Acta Aeronautica et Astronautica Sinica ›› 2023, Vol. 44 ›› Issue (21): 529343-529343.doi: 10.7527/S1000-6893.2023.29343
• Reviews • Previous Articles
Yifan WANG1, Zhengping ZOU1,2(), Maozhang CHEN2,3
Received:
2023-07-19
Revised:
2023-08-07
Accepted:
2023-09-07
Online:
2023-09-15
Published:
2023-09-15
Contact:
Zhengping ZOU
E-mail:zouzhengping@buaa.edu.cn
Supported by:
CLC Number:
Yifan WANG, Zhengping ZOU, Maozhang CHEN. Progress in thermodynamic cycle research of hypersonic precooled engine[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 529343-529343.
Table 1
Comparison of BH⁃MCESP gas properties calculation results
压力/MPa | 温度/K | 当量比 | BH-MCESP计算结果 | CEA计算结果 | 密度误差/ % | 定压比热误差/ % | ||
---|---|---|---|---|---|---|---|---|
密度/ (kg·m-3) | 定压比热/ (kJ·kg-1·K-1) | 密度/ (kg·m-3) | 定压比热/ (kJ·kg-1·K-1) | |||||
1.0 | 1 000 | 0.4 | 3.25 | 1.26 | 3.25 | 1.26 | 0 | -0.09 |
2 000 | 0.4 | 1.63 | 1.42 | 1.63 | 1.42 | 0.01 | -0.25 | |
1 000 | 0.8 | 3.05 | 1.39 | 3.05 | 1.38 | 0 | -0.10 | |
2 000 | 0.8 | 1.53 | 1.59 | 1.53 | 1.59 | 0.01 | -0.45 | |
1 000 | 1.2 | 2.79 | 1.52 | 2.79 | 1.52 | 0 | -0.12 | |
2 000 | 1.2 | 1.39 | 1.76 | 1.39 | 1.75 | 0 | -0.50 |
Table 2
Modeling methods of common components[53]
部件 | “零维”控制方程 |
---|---|
进气道 ( | |
换热器 ( 下标 | |
压气机(无引气) ( | |
涡轮(无冷却) ( | |
燃烧室 (下标f-燃料; | |
分流部件(两分流为例) ( | |
汇流部件(两汇流为例) ( | |
尾喷管(收扩临界为例,一般以冻结流动计算) ( | |
节流部件 ( |
Table 3
Properties of common fuels and coolants[71]
工质类型 | 氢 | 甲烷 | 乙醇 | 煤油 | 氦 | 氮 | 二氧化碳 | 水 |
---|---|---|---|---|---|---|---|---|
热值/(MJ·kg-1) | 118.4 | 49.7 | 26.8 | 43.1 | ||||
定压比热/(J·kg-1·K-1) | 14 540 | 2 950 | 3 121 | 2 000 | 5 192 | 1 069 | 1 058 | 4 658 |
气体常数/(J·kg-1·K-1) | 4 122 | 519 | 181 | 46 | 2 078 | 297 | 189 | 462 |
比热比 | 1.398 | 1.234 | 1.130 | 1.664 | 1.406 | 1.265 | 1.431 | |
导热系数/(W·m-1·K-1) | 0.223 5 | 0.068 3 | 0.148 2 | 0.150 0 | 0.221 9 | 0.039 4 | 0.034 0 | 0.642 7 |
动力黏度(μPa·s) | 10.5 | 17.2 | 395.8 | 2 400 | 28.4 | 26.1 | 23.8 | 117.3 |
存储温度(K) | 20 | 112 | 288 | 288 | 4 | 77 | 288 | 288 |
存储密度/(kg·m-3) | 71 | 415 | 729 | 820 | 124 | 806 | 802 | 997 |
Table 4
Previous direct precooled thermodynamic schemes
发动机 方案 | 研制国家 | 工作范围、性能及应用对象 | 典型技术特征 |
---|---|---|---|
LACE | 德国 | 1) 吸气模态Ma=0~7、比冲800 s;火箭模态Ma≥7。 2) 适用于SSTO飞行器。 | 1) 采用液氢作为冷源。 2) 将空气冷却至露点温度(81.7 K)以下,预冷器存在“夹点”问题,燃料消耗量大,导致比冲低。 3) 吸气模态与火箭模态共用燃烧室和喷管。 |
RB545 | 英国 | 1) 吸气模态Ma=0~5,火箭模态Ma≥5。 2) 发动机起飞推力367 kN,海平面比冲2 000 s。 3) 适用于单级入轨飞行器HOTOL。 | 1) 采用液氢作为冷源;部分氢气驱动涡轮。 2)压气机入口温度冷却至高于露点温度,空气压气机压比约150。 3) 预冷器面临氢脆及结冰问题。 4) 吸气模态与火箭模态共用燃烧室和喷管。 |
ATRDC | 俄罗斯 | 1) 吸气模态Ma=0~6,火箭模态Ma≥6。 2) 不带冲压通道,平均比冲2 500 s;在Ma≥2耦合冲压通道,平均比冲约4 000 s。 3) 推重比18~20。 | 1) 采用液氢冷却空气;部分氢气驱动涡轮。 2) 液氢冷却当量比约2.0。 3) 压气机入口温度98~112 K,空气压气机的压比20~40。 4) 预冷器约占整机质量40%。 5) 吸气式燃烧室和火箭燃烧室独立。 |
KLIN | 美国 | 1) 吸气模态Ma=0~6,火箭模态Ma≥6。 2) 适用于SSTO或TSTO第1级。 3) 比冲比氢氧火箭发动机最大可提高60%。 4) 推重比33。 | 1) 火箭和深度预冷涡喷发动机热力耦合。 2) 在地面空气压气机入口常温空气被冷却至110 K,压气机压比约30;在Ma=6时被冷却至200~250 K。 3) 喷注液氧防止预冷器结冰。 |
Table 5
Parameter schemes of SABRE⁃3
热力方案来源 | 循环特征 | 性能指标 |
---|---|---|
英国REL公司[ | 1) Ma=5深冷空气压气机进口约120 K。 2) 空气压气机压比约140。 3) 火箭燃烧室与吸气模态燃烧室共用。 4) 高推重比。 | 1) Ma=5比冲1 634 s。 2) Ma=5单位推力约1.24 kN/(kg·s-1)。 |
北京动力机械研究所陈操斌等[ | 1) 基于现有部件技术水平。 2) 适度预冷,Ma=5空气压气机进口301 K。 | 1) Ma=5比冲1 359 s。 2) Ma=5单位推力1.14 kN/(kg·s-1)。 |
国防科技大学Zhang等[ | 1) 基于超临界氦再循环的改进SABRE-3方案。 | 1) Ma=4.86比冲约2 452 s。 |
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