高温降涡轮高位预旋供气系统设计  

Design of turbine high radius pre-swirl system with high temperature drop

作　　者：杨显赵 刘高文[1,2] 郭令颖 马佳乐 林阿强 YANG Xianzhao;LIU Gaowen;GUO Lingying;MA Jiale;LIN Aqiang(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Shanxi Key Laboratory of Thermal Science in Aero-engine System,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]西北工业大学陕西省航空动力系统热科学重点实验室,西安710072

出　　处：《航空学报》2025年第2期159-173,共15页Acta Aeronautica et Astronautica Sinica

基　　金：航空发动机及燃气轮机基础科学中心项目(P2022-A-Ⅱ-007-001);中国博士后科学基金(2023M742834);航空科学基金(2024M070053001)。

摘　　要：预旋供气系统性能优劣直接制约先进涡轮动叶冷气供给品质。本文应用功热转换理论开展涡轮高位预旋供气系统的正向设计研究,根据已知的边界条件计算出系统各特征截面的气动参数,确定各元件通流面积及其结构参数,通过一维计算结果构建三维物理模型,经转静子匹配迭代获得高性能预旋系统结构。重点开展高温降涡轮预旋供气系统的特性分析及性能评估。结果表明,在满足涡轮动叶供气流量和供气压力要求的前提下,一维设计计算和数值模拟结果的引气流量、系统温降和温降效率的相对偏差均低于1.5%,并且与对应实验结果的系统温降相对偏差小于1.5%。在设计点预旋喷嘴、接受孔和供气孔的流量系数分别为0.937、0.716和0.744;系统温降和温降效率分别达到61.53 K和80%,系统比功耗为-55.74 kW/(kg·s^(-1))。在保证涡轮动叶供气流量和供气压力的条件下,4个巡航工况点的系统温降达到了39.73~62.88 K,比功耗可达到-55.74~-16.48 kW/(kg·s^(-1))。The performance of the pre-swirl system directly restricts the cooling air quality of the turbine blades in the transition state.In this paper,the forward design of the turbine pre-swirl system is carried out by applying the theory of power-heat conversion.The aerodynamic parameters of each characteristic cross section of the system are calculated according to known boundary conditions,and the flux area of each element and its structural parameters are determined.The three-dimensional physical model is constructed through the results of the one-dimensional calculations,and the structure of high-performance pre-swirl system is obtained through rotor-stator matching iteration.The characterization and performance evaluation of the pre-swirl system with high temperature drop are conducted.The results show that the relative deviations of the bleed air mass flow rate,system temperature drop and temperature drop efficiency of the one-dimensional design calculations and numerical simulation results are less than 1.5%,and the relative deviations of the system temperature drop from the corresponding experimental results are less than 1.5%,provided that the turbine blades supply air mass flow rate and supply air pressure requirements are met.The discharge coefficients of the pre-swirl nozzle,receiver hole and supply hole at the design point are 0.937,0.716 and 0.744,respectively.The system temperature drop and temperature drop efficiency reach 61.53 K and 80%,respectively,and the specific power consumption of the system is−55.74 kW(/kg·s^(-1)).Under the condition of ensuring the turbine blades supply air mass flow rate and the supply air pressure,the system temperature drop at the four cruise operating points reaches 39.73–62.88 K,and the specific power consumption reaches -55.74--16.48 kW(/kg·s^(-1)).

关 键 词：航空发动机 预旋供气系统 一维设计 高温降 低功耗 性能评估 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]