{
  "id": "nasa-rocketdyne-f-1",
  "title": "F-1 engine",
  "maker": "Rocketdyne, Division of North American Aviation (for NASA)",
  "maker_type": "Commercial",
  "kind": "mission",
  "category": "engines",
  "page": "https://spacemushroom.com/space-products/nasa-rocketdyne-f-1/",
  "website": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
  "summary": "Rocketdyne's 1.5-million-pound-thrust LOX/RP-1 gas-generator engine for the Saturn V first stage; the Rocketdyne-derived description on EngineHistory.org names Inconel-X chamber tubes, copper injector rings, a nickel-base-alloy nozzle extension and a Rene 41 turbine housing.",
  "application": "Five F-1 engines powered the Saturn V first stage (S-IC) that lifted Apollo spacecraft off the pad, burning RP-1 and liquid oxygen. The engine is a reference case for very large kerosene engines and for nickel-superalloy tube-wall thrust chambers; NIST studied recovered hardware to see how the Inconel X-750 changed under engine heat and decades in seawater.",
  "story": {
    "headline": "The F-1 is the Rocketdyne engine that powered the Saturn V first stage, five to a rocket.",
    "intro": [
      "Rocketdyne, a division of North American Aviation, built the F-1 for NASA. Each engine burned RP-1 kerosene with liquid oxygen and produced about 1.5 million pounds of thrust. Five of them powered the first stage of the Saturn V, which lifted Apollo spacecraft off the pad. The first flight was the unmanned Apollo 4, on 9 November 1967.",
      "The chamber wall is a bundle of tubes made of Inconel X-750, a nickel alloy built for high temperatures, with fuel running through them to cool the metal. The same fuel lubricates the pump bearings, so there is no separate lubrication system, and it doubles as the hydraulic fluid for the valves and steering actuators."
    ],
    "built": [
      {
        "title": "Chamber of brazed tubes",
        "text": "The chamber is a bell-shaped bundle of tubes, joined by brazing in a furnace. Brazing joins metal parts with a melted filler. Fuel flows through the tubes and cools the wall. The 178 primary tubes form the upper part, and 356 smaller secondary tubes continue below. A ring-shaped steel manifold carries the turbine exhaust.",
        "parts": [
          "Chamber tube bundle (178 primary and 356 secondary tubes)",
          "Primary tubes (178)",
          "Secondary tubes (356)",
          "Tube-to-tube joints",
          "Turbine exhaust manifold"
        ]
      },
      {
        "title": "Injector and baffles",
        "text": "The injector is a corrosion-resistant steel plate fitted with copper rings, fourteen for fuel and fifteen for oxygen, each drilled with small holes. Two circular and twelve radial baffles, cooled by fuel, split the face into thirteen compartments to keep the burn steady. Development tested 15 baffle designs and 14 injector configurations.",
        "parts": [
          "Injector plate (31 rings, 13 compartments)",
          "Fuel orifice rings (14)",
          "Oxidizer orifice rings (15)",
          "Circular baffles (2)",
          "Radial baffles (12)"
        ]
      },
      {
        "title": "Nozzle extension",
        "text": "Below the tube-walled bell, a welded double-wall skirt of nickel-base alloy extends the nozzle. Turbine exhaust gas is injected along its inner wall as a cooling film. Steel channel bands are welded around the outside to stiffen it, and asbestos blankets insulate the exit end.",
        "parts": [
          "Nozzle extension inner and outer walls",
          "Reinforcing channel bands",
          "Exit-end insulation blankets"
        ]
      },
      {
        "title": "Turbopump and gas generator",
        "text": "One shaft carries the oxygen pump at the top, the fuel pump below it and the turbine beneath that. Hot gas from a gas generator drives the turbine. Its welded housing is René 41, a high-nickel alloy. Cracks appeared in development and were traced to an improper welding process.",
        "parts": [
          "Turbopump assembly (LOX pump, fuel pump, shared shaft)",
          "Turbine",
          "Turbine housing",
          "Turbine honeycomb seal",
          "Gas generator combustor"
        ]
      },
      {
        "title": "Valves, ignition and gimbal",
        "text": "One oxygen valve and one fuel valve sit on each side of the engine, sealed with machined Teflon. A cartridge of self-igniting fluid, 85 percent triethylborane and 15 percent triethylaluminium, starts the engine without a pyrotechnic igniter. A spherical steel joint lets the four outer engines swivel.",
        "parts": [
          "Main oxidizer valves (2)",
          "Main fuel valves (2)",
          "Hypergolic igniter fluid",
          "Gimbal bearing",
          "Gimbal socket liner"
        ]
      }
    ],
    "materials": [
      {
        "name": "Inconel X-750",
        "mid": "inconel-x-750",
        "where": "The bundle of chamber tubes. NIST examined recovered chambers and found that engine heat had changed the metal's internal structure."
