Effects of boundary layer transition on the vane heat transfer in an integrated intermediate turbine duct

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2025-03-26 DOI:10.1016/j.ast.2025.110161

Ziyu Kang , Tayyab Raza Shah , Meijie Zhang , Chao Zhou

{"title":"Effects of boundary layer transition on the vane heat transfer in an integrated intermediate turbine duct","authors":"Ziyu Kang , Tayyab Raza Shah , Meijie Zhang , Chao Zhou","doi":"10.1016/j.ast.2025.110161","DOIUrl":null,"url":null,"abstract":"<div><div>As the inlet gas temperature of the high-pressure turbine further increases, the heat transfer of the intermediate turbine duct, which connects the high-pressure and low-pressure turbines, should also be considered. This paper investigates the heat transfer characteristics of the vane in an integrated intermediate turbine duct (IITD) by experimental, numerical, and analytical methods. The vane surface laminar-turbulent transition is found to have a key effect on the heat transfer of the vane. The surface heat transfer coefficient of the turbulent boundary layer after transition is <strong>more than twice higher than that of a laminar boundary layer.</strong> It is found that the acceleration features in the IITD can influence the flow transition and are accurately captured by the <span><math><mrow><mi>γ</mi><mo>−</mo><mi>R</mi><msub><mi>e</mi><mi>θ</mi></msub></mrow></math></span> model. A novel correlation related to the boundary layer transition of the IITD vane is proposed to predict the local Nusselt number on the vane and can reduce the time consumption for the heat transfer prediction by about <span><math><mrow><mn>1</mn><mo>/</mo><mn>4</mn></mrow></math></span>.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110161"},"PeriodicalIF":5.0000,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Aerospace Science and Technology","FirstCategoryId":"5","ListUrlMain":"https://www.sciencedirect.com/science/article/pii/S1270963825002329","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: 0

Abstract

As the inlet gas temperature of the high-pressure turbine further increases, the heat transfer of the intermediate turbine duct, which connects the high-pressure and low-pressure turbines, should also be considered. This paper investigates the heat transfer characteristics of the vane in an integrated intermediate turbine duct (IITD) by experimental, numerical, and analytical methods. The vane surface laminar-turbulent transition is found to have a key effect on the heat transfer of the vane. The surface heat transfer coefficient of the turbulent boundary layer after transition is more than twice higher than that of a laminar boundary layer. It is found that the acceleration features in the IITD can influence the flow transition and are accurately captured by the

γ - R e_{θ}

model. A novel correlation related to the boundary layer transition of the IITD vane is proposed to predict the local Nusselt number on the vane and can reduce the time consumption for the heat transfer prediction by about

1 / 4

查看原文本刊更多论文

边界层过渡对一体化中间涡轮风道叶片换热的影响

随着高压涡轮入口气体温度的进一步升高，连接高压和低压涡轮的中间涡轮风道的换热问题也要考虑进去。本文采用实验、数值和分析等方法研究了一体化中间涡轮风道叶片的传热特性。叶片表面的层流-湍流过渡对叶片的传热有重要影响。转换后的湍流边界层表面换热系数比层流边界层高2倍以上。研究发现，过渡段内的加速特性会影响流动转变，并被γ−Reθ模型准确地捕获。提出了一种新的与叶片边界层转捩相关的关系式来预测叶片上的局部努塞尔数，可将传热预测的时间减少约1/4。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

求助全文

约1分钟内获得全文求助全文

来源期刊

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.