bolts at each end of the two gimbal actuators, and the bolts holding the actuator brackets to the chamber.
High-temperature and cryogenic studs, bolts and nuts, to your drawing and material specification. Send us your drawings and material spec.
Request a quote832-446-3442A generic engine, not any maker's design and not any engine that has flown. The thrust, the chamber, throat and nozzle exit diameters and the oxidiser discharge duct flange with its bolts follow the worked example in NASA SP-125, a public textbook. Everything else is illustrative typical proportions: the nozzle contour, the dome, injector, turbopumps, valves, gas generator, ducts, gimbal block, thrust frame and actuators, and every other bolt count and size, which are typical. High-temperature and cryogenic bolting is typically A-286 or a nickel alloy such as Alloy 718. Your drawings govern. We manufacture to your drawings and specifications.
Drawn to the worked example engine in NASA SP-125 (Huzel and Huang, Design of Liquid Propellant Rocket Engines) for the thrust chamber sizes and the oxidiser discharge duct flange, with the general arrangement following the NASA SP-8000 series design monographs and standard textbooks.
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