      },
      {
        "name": "Copper",
        "mid": "copper",
        "where": "The injector's fuel and oxygen orifice rings, and its fuel-cooled circular and radial baffles."
      },
      {
        "name": "René 41",
        "mid": "rene-41",
        "where": "The turbine housing. Cracks in it were traced to an improper welding process during development."
      },
      {
        "name": "Nickel-base alloy (grade not stated)",
        "mid": "nickel-based-alloy",
        "where": "Inner and outer walls of the nozzle extension, and part of the welded oxygen dome."
      },
      {
        "name": "Corrosion-resistant steel",
        "mid": "cres-corrosion-resistant-steel",
        "where": "The injector plate, the turbine exhaust manifold, the nozzle's reinforcing bands and part of the oxygen dome."
      },
      {
        "name": "Asbestos",
        "mid": "asbestos",
        "where": "Blankets on the exit end of the nozzle extension, and layered insulators reinforced with Inconel wire."
      }
    ],
    "connections": "Five F-1 engines sat at the base of the Saturn V first stage, called the S-IC. The four outer engines swivelled to steer the rocket, and the centre engine stayed fixed. Rocketdyne built all 98 production engines, and 70 of them were tested in S-ICs. The F-1 followed Rocketdyne's earlier S-3D and H-1 engines in its propellants, packaging, chamber design and start sequence.",
    "unknown": "The published description names many materials but few grades. The corrosion-resistant steel and the nickel-base alloy have none, and the pump impellers, pump housings, braze and valve bodies are not described at all. Sources also disagree on size: 16 feet long in one, 18 feet tall in another.",
    "facts": [
      {
        "label": "Sea-level thrust",
        "value": "About 1,522,000 lbf (uprated from 1.5 million lbf)"
      },
      {
        "label": "Chamber pressure",
        "value": "1,100 psi (design)"
      },
      {
        "label": "Dry mass",
        "value": "About 18,500 lb"
      },
      {
        "label": "Burn time",
        "value": "165 s per flight"
      },
      {
        "label": "Production",
        "value": "98 production engines"
      },
      {
        "label": "First flight",
        "value": "9 November 1967, Apollo 4 (AS-501), first Saturn V"
      }
    ]
  },
  "specifications": [
    {
      "label": "Sea-level thrust",
      "value": "About 1,522,000 lbf (uprated from 1.5 million lbf)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "going to 1,522,000, plus or minus 1.5 percent"
    },
    {
      "label": "Original thrust rating",
      "value": "1.5 million lbf per engine",
      "source_url": "https://www.nasa.gov/image-article/this-week-nasa-history-nasa-approved-f-1-engine-contract-nov-18-1966/",
      "quote": "Each engine produced 1.5 million pounds of thrust."
    },
    {
      "label": "Specific impulse",
      "value": "265 s",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "was 265 seconds, which was good for those days"
    },
    {
      "label": "Chamber pressure",
      "value": "1,100 psi (design)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "This was designed at 1,100 pounds per square inch (psi)."
    },
    {
      "label": "Propellants",
      "value": "Liquid oxygen and RP-1 kerosene",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "five F-1 rocket engines that burned a combination of RP-1 and LOX"
    },
    {
      "label": "Cycle",
      "value": "Gas generator",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml",
      "quote": "overall packaging, thrust chamber design, gas generator cycle, pressure ladder start sequence"
    },
    {
      "label": "Nozzle area ratio",
      "value": "16:1 (tube wall to 10:1, double-wall extension to 16:1)",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "The nozzle had an area ratio of 16:1."
    },
    {
      "label": "Dry mass",
      "value": "About 18,500 lb",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
      "quote": "The F-1 occupied a space 12 feet in diameter by 16 feet long and weighed approximately 18,500 lb dry."
