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RD-107

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RD-107
RD-107 engine on display at the Museum of Space and Missile Technology in Saint Petersburg.
Country of originSoviet Union
Russia
DesignerOKB-456
ManufacturerJSC Kuznetsov[1]
ApplicationBooster/first stage
AssociatedLVR-7 family
PredecessorRD-105
StatusIn production
Liquid-fuel engine
PropellantLOX/RP-1
CycleGas-generator
Performance
Thrust, vacuum1,020 kN (230,000 lbf)
Thrust, sea-level839 kN (189,000 lbf)
Specific impulse,vacuum320.2 s (3.140 km/s)
Specific impulse,sea-level263.3 s (2.582 km/s)
Dimensions
Dry mass1,190 kg (2,620 lb)
References
References[2][3][4][5][6]
NotesPerformance figures are for RD-107A

TheRD-107and its sibling, theRD-108,are a type ofrocket engineused on theR-7 rocket family.RD-107 engines are used in each booster and the RD-108 is used in the central core. The engines have four maincombustion chambers(each a withnozzle) and either two (RD-107) or four (RD-108)vernierchambers.

The engines were first developed in the mid-1950s to launch theR-7 Semyorka,the firstintercontinental ballistic missile.The R-7 was later adapted into spacelaunch vehiclesand the engines have been improved over several generations. The most recent versions are theRD-107AandRD-108Aengines are used to launch theSoyuz-2,which is in active service as of 2024.

Design

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Turbopump schematic of the NPO Energomash RD-107 rocket engine.

The RD-107 was designed under the direction ofValentin Glushkoat the Experimental Design Bureau (OKB-456) between 1954 and 1957. It usesliquid oxygenandkeroseneas propellants operating in agas generatorcycle. As was typical by all the descendants of theV-2 rockettechnology, the turbine is driven by steam generated bycatalyticdecomposition ofH₂O₂.The steam generator uses solidF-30-P-Gcatalyst. These are based on a variable sized pellet covered in an aqueous solution ofpotassium permanganateandsodium.Each engine uses four fixed main combustion chambers. The RD-107 has an additional twoverniercombustion chambers that canthrust vectorin a single plane to supply attitude control. The RD-108 has four verniers to supply full vector control to the Blok-A stage. The single-axleturbopumpunit includes the steam driven turbine, an oxidizer pump, a fuel pump, and a nitrogen gas generator for tank pressurization.[3]

The RD-107 engines are used in each of the boosters of theSoyuz-2rocket, and a single RD-108 is used in the Blok-A stage (the central 1st stage).

One important innovation of this engine was the capability to use variablemixture ratiobetween fuel and oxidizer. The natural variations in manufacturing between each engine meant that without an active propellant consumption control, each booster could deplete oxygen and fuel at a different rate. This might result in as much as tens of tonnes of unused propellant near the end of the burn. It would generate enormous stress on the structure and cause difficulties in steering due to the mass imbalance. The mixture ratio control system was developed to ensure the simultaneous consumption of propellant mass among the four R-7 boosters.[3][7]

Production

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The RD-107 and RD-108 engines are produced at theJSC Kuznetsovplant inSamara, Russia,under the supervision of thePrivolzhskiybranch ofNPO Energomash,also known as theVolgabranch.[1][3][5]The Privolzhsky branch was organized as a branch of OKB-456 in 1958, specifically for the manufacture of RD-107 and RD-108 engines. The branch was led by Y.D. Solovjev until 1960, then by R.I. Zelenev until 1975, then by A.F. Udalov until 1978, and is currently led by A.A. Ganin.[8]

Versions

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Bottom of the Soyuz-2 showing the RD-107 engines in each booster and the RD-108 on the central core. Each has four nozzles and either two (RD-107) or four (RD-108) vernier nozzles.

RD-107 variants

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Modifications to the RD-107 design have led to production of several distinct versions of the engine:

