Scaling of an existing 60 kN LOX/LCH4 combustion down to a liquid 2.5 kN HTP/Kerosene combustion of an innovative hyperboloid rocket engine in Ansys Fluent

Müller, Bruno (2026) Scaling of an existing 60 kN LOX/LCH4 combustion down to a liquid 2.5 kN HTP/Kerosene combustion of an innovative hyperboloid rocket engine in Ansys Fluent. Master's, Universität Stuttgart.

PDF
18MB

Item URL in elib:

https://elib.dlr.de/221475/

Document Type:

Thesis (Master's)

Title:

Scaling of an existing 60 kN LOX/LCH4 combustion down to a liquid 2.5 kN HTP/Kerosene combustion of an innovative hyperboloid rocket engine in Ansys Fluent

Authors:

Authors	Institution or Email of Authors	Author's ORCID iD	ORCID Put Code
Müller, Bruno	UNSPECIFIED	UNSPECIFIED	UNSPECIFIED

DLR Supervisors:

Contribution	DLR Supervisor	Institution or E-Mail	DLR Supervisor's ORCID iD
Thesis advisor	Ortelt, Markus	UNSPECIFIED	UNSPECIFIED
Thesis advisor	Ess, Peter	UNSPECIFIED	https://orcid.org/0000-0002-1605-5175
Thesis advisor	Schleutker, Thorn	UNSPECIFIED	https://orcid.org/0000-0002-1833-2850

Date:

2026

Open Access:

Yes

Number of Pages:

Status:

Published

Keywords:

Space Propulsion, Thrust Chamber, Ceramic Combustion Chamber

Institution:

Universität Stuttgart

Department:

Institut für Raumfahrtsysteme

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 - GreenStaRS | Green Satellite and Rocket Engine Systems (P)

Location:

Stuttgart

Institutes and Institutions:

Institute of Structures and Design > Space System Integration
Institute for Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Institute of Combustion Technology > Computer Simulation

Deposited By:

Ortelt, Markus

Deposited On:

23 Dec 2025 09:15

Last Modified:

23 Dec 2025 09:15

Repository Staff Only: item control page