    },
    {
      "label": "Envelope (EngineHistory.org)",
      "value": "12 ft diameter by 16 ft long",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
      "quote": "The F-1 occupied a space 12 feet in diameter by 16 feet long and weighed approximately 18,500 lb dry."
    },
    {
      "label": "Envelope (Biggs, Rocketdyne)",
      "value": "18 ft tall, 12 ft wide",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "The engine was eighteen feet tall, twelve feet wide."
    },
    {
      "label": "Burn time",
      "value": "165 s per flight",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "from that point on, the burn duration was 165"
    },
    {
      "label": "Qualification life",
      "value": "20 starts and 2,250 s",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "designed for a qualification life of twenty starts and 2,250 seconds"
    },
    {
      "label": "Turbopump layout",
      "value": "One shaft: LOX pump, fuel pump, turbine",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "It had a liquid oxygen (LOX) pump on top of the shaft, then a fuel pump, then a turbine."
    },
    {
      "label": "Engines per vehicle",
      "value": "5 on the Saturn V S-IC first stage (4 outer engines gimbaled, centre engine fixed)",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "The four outer F-1s were gimbaled, allowing the Saturn V guidance and control system to control roll, pitch and yaw"
    },
    {
      "label": "Production",
      "value": "98 production engines",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml",
      "quote": "Rocketdyne built 98 production F-1s, 70 of which were tested in S-ICs."
    },
    {
      "label": "Contract",
      "value": "NASA contract NAS8-18734 for 30 F-1 engines (approved 18 Nov 1966)",
      "source_url": "https://www.nasa.gov/image-article/this-week-nasa-history-nasa-approved-f-1-engine-contract-nov-18-1966/",
      "quote": "NASA approved the F-1 engine contract NAS8-18734, which provided for 30 F-1 engines"
    },
    {
      "label": "First flight",
      "value": "9 November 1967, Apollo 4 (AS-501), first Saturn V",
      "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1967-113A",
      "quote": "The unmanned Saturn/Apollo 4 (AS-501) mission was the first all-up test of the three stage Saturn V rocket."
    },
    {
      "label": "First flight date",
      "value": "1967-11-09",
      "source_url": "https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1967-113A",
      "quote": "Launch Date: 1967-11-09"
    }
  ],
  "features": [
    {
      "text": "One turbopump on one shaft drives both the LOX and fuel pumps",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "The major features are that it had a single turbopump"
    },
    {
      "text": "RP-1 fuel lubricates the turbopump bearings, so no separate lubrication system",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "we used the fuel for lubricating turbopump bearing"
    },
    {
      "text": "Fuel also acts as the hydraulic fluid for the engine valves and thrust-vector actuators",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "It was used to power the engine valves and the thrust vector control actuators"
    },
    {
      "text": "Turbine exhaust gas film-cools the inner wall of the welded nozzle extension",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
      "quote": "Film cooling of the inner walls was achieved by injecting turbine exhaust gas"
    },
    {
      "text": "Hypergolic cartridge starts the engine without a pyrotechnic igniter",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "The hypergol cartridge in the middle of the control system held a fluid that would automatically ignite"
    },
    {
      "text": "Injector baffles divide the face into thirteen compartments to damp combustion instability",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "The injector had baffles sticking down, dividing it into thirteen compartments."