  • RD-107(GRAUcode:8D74): Original version.[4]Used on ICBM versions of the R-7, 8K72, 8K72L, and 8K72K boosters.[3]
  • RD-107K(GRAU code:8D74K): Improved version of the 8D74. Used on 8K78, 8A92, 8A92M, and 11A57 boosters.[3]
  • RD-107ММ(GRAU code:8D728or8D74M): Increased thrust over the 8D74K by 5%.[4]Used on theMolniya-M(8К78М) and universally adopted on R-7 vehicles in 1966.[3]
  • RD-117(GRAU code:11D511): Improved structural changes.[4]Used on theSoyuz-U(11А511U) andSoyuz-U2(11A511U2).[3]
  • RD-107А(GRAU code:14D22): Improved version of the 11D511 with new injector design that eliminated high frequency combustion instabilities.[4]Used on theSoyuz-FG(11А511U-FG),Soyuz-STA(372RN21A) andSoyuz-STB(372RN21B).[3]
  • RD-107А(GRAU code:14D22KhZ): Chemical ignited version of the 14D22. Used on theSoyuz-2.1a(14A14-1A) andSoyuz-2.1b(14A14-1B).[3][9]
RD-107 family of engines
Engine RD-107 RD-107K RD-107ММ RD-117 RD-107A RD-107A
GRAU code 8D74 8D74K 8D728 or 8D74M 11D511 14D22 14D22KhZ
Development 1954-1959 1965-1976 1969-1975 1993-2001 2001-2004
Engine cycle Liquid propellantrocket engineburningRG-1/LOXin agas generatorcycle with the turbine driven by steam generated bycatalyticdecomposition ofH2O2
Combustion chamber pressure 5.88 MPa (853 psi) 5.88 MPa (853 psi) 5.85 MPa (848 psi) 5.32 MPa (772 psi) 6.00 MPa (870 psi) 6.00 MPa (870 psi)
Thrust, sea level 813.98 kN (182,990 lbf) 818.88 kN (184,090 lbf) 755.14 kN (169,760 lbf) 778.68 kN (175,050 lbf) 839.48 kN (188,720 lbf) 839.48 kN (188,720 lbf)
Thrust, vacuum 1,000.31 kN (224,880 lbf) 995.41 kN (223,780 lbf) 921.86 kN (207,240 lbf) Unknown 1,019.93 kN (229,290 lbf) 1,019.93 kN (229,290 lbf)
Specific impulse, sea level 256 s (2.51 km/s) 256.2 s (2.512 km/s) 257 s (2.52 km/s) 253 s (2.48 km/s) 263.3 s (2.582 km/s) 263.3 s (2.582 km/s)
Specific impulse, vacuum 313 s (3.07 km/s) 313.3 s (3.072 km/s) 314 s (3.08 km/s) 316 s (3.10 km/s) 320.2 s (3.140 km/s) 320.2 s (3.140 km/s)
Height 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,578 mm (101.5 in) 2,578 mm (101.5 in)
Diameter 1,850 mm (73 in) 1,850 mm (73 in) 1,850 mm (73 in) 1,850 mm (73 in) 1,850 mm (73 in) 1,850 mm (73 in)
Intended use R-7,Sputnik,Vostok,andVoskhod Molniya(8К78) Molniya-M(8К78М) andSoyuz(11A511) Soyuz-U(11А511U) andSoyuz-U2(11A511U2) Soyuz-FG(11А511U-FG),Soyuz-STA(372RN21A), andSoyuz-STB(372RN21B) Soyuz-2.1a(14A14-1A) andSoyuz-2.1b(14A14-1B)
Status Retired Retired Retired Retired In production In production
References Unless otherwise noted:[3][4]

RD-108 variants

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Similar modifications have led to several distinct versions of the RD-108:

