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

Parametric Optimization of Turbopump for Reusable Rocket Engine (RRE) Applications

Gulczynski, Mateusz T. and Dos Santos Hahn, Robson Henrique and Waxenegger-Wilfing, Günther and Deeken, Jan C. and Oschwald, Michael (2023) Parametric Optimization of Turbopump for Reusable Rocket Engine (RRE) Applications. In: 34th International Symposium on Space Technology and Science, 2023-o (-1-07). The Japan Society for Aeronautical and Space Sciences. 34th International Symposium on Space Technology and Science, 3-9 June 2023, Kurume in Fukuoka, JAPAN. (In Press)

[img] PDF

Official URL: https://archive.ists.ne.jp/


With the development of contemporaneous reusable launchers, including projects such as Themis with a liquid LOX/LCH4 Prometheus engine, CALLISTO - Reusable VTVL launcher first stage demonstrator with a LOX/LH2 RSR2 engine, or Space-X’s Falcon 9 with a Merlin 1 engine, it is essential to further advance control algorithms to secure a failure-free engine operation. The engine's multi-restart capability not only implies additional requirements regarding throttling, where an extended controller-validity domain must be attained to safely reach low thrust levels for various engine operating regimes, but primarily increases the likelihood of component failure, including evolving parameters related to the mission profile. Therefore, to efficiently evaluate the fully continuous engine phases from start-up to shutdown transient, the dynamic reliability of the reusable rocket engine (RRE) is assessed along with its subcomponents under assorted failure modes, and a study based on multi-physics system-level modelling and simulation is proposed with a focus on the turbopump components. The modelling and performance analysis under transient conditions are conducted with EcosimPro ESPSS software, an object-oriented programming language. Within the presented deterministic thermically dependent structural simulation, the main control objectives pertain to end-state tracking of combustion chamber pressure and mixture ratios, along with operational constraints verification based on the LUMEN demonstrator engine and LE-5B-2 engine class. To predict the turbopump components remaining useful life, a model-based method for turbopump optimization incorporating analytical (0D) calculation is utilized.

Item URL in elib:https://elib.dlr.de/195494/
Document Type:Conference or Workshop Item (Speech)
Title:Parametric Optimization of Turbopump for Reusable Rocket Engine (RRE) Applications
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Gulczynski, Mateusz T.UNSPECIFIEDhttps://orcid.org/0000-0001-5932-8981UNSPECIFIED
Dos Santos Hahn, Robson HenriqueUNSPECIFIEDhttps://orcid.org/0000-0002-2389-2043UNSPECIFIED
Waxenegger-Wilfing, GüntherUNSPECIFIEDhttps://orcid.org/0000-0001-5381-6431UNSPECIFIED
Deeken, Jan C.UNSPECIFIEDhttps://orcid.org/0000-0002-5714-8845UNSPECIFIED
Oschwald, MichaelUNSPECIFIEDhttps://orcid.org/0000-0002-9579-9825UNSPECIFIED
Journal or Publication Title:34th International Symposium on Space Technology and Science
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Publisher:The Japan Society for Aeronautical and Space Sciences
Series Name:Special Session on Sustainable Space Transportation for the Next-Generation
Status:In Press
Keywords:EcosimPro European Space Propulsion System Simulation (ESPSS), Engine Cycle Modelling, Reusable Rocket Engine (RRE), Fatigue Life Analysis, Turbine Blade, Turbopump
Event Title:34th International Symposium on Space Technology and Science
Event Location:Kurume in Fukuoka, JAPAN
Event Type:international Conference
Event Dates:3-9 June 2023
Organizer:The Japan Society for Aeronautical and Space Sciences
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Project LUMEN (Liquid Upper Stage Demonstrator Engine)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion
Deposited By: Gulczynski, Mateusz T.
Deposited On:19 Jun 2023 11:03
Last Modified:27 Jun 2023 12:21

Repository Staff Only: item control page

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