The RD-107 and its sibling, the RD-108, are a type of rocket engine used on the R-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 main combustion chambers (each a with nozzle) and either two (RD-107) or four (RD-108) vernier chambers.
 RD-107 engine on display at the Museum of Space and Missile Technology in Saint Petersburg. | |
| Country of origin | Soviet Union Russia |
|---|---|
| Designer | OKB-456 |
| Manufacturer | JSC Kuznetsov[1] |
| Application | Booster/first stage |
| Associated LV | R-7 family |
| Predecessor | RD-105 |
| Status | In production |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Gas-generator |
| Performance | |
| Thrust, vacuum | 1,020 kN (230,000 lbf) |
| Thrust, sea-level | 839 kN (189,000 lbf) |
| Specific impulse, vacuum | 320.2 s (3.140 km/s) |
| Specific impulse, sea-level | 263.3 s (2.582 km/s) |
| Dimensions | |
| Dry mass | 1,190 kg (2,620 lb) |
| References | |
| References | [2][3][4][5][6] |
| Notes | Performance figures are for RD-107A |
The engines were first developed in the mid-1950s to launch the R-7 Semyorka, the first intercontinental ballistic missile. The R-7 was later adapted into space launch vehicles and the engines have been improved over several generations. The most recent versions are the RD-107A and RD-108A engines are used to launch the Soyuz-2, which is in active service as of 2024[update].
Design
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The RD-107 was designed under the direction of Valentin Glushko at the Experimental Design Bureau (OKB-456) between 1954 and 1957. It uses liquid oxygen and kerosene as propellants operating in a gas generator cycle. As was typical by all the descendants of the V-2 rocket technology, the turbine is driven by steam generated by catalytic decomposition of H₂O₂. The steam generator uses solid F-30-P-G catalyst. These are based on a variable sized pellet covered in an aqueous solution of potassium permanganate and sodium. Each engine uses four fixed main combustion chambers. The RD-107 has an additional two vernier combustion chambers that can thrust vector in 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-axle turbopump unit 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 the Soyuz-2 rocket, 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 variable mixture ratio between 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
editThe RD-107 and RD-108 engines are produced at the JSC Kuznetsov plant in Samara, Russia, under the supervision of the Privolzhskiy branch of NPO Energomash, also known as the Volga branch.[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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RD-107 variants
editModifications to the RD-107 design have led to production of several distinct versions of the engine:
- RD-107 (GRAU code: 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: 8D728 or 8D74M): Increased thrust over the 8D74K by 5%.[4] Used on the Molniya-M (8К78М) and universally adopted on R-7 vehicles in 1966.[3]
- RD-117 (GRAU code: 11D511): Improved structural changes.[4] Used on the Soyuz-U (11А511U) and Soyuz-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 the Soyuz-FG (11А511U-FG), Soyuz-STA (372RN21A) and Soyuz-STB (372RN21B).[3]
- RD-107А (GRAU code: 14D22KhZ): Chemical ignited version of the 14D22. Used on the Soyuz-2.1a (14A14-1A) and Soyuz-2.1b (14A14-1B).[3][9]
| 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 propellant rocket engine burning RG-1/LOX in a gas generator cycle with the turbine driven by steam generated by catalytic decomposition of H2O2 | |||||
| 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, and Voskhod | Molniya (8К78) | Molniya-M (8К78М) and Soyuz (11A511) | Soyuz-U (11А511U) and Soyuz-U2 (11A511U2) | Soyuz-FG (11А511U-FG), Soyuz-STA (372RN21A), and Soyuz-STB (372RN21B) | Soyuz-2.1a (14A14-1A) and Soyuz-2.1b (14A14-1B) |
| Status | Retired | Retired | Retired | Retired | In production | In production |
| References | Unless otherwise noted:[3][4] | |||||
RD-108 variants
editSimilar modifications have led to several distinct versions of the RD-108:
- RD-108 (GRAU code: 8D75): Original version.[4] Used on the R-7, Sputnik, Vostok and Voskhod.[3]
- RD-108K (GRAU code: 8D75K): Improved version of the 8D74. Used on the Molniya (8К78).[3]
- RD-108ММ (GRAU code: 8D727 or 8D75M): Increased thrust over the 8D74K by 5%.[4] Used on the Molniya-M (8К78М) and Soyuz (11A511).[3]
- RD-118 (GRAU code: 11D512): Improved structural changes.[4] Used on the Soyuz-U (11А511U).[3]
- RD-118PF (GRAU code: 11D512PF): Version of the 11D5212 that run on Syntin rather than RG-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 the Soyuz-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 the Soyuz-FG (11А511U-FG), Soyuz-STA (372RN21A) and Soyuz-STB (372RN21B).[3]
- RD-108А (GRAU code: 14D21KhZ): Chemical ignited version of the 14D22. Used on the Soyuz-2.1a (14A14-1A) and Soyuz-2.1b (14A14-1B).[3][9]
| 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 propellant rocket engine burning RG-1/LOX in the gas generator cycle with the turbine driven by steam generated by catalytic decomposition of H2O2 | ||||||
| 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, Vostok and Voskhod | Molniya (8К78) | Molniya-M (8К78М) and Soyuz (11A511) | Soyuz-U (11А511U) | Soyuz-U2 (11A511U2) | Soyuz-FG (11А511U-FG), Soyuz-STA (372RN21A) and Soyuz-STB (372RN21B) | Soyuz-2.1a (14A14-1A) and Soyuz-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 increase specific impulse. The first launch of a Progress cargo spacecraft using a launch vehicle equipped with these engines took place in May 2001. The first human spaceflight launch utilizing these engines took place in October 2002.[5]
Hypergolic vs. pyrotechnic ignition
editCurrently produced engines are ignited with a pyrotechnic ignition system. Energomash reports a new, hypergolic ignition system (on engines designated 14D21KhZ and 14D22KhZ) are ready for certification and flight tests.[5]
See also
editReferences
edit- ^ a b "RD-107, RD-108". JSC Kuznetsov. Archived from the original on 21 July 2015.
- ^ "RD-107-8D74". Encyclopedia Astronautica. Archived from the original on March 21, 2002. Retrieved 2015-07-14.
- ^ a b c d e f g h i j k l m n o p q r s "ЖРД РД-107 и РД-108 и их модификации" [RD-107 and RD-108 and their modifications] (in Russian). Retrieved 2024-02-19.
- ^ a b c d e f g h i j k "NPO Energomash list of engines". NPO Energomash. Archived from the original on 7 November 2014.
- ^ a b c d "RD-107/108". NPO Energomash. Archived from the original on 2 April 2015.
- ^ John R. London III (October 1994). LEO on the Cheap (PDF). Air University Press. pp. 68–69. ISBN 0-89499-134-5. Archived from the original (PDF) on 2008-05-14.
- ^ 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. Retrieved 2015-07-15.
- ^ "History". NPO Energomash. Archived from the original on 18 November 2014.
- ^ a b Zak, Anatoly. "Soyuz-2 launch vehicle (14A14)". RussianSpaceWeb.
- ^ a b c Pillet, Nicolas. "Le lanceur Soyouz-U2 (11A511U-2)" [The Soyuz-U2 Launcher (11A511U-2)] (in French). Kosmonavtika.com. Retrieved 2015-07-14.
External links
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