    },
    {
      "text": "Development tested 15 baffle designs and 14 injector configurations",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml",
      "quote": "consisting of 15 different baffle designs and 14 injector configurations"
    },
    {
      "text": "Tank-head start takes about five seconds with no outside help",
      "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
      "quote": "It took about five seconds for the engine to start"
    },
    {
      "text": "Ground crews fill the chamber tubes with ethylene glycol about 15 hours before launch",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
      "quote": "with an inert ethylene glycol solution that served to smooth out the engine starting combustion sequence"
    },
    {
      "text": "Turbine housing alloy Rene 41 cracked in development until the welding process was fixed",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml",
      "quote": "Cracks in the high-nickel René 41 alloy turbine housing were traced to an improper welding process"
    },
    {
      "text": "NIST found engine heat had changed the Inconel X-750 microstructure of recovered chambers",
      "source_url": "https://www.nist.gov/nist-time-capsule/nist-beneath-waves/nist-helps-restore-blast-past",
      "quote": "tiny branch-like structures called dendrites"
    }
  ],
  "parts": [
    {
      "assembly": "Thrust chamber",
      "parts": [
        {
          "part": "Chamber tube bundle (178 primary and 356 secondary tubes)",
          "material": "Inconel X-750 (nickel-based superalloy)",
          "form": "tube-wall, regeneratively fuel-cooled to the 10:1 plane",
          "finish": null,
          "standard": null,
          "hardware_ref": "NIST describes recovered thrust chambers and the exhaust nozzle; EngineHistory.org prints the tubing as Inconel-X",
          "quote": "constructed of a nickel-based superalloy called Inconel X-750",
          "source_url": "https://www.nist.gov/nist-time-capsule/nist-beneath-waves/nist-helps-restore-blast-past",
          "profile": null,
          "mid": "inconel-x-750"
        },
        {
          "part": "Primary tubes (178)",
          "material": null,
          "form": "hydraulically formed tubes, above the 3:1 plane",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A total of 178 primary tubes, each hydraulically formed",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Secondary tubes (356)",
          "material": "Inconel-X",
          "form": "smaller secondary tubes, 3:1 to 10:1 plane",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Inconel-X secondary tubes formed the chamber from the 3:1 to the 10:1 expansion ratio plane",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "inconel-x-750"
        },
        {
          "part": "Tube-to-tube joints",
          "material": null,
          "form": "furnace brazed (braze alloy not stated)",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The thrust chamber body was a furnace-brazed, bell-shaped assembly",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Turbine exhaust manifold",
          "material": "corrosion-resistant steel (CRES)",
          "form": "torus manifold",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a corrosion resistant steel (CRES) torus",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "cres-corrosion-resistant-steel"
        },
        {
          "part": "Dome-to-injector flange gasket",
          "material": "Teflon-filled Flexitallic gasket",
          "form": "gasket",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The dome and injector mating flanges were sealed by a Teflon-filled Flexitallic gasket.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "teflon-filled-flexitallic-gasket"
        },
        {
          "part": "Dome-to-injector inner O-ring",
          "material": "Inconel-X",
          "form": "hollow O-ring with drilled holes",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "at the inner diameter by a hollow Inconel-X O-ring",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "inconel-x-750"
        },
        {
          "part": "Dome-to-injector outer O-ring",
          "material": "Viton-A",
          "form": "O-ring",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "sealed at the outer diameter by a Viton-A O-ring",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "viton-a"
        }
      ]
    },
    {
      "assembly": "Injector",
      "parts": [
        {
          "part": "Injector plate (31 rings, 13 compartments)",
          "material": "corrosion-resistant steel (CRES)",
          "form": "plate-type, 31 rings",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "It was a CRES, 31-ring, plate-type injector, divided into 13 compartments by 2 circular and 12 radial baffles.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "cres-corrosion-resistant-steel"
        },
        {
          "part": "Fuel orifice rings (14)",
          "material": "copper",
          "form": "orifice-drilled rings, fuel-on-fuel doublet",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Fourteen copper rings, orifice-drilled to provide a doublet fuel-on-fuel impingement",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": "copper",
          "mid": "copper"
        },
        {
          "part": "Oxidizer orifice rings (15)",
          "material": "copper",
          "form": "orifice-drilled rings, oxidizer-on-oxidizer doublet",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Fifteen copper rings, orificed-drilled to provide a doublet oxidizer-on-oxidizer impingement",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": "copper",
          "mid": "copper"
        },
        {
          "part": "Circular baffles (2)",
          "material": "copper",
