Acta Aeronautica et Astronautica Sinica ›› 2024, Vol. 45 ›› Issue (7): 29713-029713.doi: 10.7527/S1000-6893.2024.29713
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Zeyong YIN1(), Gaiqi LI2, Jiancheng SHI2, Yueqian YIN2
Received:
2023-10-12
Revised:
2023-11-10
Accepted:
2024-01-11
Online:
2024-04-15
Published:
2024-01-15
Contact:
Zeyong YIN
E-mail:yinzy14500043@608.aecc
Supported by:
CLC Number:
Zeyong YIN, Gaiqi LI, Jiancheng SHI, Yueqian YIN. Concept, method and practice of advanced versatile core engine derivative[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 29713-029713.
Table 1
Development of typical versatile core engine derivative in foreign countries
核心机 | 派生发展 | ||
---|---|---|---|
涡轴发动机 | 涡桨发动机 | 涡扇发动机 | |
T406核心机 (14级轴流,压比14, 环形直流燃烧室,2级轴流涡轮) | T406-AD-400 (功率4 586 kW, 耗油率0.255 kg/(kW∙h) (最大连续状态),装V-22) | AE2100J (功率3 426 kW, 装Saab 2000) | AE3007 (涵道比5.0,推力3 060 daN, 耗油率0.400 kg/(daN·h), 装EMB-145) |
GE27/GE38核心机 (5级轴流+一级离心,压比23, 环形直流燃烧室,2级冷却涡轮) | T407 (功率4 400 kW) | GLC38 (功率4 400 kW) | CFE738 (涵道比5.4,推力2 662 daN, 耗油率0.389 kg/(kgf·h), 装“猎鹰”2000) |
T55核心机 (7级轴流+一级离心,压比9.3, 环形回流燃烧室,2级冷却涡轮) | T55-L-714 (功率3 629 kW, 耗油率0.313 5 kg/(kW∙h), 装CH-47D) | ALF502 (涵道比5.0~5.89,推力2 978 daN, 耗油率0.422 kg/(daN·h), 装“挑战者”600) | |
T64核心机 (14级轴流,压比14, 环形直流燃烧室,2级冷却涡轮) | T64-GE-100 (功率3 326 kW, 耗油率0.286 kg/(kW∙h), 装CH-53E) | CT64-820-4 (功率2 336 kW, 装DHC-5D/5E) | TF34/CF34 (涵道比6.2,推力4 133 daN, 耗油率0.37 kg/(daN·h), 装“挑战者”601) |
RTM322核心机 (3级轴流+一级离心,压比15, 短环形燃烧室,2级冷却涡轮) | 涡轴型 (功率1 565~2 237 kW, 耗油率0.27 kg/(kW∙h) (最大连续状态),装EH101、NH90) | 涡桨型 (功率1 342~1 864 kW) | 涡扇型 (推力1 009~1 546 daN,装S-3A) |
D36核心机 (7级轴流,环形燃烧室, 1级冷却涡轮) | D136 (功率7 457 kW, 耗油率0.278 kg/(kW∙h),装米-26) | D36 (涵道比6.3,推力6 374 daN, 耗油率0.367 kg/(daN·h), 装安-72等) |
Table 4
Market forecast of various types of engines
发动机类型 | 推力/功率等级 | 需求量/台 | 市场价值/亿美元 |
---|---|---|---|
涡轴发动机 | <800 kW | 1 018 | 4.9 |
800~1 500 kW | 1 052 | 13.7 | |
>1 500 kW | 484 | 10.2 | |
涡桨发动机 | <800 kW | 967 | 4.8 |
800 ~1 500 kW | 1 020 | 6.1 | |
>1 500 kW | 120 | 0.56 | |
涡扇发动机 | <2 000 kgf | 624 | 8.6 |
2 000~4 000 kgf | 1 340 | 22.9 | |
4 000~10 000 kgf | 810 | 37.2 | |
燃气轮机 | <500 kW | 900 | 6.0 |
500~1 500 kW | 500 | 4.8 | |
>1 500 kW | 300 | 5.0 |
Table 5
Parameters of an advanced versatile core engine
对象 | 构型 | 参数 | 指标 | 国际在役发动机核心机指标[ |
---|---|---|---|---|
压气机 | 3级轴流+1级离心 | 绝热效率 | 约0.80 | 0.79~0.80 |
