Fusion algorithm of multi design points for turboshaft-turbofan variable cycle engine scheme design
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摘要:
针对有涡轴和涡扇两种工作模态的涡轴-涡扇变循环发动机，提出了其方案设计的多设计点融合算法。以涡喷发动机为例，对发动机多设计点设计的融合算法模型的建立方法进行了介绍； 建立了涡轴-涡扇变循环发动机的多设计点融合算法模型；确定涡轴-涡扇变循环发动机的典型工况点包括高空巡航涡扇模态工况点、地面涡轴模态工况点及转模态工况点，完成发动机方案设计；最后以各典型工况点处飞行器对发动机的性能需求为多设计点融合算法的输入条件，与常规方法得到的参数进行对比验证，结果差异在1%以内。所提出的多设计点融合算法可为变循环发动机总体方案设计提供借鉴。
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关键词:
- 涡轴-涡扇变循环发动机 /
- 多设计点 /
- 融合算法 /
- 垂直起降高速巡航飞行器 /
- 发动机方案设计
Abstract:A fusion algorithm of multi design points (FAMDP) was proposed for the design of turboshaft-turbofan variable cycle engine (TSFVCE) with two operating modes, including: turboshaft mode and turbofan mode. A turbojet engine was taken as an example to introduce the establishment of a FAMDP model. The FAMDP model for the TSFVCE was established. The typical operating points of the TSFVCE, including high-altitude cruise turbofan mode operating points, ground turboshaft mode oper-ating points, and modal conversion operating points, were determined, and the design of the engine scheme was completed. The performance requirements of the aircraft for the TSFVCE at each typical operating point were used as input for the FAMDP. Compared with the parameters obtained by conventional methods, the results showed a difference of less than 1%. The fusion algorithm of multi design points proposed can provide a reference for the overall design of variable cycle engines.
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图 1 涡轴-涡扇变循环发动机结构简图
Figure 1. Structure diagram of turboshaft-turbofan variable cycle engine
图 2 传统涡轮发动机总体性能匹配流程
Figure 2. Traditional turbine engine overall performance matching process
图 3 涡轴-涡扇变循环发动机最大状态控制规律
Figure 3. Maximum state control law of the turboshaft-turbofan variable cycle engine
图 4 各可调机构的调节规律和相关参数的变化情况
Figure 4. Adjustment rules of each adjustable mechanism and changes of relevant parameters
图 5 垂直起降高速巡航飞行器的转模态过程
Figure 5. Modal transition process of vertical take-off and landing aircraft
图 6 传统方法与多设计点融合算法设计流程对比
Figure 6. Comparison of design processes between traditional methods and fusion algorithms of multi design points
表 1 涡轴-涡扇变循环发动机设计点参数
Table 1. Design point parameters of turboshaft-turbofan variable cycle engine
部件 参数 数值 进气道 空气流量Wa /（kg/s） 118.02 Flade内涵风扇 增压比πf 1.48 Flade外涵风扇 增压比πFlade 1.98 导叶角度αFlade/（°） 0.0 CDFS 增压比πCDFS 1.53 导叶角度αCDFS/（°） −5.0 高压压气机 增压比πc 6.9 燃烧室 出口总温T4/K 1469.16 外涵道 第一涵道比γ1 0.11 第二涵道比γ2 3.0 注：Flade外涵风扇导叶角度为0°时表示导叶处于完全打开状 态，−90.0°时表示导叶处于完全关闭状态，外涵流道不再有 空气流入。 
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表 2 涡轴-涡扇变循环发动机设计点总体性能
Table 2. Overall performance of turboshaft-turbofan variable cycle engine
性能参数 数值 发动机地面推力Fn/daN 2574.9 单位推力Fs/（daN/（kg/s）） 21.82 耗油率ζ/（kg/（daN·h）） 0.8005
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表 3 各限制参数设计点处取值和最大限制值
Table 3. Value and the maximum limit value of each limiting parameter at the design point
限制参数 设计点取值 限制值 低压转子物理百分比转速nf 100.0 100.0 低压转子相对换算转速nf,cor 1.0 1.0 高压转子物理百分比转速nc 85.42 100.0 低压转子相对换算转速nc,cor 1.00 1.00 燃烧室出口温度T4/K 1469.2 1600.0
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表 4 涡轴-涡扇变循环发动机各设计点处相关参数
Table 4. Relevant parameters at each design point of the turboshaft-turbofan variable cycle engine
部件 参数 H=9 km，Ma=0.8 H=0 km，Ma=0 H=0.5 km，Ma=0 进气道 空气换算流量/（kg/s） 118.03 61.26 155.3 Flade内涵风扇 物理百分比转速 100.0 100.0 100.0 增压比 1.48 1.499 1.499 Flade外涵风扇 增压比 1.98 1.34 导叶角度/（°） 0.0 −90.0 −52.0 CDFS 增压比 1.53 1.53 1.53 导叶角度/（°） −5.0 −4.9 −4.9 高压压气机 物理百分比转速 85.42 90.0 89.51 增压比 6.9 6.76 6.77 燃烧室 出口总温/K 1469.16 1560.7 1546.87 涵道比 第一涵道比 0.11 0.11 0.11 第二涵道比 3.0 1.676 性能参数 推力/daN 2574.9 3334.0 单位推力/（daN/（kg/s）） 21.82 21.46 涡扇模态耗油率/（kg/（daN·h）） 0.8005 1.278 功率/kW 16500.0 12000.0 单位功率/（kW/（kg/s）） 269.35 77.26 涡轴模态耗油率/（kg/（kW·h）） 0.2754 0.355
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表 5 涡轴-涡扇变循环发动机性能设计要求
Table 5. Performance design requirements of the turboshaft-turbofan variable cycle engine
参数 H=9 km，Ma=0.8 H=0 km，Ma=0 H=0.5 km，Ma=0 推力/daN 2574.9 3334.0 涡扇模态耗油率/（kg/（daN·h）） 0.8005 1.278 功率/kW 16500.0 12000.0 涡轴模态耗油率/（kg/（kW·h）） 0.2754 0.355
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表 6 涡轴-涡扇变循环发动机部件参数
Table 6. Engine component parameters of turboshaft-turbofan variable cycle engine
部件 参数 H=9 km，Ma=0.8 H=0 km，Ma=0 H=0.5 km，Ma=0 进气道 空气流量/（kg/s） 118.74 61.48 156.5 Flade内涵风扇 物理百分比转速 100.0 100.0 100.0 增压比 1.48 1.499 1.499 Flade外涵风扇 增压比 1.98 1.34 导叶角度/（°） 0 −90.0 −52.2 CDFS 增压比 1.53 1.53 1.53 导叶角度/（°） −5.0 −4.9 −4.9 高压压气机 物理百分比转速 85.7 90.1 89.53 增压比 6.92 6.77 6.77 燃烧室 出口总温/K 1470.0 1561.4 1547.2 涵道比 第一涵道比 0.11 0.11 0.11 第二涵道比 3.0 1.677
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