  • RD-108(GRAU code:8D75): Original version.[4]Used on theR-7,Sputnik,VostokandVoskhod.[3]
  • RD-108K(GRAU code:8D75K): Improved version of the 8D74. Used on theMolniya(8К78).[3]
  • RD-108ММ(GRAU code:8D727or8D75M): Increased thrust over the 8D74K by 5%.[4]Used on theMolniya-M(8К78М) andSoyuz(11A511).[3]
  • RD-118(GRAU code:11D512): Improved structural changes.[4]Used on theSoyuz-U(11А511U).[3]
  • RD-118PF(GRAU code:11D512PF): Version of the 11D5212 that run onSyntinrather thanRG-1.It used selected injectors to minimize instabilities without changing constructions methods, but it required a significant number of engines produced to get injectors that complied with the stringent specifications. Used on theSoyuz-U2(11A511U2).[3][10]
  • RD-108А(GRAU code:14D21): Improved version of the 11D511 with new injector design that eliminated the high frequency combustion instabilities.[4]Used on theSoyuz-FG(11А511U-FG),Soyuz-STA(372RN21A) andSoyuz-STB(372RN21B).[3]
  • RD-108А(GRAU code:14D21KhZ): Chemical ignited version of the 14D22. Used on theSoyuz-2.1a(14A14-1A) andSoyuz-2.1b(14A14-1B).[3][9]
RD-108 family of engines
Engine RD-108 RD-108K RD-108ММ RD-118 RD-118PF RD-108A RD-108A
GRAU code 8D75 8D75K 8D727 or 8D75M 11D512 11D512PF[10] 14D21 14D21KhZ
Development 1954-1959 1965-1976 1969-1975 1979-1981 1993-2001 2001-2004
Engine cycle Liquid propellantrocket engineburningRG-1/LOXin thegas generatorcycle with the turbine driven by steam generated bycatalyticdecomposition ofH2O2
Propellant RG-1/LOX Syntin/LOX[10] RG-1/LOX
Combustion chamber pressure 5.10 MPa (740 psi) 5.10 MPa (740 psi) 5.32 MPa (772 psi) 5.85 MPa (848 psi) 5.39 MPa (782 psi) 5.44 MPa (789 psi) 5.44 MPa (789 psi)
Thrust, sea level 745.33 kN (167,560 lbf) 745.33 kN (167,560 lbf) 676.68 kN (152,120 lbf) 818.88 kN (184,090 lbf) Unknown 792.41 kN (178,140 lbf) 792.41 kN (178,140 lbf)
Thrust, vacuum 941.47 kN (211,650 lbf) 941.47 kN (211,650 lbf) 833.60 kN (187,400 lbf) 1,000.31 kN (224,880 lbf) Unknown 921.86 kN (207,240 lbf) 921.86 kN (207,240 lbf)
Specific impulse, sea level 248 s (2.43 km/s) 248.2 s (2.434 km/s) 253 s (2.48 km/s) 257 s (2.52 km/s) 263.5 s (2.584 km/s) 257.7 s (2.527 km/s) 257.7 s (2.527 km/s)
Specific impulse, vacuum 315 s (3.09 km/s) 314.2 s (3.081 km/s) 316 s (3.10 km/s) 314 s (3.08 km/s) Unknown 320.6 s (3.144 km/s) 320.6 s (3.144 km/s)
Height 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,865 mm (112.8 in) 2,865 mm (112.8 in)
Diameter 1,950 mm (77 in) 1,950 mm (77 in) 1,950 mm (77 in) 1,950 mm (77 in) 1,950 mm (77 in) 1,950 mm (77 in) 1,950 mm (77 in)
Intended use R-7,Sputnik,VostokandVoskhod Molniya(8К78) Molniya-M(8К78М) andSoyuz(11A511) Soyuz-U(11А511U) Soyuz-U2(11A511U2) Soyuz-FG(11А511U-FG),Soyuz-STA(372RN21A) andSoyuz-STB(372RN21B) Soyuz-2.1a(14A14-1A) andSoyuz-2.1b(14A14-1B)
Status Retired Retired Retired Retired Retired In production In production
References Unless otherwise noted:[3][4]

Work on the 14D21 and 14D22 engines started in 1986, with a preliminary design completed in 1993. These engines incorporate a new injector head design to increasespecific impulse.The first launch of aProgresscargo spacecraft using a launch vehicle equipped with these engines took place in May 2001. The firsthuman spaceflightlaunch utilizing these engines took place in October 2002.[5]

Hypergolic vs. pyrotechnic ignition

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Currently produced engines are ignited with apyrotechnicignition system. Energomash reports a new,hypergolicignition system (on engines designated 14D21KhZ and 14D22KhZ) are ready for certification and flight tests.[5]

See also

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References

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  1. ^ab"RD-107, RD-108".JSC Kuznetsov. Archived fromthe originalon 21 July 2015.
  2. ^"RD-107-8D74".Encyclopedia Astronautica. Archived fromthe originalon March 21, 2002.Retrieved2015-07-14.
  3. ^abcdefghijklmnopqrs"ЖРД РД-107 и РД-108 и их модификации"[RD-107 and RD-108 and their modifications] (in Russian).Retrieved2024-02-19.
  4. ^abcdefghijk"NPO Energomash list of engines".NPO Energomash.Archived fromthe originalon 7 November 2014.
  5. ^abcd"RD-107/108".NPO Energomash.Archived fromthe originalon 2 April 2015.
  6. ^John R. London III (October 1994).LEO on the Cheap(PDF).Air University Press. pp. 68–69.ISBN0-89499-134-5.Archived fromthe original(PDF)on 2008-05-14.
  7. ^Chertok, Boris (June 2006). "Chapter 16 — The Seven Problems of the R-7 Missile".Rockets and People Vol. 2 — Creating a Rocket Industry(PDF).Vol. 2 (NASA SP-2006-4110).NASA.p. 292.Retrieved2015-07-15.
  8. ^"History".NPO Energomash.Archived fromthe originalon 18 November 2014.
  9. ^abZak, Anatoly."Soyuz-2 launch vehicle (14A14)".RussianSpaceWeb.
  10. ^abcPillet, Nicolas."Le lanceur Soyouz-U2 (11A511U-2)"[The Soyuz-U2 Launcher (11A511U-2)] (in French). Kosmonavtika.Retrieved2015-07-14.
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