低疲劳循环寿命/次 | 约15 000 | ~15 000 | ||
燃烧室 | 环形回流 | 燃烧效率 | 0.998 | 0.995~0.999 |
总压损失/% | 3.5 | 3.5~4.0 | ||
涡轮 | 2级轴流 | 绝热效率 | 约0.89 | 0.85~0.89 |
低疲劳循环寿命/次 | 约12 000 | ~12 000 | ||
核心机 | 进口流量/(kg∙s-1) | 约4.0 | 4.0~5.0 | |
压比 | ≥13 | 12~16 | ||
T4/K | 约1 550 | 1 350~1 600 | ||
涡轮出口温度/核心机进口温度 | 约4.0 | 3.7~4.2 |
Table 6
Advanced performance of derived turboshaft engine
发动机 | 功率/ kW | 耗油率/ (kg·kW-1·h-1) | 单位功率/(kW·s·kg-1) | 压气机换算流量/ (kg·s-1) | 压比 | 涡轮进口总温/K | 取证时首翻期寿命/h | 研制 国家 |
---|---|---|---|---|---|---|---|---|
派生发展的涡轴 | 约1 100 | 约0.276 | 约280 | 约4.0 | 约13 | 约1 550 | 3 000 | 中国 |
Ardiden 1H1 Ardiden 3C[ | 1 014~1 243 | 0.283~0.288 | 268~286 | 3.54~4.63 | 12.7~15 | 1 450~1 550 | 3 000 | 法国 |
CTS800-4[ | 1 014~1 243 | 0.283~0.288 | 268~286 | 3.54~4.63 | 12.7~15 | 1 450~1 550 | 3 000 | 美国 |
Table 7
Advanced performance of derived turboprop engine
发动机 | 功率/ kW | 耗油率/ (kg·kW-1·h-1) | 单位功率/ (kW·s·kg-1) | 压气机换算流量/ (kg·s-1) | 压比 | 涡轮进口总温/K | 首翻期寿命/h | 研制 国家 |
---|---|---|---|---|---|---|---|---|
AEP100 | 900 | 0.31 | 约225 | 约4.0 | >13 | 约1 550 | 3 000 | 中国 |
PT6A-65B[ | 820 | 0.326 | 约191 | 4.3 | 10.0 | 3 500 | 加拿大 | |
ARDIDEN-3TP[ | 900 | 0.315 | 约13 | 约1 450 | 5 000 | 法国 | ||
TPE331-10[ | 746 | 0.338 | 214 | 3.49 | 10.8 | 1 323 | 3 000 | 美国 |
Table 8
Advanced performance of derived turbofan engine
发动机 | 起飞推力/ kgf | 起飞耗油率/ (kg·kgf-1·h-1) | 12 km、Ma=0.6巡航耗油率/ (kg·kgf-1·h-1) | 总压比 | 涡轮前温度/ K | 首翻期/ h | 推重比/ (kgf·kg-1) | 研制国家 |
---|---|---|---|---|---|---|---|---|
派生发展的涡扇 | 约850 | 约0.46 | 约0.69 | 约16 | 约1 550 | 约3 000 | 约3.7 | 中国 |
PW617F1-E[ | 784 | 0.52* | 0.74 | 12.4 | 1 320 | 3 500 | 4.5 | 加拿大 |
FJ44-1AP[ | 952 | 0.486* | 13.5 | 1 280 | 3 500 | 4.0 | 美国 | |
HF120[ | 929 | 0.48* | 0.714 | 24 | 1 480 | 5 000 | 4.2 | 美国和日本联合研制 |
Table 9
Advanced performance of derived vehicle gas turbine
发动机 | 功率/kW | 燃油消耗率/ (kg·kW-1·h-1) | 重量/kg | 输出转速/(r∙min-1) | 功重比/ (kW∙kg-1) | 涡轮进口 总温/K | 首翻期/h | 最大使用 高度/m | 研制国家 |
---|---|---|---|---|---|---|---|---|---|
派生发展的 车用燃机 | 约900 | 约0.32 | 约1 100 | 3 150 | 约0.90 | 约1 400 | 1 500 | 5 500 | 中国 |
AGT-1500[ | 780~1 119 | 0.28~0.34 | 1 120~1 200 | 3 000~3 150 | 0.82~0.98 | 1 330~1 466 | 1 000~1 500 | 5 500 | 美国 |
GTD-1250[ GTD-1500[ | 780~1 119 | 0.28~0.34 | 1 120~1 200 | 3 000~3 150 | 0.82~0.98 | 1 330~1 466 | 1 000~1 500 | 5 500 | 俄罗斯 |
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