{"title":"Combustor technology of high temperature rise for aero engine","authors":"Qinghua Zeng, Xuanwu Chen","doi":"10.1016/j.paerosci.2023.100927","DOIUrl":null,"url":null,"abstract":"<div><p>The development of advanced military aero-engines with high thrust-to-weight ratios requires high-temperature-rise (HTR) technology for core component combustors. This poses a major challenge to multidisciplinary design and optimization of combustors. This paper analyzes the technical characteristics of the HTR combustor and summarizes and proposes three current major technical challenges. For each technical challenge, systematic analysis and comprehensive discussion are conducted from the aspects of technical strategies and research progress. The three technologies reviewed in this paper include (1) combustion configuration technology, (2) liner thermal protection technology involving advanced liner cooling and ceramic matrix composite (CMC) liners, and (3) outlet distribution control technology. We also present our insights regarding current solutions and future research trends related to the three major technical limitations of the HTR combustor.</p></div>","PeriodicalId":54553,"journal":{"name":"Progress in Aerospace Sciences","volume":"140 ","pages":"Article 100927"},"PeriodicalIF":11.5000,"publicationDate":"2023-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"1","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Progress in Aerospace Sciences","FirstCategoryId":"5","ListUrlMain":"https://www.sciencedirect.com/science/article/pii/S037604212300043X","RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q1","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}
引用次数: 1
Abstract
The development of advanced military aero-engines with high thrust-to-weight ratios requires high-temperature-rise (HTR) technology for core component combustors. This poses a major challenge to multidisciplinary design and optimization of combustors. This paper analyzes the technical characteristics of the HTR combustor and summarizes and proposes three current major technical challenges. For each technical challenge, systematic analysis and comprehensive discussion are conducted from the aspects of technical strategies and research progress. The three technologies reviewed in this paper include (1) combustion configuration technology, (2) liner thermal protection technology involving advanced liner cooling and ceramic matrix composite (CMC) liners, and (3) outlet distribution control technology. We also present our insights regarding current solutions and future research trends related to the three major technical limitations of the HTR combustor.
期刊介绍：
"Progress in Aerospace Sciences" is a prestigious international review journal focusing on research in aerospace sciences and its applications in research organizations, industry, and universities. The journal aims to appeal to a wide range of readers and provide valuable information.
The primary content of the journal consists of specially commissioned review articles. These articles serve to collate the latest advancements in the expansive field of aerospace sciences. Unlike other journals, there are no restrictions on the length of papers. Authors are encouraged to furnish specialist readers with a clear and concise summary of recent work, while also providing enough detail for general aerospace readers to stay updated on developments in fields beyond their own expertise.
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