RD-107
 | |
| 原产国 |  苏联、 俄罗斯 |
|---|---|
| 设计者 | OKB-456 |
| 制造者 | Кузнецов[1] |
| 用途 | 增压发动机 |
| 相关产品 | R-7系列火箭 |
| 上一代产品 | RD-105 |
| 现状 | 生产中 |
| 液体 | |
| 性能 | |
| 推力（真空） | RD-107：1,000 kN（220,000 lbf） RD-107A：1,020 kN（230,000 lbf） |
| 推力（海平面） | RD-107：810 kN（180,000 lbf） RD-107A：839 kN（189,000 lbf） |
| 比冲（真空） | RD-107：313 s RD-107A：320.2 s |
| 比冲（海平面） | RD-107：256 s RD-107A：263.3 s |
| 尺寸 | |
| 净重 | RD-107：1,190千克（2,620磅） RD-107A1,190千克（2,620磅） |
| 用于 | |
| R-7系列火箭第一级助推器 | |
| 参考文献 | |
| 参考文献 | [2][3][4][5][6] |
RD-107（РД-107；索引8Д74）是一种火箭发动机，最初用于发射R-7弹道导弹，但后来用于造R-7系列火箭。用于联盟号家族所有运载火箭第一级的每个侧块。截至2021年[update]，非常相似的RD-107A和RD-108A引擎也用于发射现役联盟2号运载火箭。[7]
设计
[编辑]
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 of such vernier combustion chambers 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 boosters would deplete oxygen and fuel at different rates. This might result in as much as tens of tonnes of unburned propellant near the end of the burn. It would generate enormous strains on the structure and control authority due to the mass imbalance. Thus, the mixture ratio control system was developed to ensure the simultaneous consumption of propellant mass among the four R-7 boosters.[3][8]
生产
[编辑]The 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.[9]
自燃与烟火点火
[编辑]Currently 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]
RD-107变体
[编辑]Modifications to the RD-107 design have led to production of several distinct versions of the engine:
- RD-107（索引8D74）：原始版本。[4] Used on the R-7, Sputnik, Vostok and Voskhod.[3]
- RD-107K（索引8D74K）：Improved version of the 8D74. Used on the Molniya (8К78).[3]
- RD-107ММ（索引8D728 or 8D74M）：Increased thrust over the 8D74K by 5%.[4] Used on the Molniya-M (8К78М) and Soyuz (11A511).[3]
- RD-117（索引11D511）：Improved structural changes.[4] Used on the Soyuz-U (11А511U) and Soyuz-U2 (11A511U2).[3]
- RD-107А（索引14D22）：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-107А（索引14D22KhZ）：Chemical ignited version of the 14D22. Used on the Soyuz-2.1a (14A14-1A) and Soyuz-2.1b (14A14-1B).[3][10]
| Engine | RD-107 | RD-107K | RD-107ММ | RD-117 | RD-107A | RD-107A |
|---|---|---|---|---|---|---|
| 索引 | 8D74 | 8D74K | 8D728 or 8D74M | 11D511 | 14D22 | 14D22KhZ |
| 发展 | 1954-1959 | 1965-1976 | 1969-1975 | 1993-2001 | 2001-2004 | |
| 发动机循环 | 液体火箭发动机在气体发生器循环燃烧火箭推进剂-1/液氧催化分解H2O2产生的蒸汽驱动涡轮循环 | |||||
| 燃烧室压力 | 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） |
| 海平面推力 | 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） |
| 真空推力 | 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） |
| 海平面比冲 | 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） |
| 真空比冲 | 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） |
| 高度 | 2,865 mm（112.8英寸） | 2,865 mm（112.8英寸） | 2,865 mm（112.8英寸） | 2,865 mm（112.8英寸） | 2,578 mm（101.5英寸） | 2,578 mm（101.5英寸） |
| 直径 | 1,850 mm（73英寸） | 1,850 mm（73英寸） | 1,850 mm（73英寸） | 1,850 mm（73英寸） | 1,850 mm（73英寸） | 1,850 mm（73英寸） |
| 状态 | 退休 | 退休 | 退休 | 退休 | 生产中 | 生产中 |
| 参考 | 除非另有说明：[3][4] | |||||
参考
[编辑]- ^ 1.0 1.1 RD-107, RD-108. JSC Kuznetsov. （原始内容存档于21 July 2015）.
- ^ RD-107-8D74. Encyclopedia Astronautica. [2015-07-14]. （原始内容存档于March 21, 2002）.
- ^ 3.00 3.01 3.02 3.03 3.04 3.05 3.06 3.07 3.08 3.09 3.10 ЖРД РД-107 и РД-108 и их модификации [RD-107 and RD-108 and their modifications]. [2015-07-14]. （原始内容存档于2012-08-26） （俄语）.
- ^ 4.0 4.1 4.2 4.3 4.4 4.5 NPO Energomash list of engines. NPO Energomash. （原始内容存档于7 November 2014）.
- ^ 5.0 5.1 5.2 RD-107/108. NPO Energomash. （原始内容存档于2 April 2015）.
- ^ John R. London III. LEO on the Cheap (PDF). Air University Press. October 1994: 68–69. ISBN 0-89499-134-5. （原始内容 (PDF)存档于2008-05-14）.
- ^ Engines. NPO Energomash. （原始内容存档于29 October 2014）.
- ^ Chertok, Boris. Chapter 16 — The Seven Problems of the R-7 Missile. Rockets and People Vol. 2 — Creating a Rocket Industry (PDF). 2 (NASA SP-2006-4110). NASA. June 2006: 292 [2015-07-15]. （原始内容存档 (PDF)于2020-04-03）.
- ^ History. NPO Energomash. （原始内容存档于18 November 2014）.
- ^ Zak, Anatoly. Soyuz-2 launch vehicle (14A14). RussianSpaceWeb. [2022-12-29]. （原始内容存档于2016-04-30）.
