elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

A NUMERICAL ANALYSIS OF CROSS-FLOW REINFORCED IMPINGEMENT COOLING WITH A U-SHAPED FLOW-GUIDE ON THE HOLE PLATE

Brakmann, Robin and Brose, Nina and Carvalho, Francisco and Chargui, Safae and Guarino, Roberto (2023) A NUMERICAL ANALYSIS OF CROSS-FLOW REINFORCED IMPINGEMENT COOLING WITH A U-SHAPED FLOW-GUIDE ON THE HOLE PLATE. In: ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, GT 2023. Proceedings of ASME 2023 Turbomachinery Technical Conference, 2023-06-26 - 2023-06-30, Boston, MA, United States of America. doi: 10.1115/GT2023-101097.

Full text not available from this repository.

Official URL: https://asmedigitalcollection.asme.org/GT/proceedings-abstract/GT2023/87011/V07BT15A003/1168164

Abstract

Impingement cooling offers an efficient usage of cooling air in order to obtain high heat transfer rates. In this study a U-shaped turbulator is installed downstream of the jet hole. This arrangement uses the cross-flow to reinforce the jet by guiding it into the adjacent jet and thus increasing its effective jet Reynolds number. Compared to a smooth channel configuration, the Nusselt number on the target can be increased by 5–16% without a significant change in the pressure loss. This is a purely aerodynamic effect and is not caused by increasing the area of the heat exchanging surface. The geometry represents a generic impingement cooling configuration with a row of nine inline impingement jets. All jets are influenced by a self-induced cross-flow. The jet-to-plate spacing as well as jet pitch are set to 5D and the curved U-shape ribs are installed downstream of the jet on the hole plate. The RANS simulations are performed with the SST turbulence model. The effects of different jet-to-plate spacing, jet Reynolds number as well as rib height, position and shape are investigated numerically. The effectiveness of the U-shaped turbulator is discussed in combination with additional turbulators (from the literature). This paper concludes with a recommended set of rib and impingement parameters for the usage of the U-shaped turbulator in gas turbine cooling designs. A discussion of the manufacturability by Selective Laser Melting is included.

Item URL in elib:https://elib.dlr.de/199423/
Document Type:Conference or Workshop Item (Speech)
Title:A NUMERICAL ANALYSIS OF CROSS-FLOW REINFORCED IMPINGEMENT COOLING WITH A U-SHAPED FLOW-GUIDE ON THE HOLE PLATE
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Brakmann, RobinUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Brose, NinaUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Carvalho, FranciscoUNSPECIFIEDhttps://orcid.org/0000-0002-3069-8345UNSPECIFIED
Chargui, SafaeUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Guarino, RobertoUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Date:June 2023
Journal or Publication Title:ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, GT 2023
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI:10.1115/GT2023-101097
Status:Published
Keywords:Heat transfer, CFD, PIV, Impingement cooling, Prallkühlung, Turbine, Kühlung, cooling, internal cooling
Event Title:Proceedings of ASME 2023 Turbomachinery Technical Conference
Event Location:Boston, MA, United States of America
Event Type:international Conference
Event Start Date:26 June 2023
Event End Date:30 June 2023
Organizer:ASME
HGF - Research field:Energy
HGF - Program:Materials and Technologies for the Energy Transition
HGF - Program Themes:High-Temperature Thermal Technologies
DLR - Research area:Energy
DLR - Program:E VS - Combustion Systems
DLR - Research theme (Project):E - Combustion and Power Plant Systems
Location: Göttingen
Institutes and Institutions:Institute of Propulsion Technology > Turbine
Deposited By: Brakmann, Robin
Deposited On:28 Nov 2023 13:35
Last Modified:24 Apr 2024 21:00

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Website and database design: Copyright © German Aerospace Center (DLR). All rights reserved.