          "form": "fuel-cooled baffles, brazed",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "two circular, fuel-cooled copper baffles were brazed to the fuel ring grooves",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": "copper",
          "mid": "copper"
        },
        {
          "part": "Radial baffles (12)",
          "material": "copper",
          "form": "fuel-cooled baffles",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The twelve radial, fuel-cooled, copper baffles were supplied with fuel by the outer circular baffle",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": "copper",
          "mid": "copper"
        }
      ]
    },
    {
      "assembly": "Oxidizer dome and manifold",
      "parts": [
        {
          "part": "Dome body and torus manifold, CRES parts",
          "material": "corrosion-resistant steel (CRES)",
          "form": "welded unit",
          "finish": null,
          "standard": null,
          "hardware_ref": "Shares one quote with the nickel-base alloy portion below",
          "quote": "The assembly was a welded, CRES and nickel-base alloy unit consisting of a dome body and a torus manifold.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "cres-corrosion-resistant-steel"
        },
        {
          "part": "Dome body and torus manifold, nickel-base alloy parts",
          "material": "nickel-base alloy (grade not stated)",
          "form": "welded unit",
          "finish": null,
          "standard": null,
          "hardware_ref": "Source does not say which parts are CRES and which are nickel-base alloy",
          "quote": "The assembly was a welded, CRES and nickel-base alloy unit consisting of a dome body and a torus manifold.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "nickel-based-alloy"
        }
      ]
    },
    {
      "assembly": "Nozzle extension",
      "parts": [
        {
          "part": "Nozzle extension inner and outer walls",
          "material": "nickel-base alloy (grade not stated)",
          "form": "welded double wall, 10:1 to 16:1",
          "finish": null,
          "standard": null,
          "hardware_ref": "Inner wall film-cooled by turbine exhaust",
          "quote": "The nozzle extension was of welded construction, incorporating nickel-base-alloy inner and outer walls",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "nickel-based-alloy"
        },
        {
          "part": "Reinforcing channel bands",
          "material": "corrosion-resistant steel (CRES)",
          "form": "channel bands, welded",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "CRES reinforcing channel bands welded to the outer wall circumference",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "cres-corrosion-resistant-steel"
        },
        {
          "part": "Exit-end insulation blankets",
          "material": "asbestos",
          "form": "blankets",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Asbestos blankets were used on the exit end of the nozzle extension",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "asbestos"
        }
      ]
    },
    {
      "assembly": "Turbopump",
      "parts": [
        {
          "part": "Turbopump assembly (LOX pump, fuel pump, shared shaft)",
          "material": null,
          "form": "single shaft parallel to the chamber axis",
          "finish": null,
          "standard": null,
          "hardware_ref": "Pump and impeller alloys not stated",
          "quote": "It had a liquid oxygen (LOX) pump on top of the shaft, then a fuel pump, then a turbine.",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Centrifugal pumps (two, double discharge)",
          "material": null,
          "form": "LOX and fuel centrifugal pumps",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The turbopump assembly was composed of two centrifugal pumps",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Turbine",
          "material": null,
          "form": "two-stage velocity-compounded impulse",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "directly driven by a two-stage, velocity compounded, impulse gas turbine",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Turbine housing",
          "material": "Rene 41 (high-nickel alloy)",
          "form": "welded housing",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Cracks in the high-nickel René 41 alloy turbine housing were traced to an improper welding process",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml",
          "profile": null,
          "mid": "rene-41"
        },
        {
          "part": "Turbine honeycomb seal",
          "material": "Inconel (grade not stated)",
          "form": "honeycomb circular strip",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The honeycomb seal was an Inconel honeycomb circular strip",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "inconel"
        },
        {
          "part": "Shaft ball bearings (twin)",
          "material": null,
          "form": "fuel-cooled ball bearings, oxidizer end",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The shaft was supported by twin electrically heated, fuel-cooled ball bearing assemblies",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Shaft roller bearing",
          "material": null,
          "form": "fuel-cooled roller bearing, turbine end",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "one fuel-cooled roller bearing assembly at the turbine area",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Carbon shaft seals",
          "material": "carbon",
          "form": "carbon-nose and carbon-segmented seals",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Six carbon-nose and three carbon-segmented seals",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "carbon-seal"
