轴流压气机性能预测及喘振/堵塞流量边界分析
Performance Prediction and Surge/Chock Boundary Analysis of Axial Compressor
孙伟文 1王巍 2王晓放2
作者信息
- 1. 大连理工大学能源与动力学院,大连 116024
- 2. 大连理工大学能源与动力学院,大连 116024;大连理工大学海洋能源利用与节能教育部重点实验室,大连 116024
- 折叠
摘要
轴流压气机一维分析在压气机设计及性能快速预测领域具有重要作用,本文基于广泛实验得到的冲角、落后角及各类总压损失模型,建立了逐叶片排计算的一维平均中径程序,利用NASA 2级压气机验证了程序计算精度.通过对四类失速边界模型和三种堵塞边界模型的预测结果对比,分析各类模型在不同转速下的适用性,对压气机流量边界的一维预测提供指导,同时基于速度比提出了一种堵塞边界预测方法,取得较好的效果.
Abstract
One-dimensional analysis of axial compressor plays an important role in the field of compressor design and rapid performance prediction.Based on the incidence angle,deviation an-gle and a serial of total pressure loss models obtained by classical experiments,a one-dimensional meanline program is established in this paper.The accuracy of the program is verified with a NASA 2-stage compressor from public literature.By comparing the prediction results of four stall boundary models and three chock boundary models,the suitability of various models under different condition is analyzed,which provides guidance for one-dimensional prediction of compressor flow boundary.Meanwhile,a chock boundary prediction method based on velocity ratio is proposed with less error.
关键词
轴流压气机/一维平均中径法/特性仿真/流量边界预测Key words
axial compressor/one-dimensional meanline method/performance simulation/predic-tion of flow boundary引用本文复制引用
基金项目
国家科技重大专项(J2019-Ⅰ-0012-0012)
出版年
2024
NETL
NSTL
万方数据