        },
        {
          "part": "Fuel pump wear rings",
          "material": "lead-plated brass",
          "form": "wear rings",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "three synthetic rubber O-rings and two lead-plated brass wear rings",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "lead-plated-brass"
        },
        {
          "part": "Oxidizer pump wear ring",
          "material": "Kel-F",
          "form": "labyrinth seal",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The Kel-F wear ring was a labyrinth seal",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "kel-f"
        }
      ]
    },
    {
      "assembly": "Gas generator and heat exchanger",
      "parts": [
        {
          "part": "Gas generator combustor",
          "material": null,
          "form": "welded single-walled manifold",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The gas generator combustor was a welded single-walled manifold connecting the gas generator injector and the turbine inlet.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Gas generator thermal shell",
          "material": null,
          "form": "bolted sheet metal shell (alloy not stated)",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The combustor was thermally insulated by a sheet metal shell that bolted around the combustor body.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": null
        },
        {
          "part": "Gas generator hot-gas seals",
          "material": "silver-plated stainless steel",
          "form": "Naflex and K-seals",
          "finish": null,
          "standard": null,
          "hardware_ref": "Copper crush washers used with them",
          "quote": "silver-plated stainless-steel Naflex and K-seals and copper crush washers for hot-gas applications",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "silver-plated-stainless-steel"
        },
        {
          "part": "Heat exchanger (LOX and helium coils)",
          "material": null,
          "form": "coils; alloy not stated",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "using a heat exchanger to vaporize LOX and heat helium to pressurize the LOX and RP-1 tanks",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml",
          "profile": null,
          "mid": null
        }
      ]
    },
    {
      "assembly": "Valves and ducts",
      "parts": [
        {
          "part": "Main oxidizer valves (2)",
          "material": null,
          "form": "one each side of the engine",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "There were two LOX valves, one on each side of the engine",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Main oxidizer valve poppet seal",
          "material": "Teflon",
          "form": "machined seal",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a poppet with a machined Teflon seal secured by a seal retainer",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "teflon-ptfe"
        },
        {
          "part": "Main fuel valves (2)",
          "material": null,
          "form": "one each side of the engine",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "and two fuel valves, one on each side of the engine as well",
          "source_url": "https://www.nasa.gov/wp-content/uploads/2023/04/sp-4545.pdf",
          "profile": null,
          "mid": null
        },
        {
          "part": "Main fuel valve poppet seal",
          "material": "Teflon",
          "form": "machined seal",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "a spring-loaded poppet with a machined Teflon seal secured by a seal retainer",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "teflon-ptfe"
        },
        {
          "part": "High-pressure propellant ducts",
          "material": "aluminum tubing (alloy not stated)",
          "form": "drawn tubing",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The ducts were constructed of drawn aluminum tubing, bent in a continuous section.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": "aluminium",
          "mid": "aluminium"
        }
      ]
    },
    {
      "assembly": "Ignition",
      "parts": [
        {
          "part": "Hypergolic igniter fluid",
          "material": "triethylborane 85% and triethylaluminum 15% pyrophoric fluid",
          "form": "fluid in a burst-diaphragm cartridge",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "pyrophoric fluid consisting of 85% triethylborane and 15% triethylaluminum",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "triethylborane-triethylaluminum"
        }
      ]
    },
    {
      "assembly": "Gimbal and thermal protection",
      "parts": [
        {
          "part": "Gimbal bearing",
          "material": "steel (grade not stated)",
          "form": "spherical universal joint",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "The assembly was a spherical, low-friction, steel universal joint",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "steel-grade-unstated"
        },
        {
          "part": "Gimbal socket liner",
          "material": "Fabroid (Teflon-impregnated fiberglass)",
          "form": "liner bonded to sockets",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A composition of Teflon-impregnated fiberglass (Fabroid) was bonded to the bearing surfaces of the sockets.",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "fabroid"
        },
        {
          "part": "Gimbal boot",
          "material": "silicone-impregnated fiberglass",
          "form": "boot",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "A silicone-impregnated fiberglass boot",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "silicone-impregnated-fiberglass"
        },
        {
          "part": "Foil-batt insulators",
          "material": "Inconel foil over random fibre batting",
          "form": "preformed segments",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "constructed of random fiber batting secured between two layers of textured inconel foil",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "inconel"
        },
        {
          "part": "Asbestos blanket insulators",
          "material": "asbestos cloth with Inconel lockwire",
          "form": "multi-layer blankets",
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "Asbestos blanket insulators were composed of multiple layers of asbestos cloth reinforced with Inconel lockwire",
          "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.12.shtml",
          "profile": null,
          "mid": "asbestos"
        }
      ]
    },
    {
      "assembly": "Propellants",
      "parts": [
        {
          "part": "Oxidizer",
          "material": "liquid oxygen (LOX)",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "five F-1 rocket engines that burned a combination of RP-1 and LOX",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": "liquid-oxygen"
        },
        {
          "part": "Fuel",
          "material": "RP-1 kerosene",
          "form": null,
          "finish": null,
          "standard": null,
          "hardware_ref": null,
          "quote": "five F-1 rocket engines that burned a combination of RP-1 and LOX",
          "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml",
          "profile": null,
          "mid": "rp-1-kerosene"
        }
      ]
    }
  ],
  "materials": [
    {
      "id": "inconel-x-750",
      "name": "Inconel-X",
      "material_page": null
    },
    {
      "id": "cres-corrosion-resistant-steel",
      "name": "corrosion-resistant steel (CRES)",
      "material_page": null
    },
    {
      "id": "teflon-filled-flexitallic-gasket",
      "name": "Teflon-filled Flexitallic gasket",
      "material_page": null
    },
    {
      "id": "viton-a",
      "name": "Viton-A",
      "material_page": null
    },
    {
      "id": "copper",
      "name": "copper",
      "material_page": "https://spacemushroom.com/profiles/copper/"
    },
    {
      "id": "nickel-based-alloy",
      "name": "nickel-base alloy (grade not stated)",
      "material_page": null
    },
    {
      "id": "asbestos",
      "name": "asbestos cloth with Inconel lockwire",
      "material_page": null
    },
    {
      "id": "rene-41",
      "name": "Rene 41 (high-nickel alloy)",
      "material_page": null
    },
    {
      "id": "inconel",
      "name": "Inconel foil over random fibre batting",
      "material_page": null
    },
    {
      "id": "carbon-seal",
      "name": "carbon",
      "material_page": null
    },
    {
      "id": "lead-plated-brass",
      "name": "lead-plated brass",
      "material_page": null
    },
    {
      "id": "kel-f",
      "name": "Kel-F",
      "material_page": null
    },
    {
      "id": "silver-plated-stainless-steel",
      "name": "silver-plated stainless steel",
      "material_page": null
    },
    {
      "id": "teflon-ptfe",
      "name": "Teflon",
      "material_page": null
    },
    {
      "id": "aluminium",
      "name": "aluminum tubing (alloy not stated)",
      "material_page": "https://spacemushroom.com/profiles/aluminium/"
    },
    {
      "id": "triethylborane-triethylaluminum",
      "name": "triethylborane 85% and triethylaluminum 15% pyrophoric fluid",
      "material_page": null
    },
    {
      "id": "steel-grade-unstated",
      "name": "steel (grade not stated)",
      "material_page": null
    },
    {
      "id": "fabroid",
      "name": "Fabroid (Teflon-impregnated fiberglass)",
      "material_page": null
    },
    {
      "id": "silicone-impregnated-fiberglass",
      "name": "silicone-impregnated fiberglass",
      "material_page": null
    },
    {
      "id": "liquid-oxygen",
      "name": "liquid oxygen (LOX)",
      "material_page": null
    },
    {
      "id": "rp-1-kerosene",
      "name": "RP-1 kerosene",
      "material_page": null
    }
  ],
  "standards": [],
  "relations": [
    {
      "type": "part_of",
      "target": "Saturn V (S-IC first stage)",
      "target_slug": "nasa-saturn-v",
      "note": "Five F-1 engines at the base of the S-IC; four outer engines gimbaled, centre engine fixed",
      "quote": "five F-1 rocket engines that burned a combination of RP-1 and LOX",
      "source_url": "https://enginehistory.org/Rockets/RPE08.10/RPE08.10.shtml"
    },
    {
      "type": "supplied_by",
      "target": "Rocketdyne Division of North American Aviation",
      "target_slug": null,
      "note": "Engine builder; NASA approved contract NAS8-18734 for 30 F-1 engines in 1966",
      "quote": "furnished by Rocketdyne Division of North American Aviation",
      "source_url": "https://www.nasa.gov/image-article/this-week-nasa-history-nasa-approved-f-1-engine-contract-nov-18-1966/"
    },
    {
      "type": "heritage_of",
      "target": "S-3D and H-1 engines (Rocketdyne)",
      "target_slug": null,
      "note": "F-1 followed their propellant choice, packaging, chamber design, gas generator cycle and start sequence",
      "quote": "Rocketdyne followed the S-3D and H-1 proven examples in propellant choice",
      "source_url": "https://enginehistory.org/Rockets/RPE08.11/RPE08.11.shtml"
    }
  ],
  "not_published": "No alloy grades except Inconel X-750 (NIST) and Rene 41; CRES and nickel-base alloy are printed without a grade. No standards.",
  "depth": "partial",
  "photos": [],
  "context": {
    "size": [],
    "mass": [],
    "orbit": []
  },
  "licence": "Product data CC BY 4.0, cite Space Mushroom. Photos keep their own licences, given per photo.",
  "mcp": "https://spacemushroom.com/mcp"
}