TU BRAUNSCHWEIG

Current page: Welcome Page > Research Programs > SFB TR40

SFB TR40: Technological Foundations for the Design of Thermally and Mechanically Highly Loaded Components of Future Space Transportation Systems

Vicarious representative/spokesman and coordinator of Subarea B: Prof. Dr. -Ing. Rolf Radespiel

For detailed information feel welcome to visit the SFB TR40 homepage.

Mission

Logo des Forschungsprojektes SFB-TR 40

The aim of the special research field SFBTR40 is to integrate rocket propulsion into aerospace transportation systems thereby creating a compromise between research and development as well as production costs and desired performance. To achieve this, research focuses on chemical rocket propulsion in main drive units. For this type of propulsion provides the most profitable relation of development and production costs. Referring to this, to be able to compete with international suppliers, intensive support of research in the area of rocket propulsion is of great importance. For this reason technological progress and the generation of innovative ideas, based on fundamental research, constitute the cornerstones of the SFB TR40. Moreover, both joint collaboration and the exchange of ideas and expertise on a national level are considered to play a central role regarding the success and advancement of research in the area. In order to provide a profitable environment for research in the field of rocket propulsion, the German Research Foundation in July 2008 established the SFB TR40. The research field focuses on complexity and extreme technical and mechanical strains regarding aerospace transportation systems.

Research programs A, B, C and K

The SFB TR40 consists of five sub-projects (A, B, C, D and K), which focus on different aspects of the research area.

A: Structure Cooling

Brief Description of Activities:

Sub-project A deals with structure cooling regarding critical components of thrust chambers. Because of vast compressive load and extremely high temperatures inside the combustion chambers and nozzle throat, those components succumb extreme thermal stress. This leads to a pressure drop in the cooling system. In order to inhibit this transaction, the development of enhanced measures for film and transpiration cooling is needed. In this connection a variety of challenges has to be meat. Especially complex reciprocal effects between hot flow and coolant flow have to be investigated in detail before any prediction of heat transfer can be made. Further challenges exist regarding transpiration cooling, which can be of great advantage in combination with ceramic components.

Sub-Programs:

A1: Multi-scale Technology for the Simulation of Coolant Flow through Porous Media

A2: Film Cooling in Rocket Nozzles

A3: Impacts/Effects of Increased Heat Transfer during Oscillating Flow on Thermal Strain/Stress and Damping Performance of Resonators

A4: Numeric Simulation of Film Cooling in Supersonic Interfaces/Boundary Layers

A5: Innovative Cooling of Rocket Combustion Chambers

Sub-Project B: Stern Flow

Brief Description of Activities:

The focus of Sub-project B is on aerodynamic phenomena, which arise in different flow conditions in rocket propelled space transportation and their reciprocal effects on each other. Particularly in the transonic part of the trajectory, variations of flow inside the trail of the rocket-body as well as in the area of the nozzle flow can occur. Those may lead to unwished structural vibrations which have to be inhibited. A further task of the sub-project is the analysis of relevant dynamics of the stern flow and the exploration of a suitable simulation model for their prediction. In order to simulate aerodynamic interdependencies between the shear layers of the trail and hot nozzle flow, methods have been used that were based on/used for Reynolds Averaged Navier Stokes (RANS). However discrepancies occurred with regard to aerodynamic loads on the stern. This is the reason why the dynamics could not be solved in past surveys. This problem now is aimed to be solved with the help of a set of high-resolution experiments and turbulence resolving, numeric simulations.

Sub-programs:

B1: Experimental Analysis of interdependency between hot nozzle flow and transonic flow

B2: Computing of Actively and Passively Influenced Turbulent Shear Layers in Trail of Blunter Objects

B3: Experimental Methodology for the Characterisation of Turbulent Trail with Propulsion Jet

B4: Efficient Computing of Transonic Stern Flow with Hot Nozzle Jet

B5: RANS-Model for porous surfaces B6: Characterisation and Control of turbulent wake flow in transonic both with and without jet simulation

Sub-project C: Combustion Chamber

Brief Description of Activities:

The aim of the project is the development and interlinking of tools for the synthesis of new engines. These tools are meant to help generating a reliable computation of thermo-fluid dynamical processes in rocket thrust chambers. With regard to this, two elements have to be taken into consideration: on one side the characterisation of compressible stationary reacting flows related with mainly convective heat transmission onto the walls and on the other side computation of stability against the appearance of dangerous combustion instabilities. In the long run, the sub-project aims at modelling the just described phenomena with the help of developed tools and inside a film cooled combustion chamber with various injectors (demonstrator thrust chamber).

Sub-Programs:

C1: Modelling of injection, mixing and combustion processes in rocket engines under compressibility conditions

C3: Thermal-fluid Dynamic Instabilities in Rocket Engines

C4: Experimental and Numeric Investigation of evaporation processes in the trans-critical area

C5: Subcritical and Supercritical Simulation of Rocket Combustion Chambers with Assumed- and transport equation-PDF-techniques

C6: modelling of Heat Transmission in Rocket Combustion Chambers

C7: Interdependencies between Acoustics and Combustion in Rocket Combustion Chambers

Sub-Project D: Jet Nozzle

Brief Description of Activities:

Sub-project D encompasses various particular projects that concentrate on modelling and physical foundations concerning thermal and mechanical fluid-structure interdependencies inside the thrust nozzle. In order to control these interdependencies, the different projects focus on the generation of new concepts and methods. Sub-Project D is highly interlinked with the other sub-projects since physical relations and interdependencies are important phenomena also related to research on the prediction of combustion chamber flow as well as stern flow.

Sub-programs:

D1: Interlinked solution approaches and sensitivity analysis of Aero Thermo-elastic Problems in Supersonic

D2: Mechanic Integrity of Thermal Insulation Layers – Layer Development and Micromechanics

D3: Prediction of Durability for Nozzle Structure Exposed to Flow Loadings

D4: Interdependency of flow and structure in thrust nozzles

D6: Experimental Surveys Concerning Flow-structure Interdependencies on Generic Models

D7: Development of New Fibre-Ceramic Materials for Thrust Chambers

D8: Discreet Damages in Rocket Engines

D9: Experimental Surveys for Lifetime/Durability Predictions

Sub-project K: Thrust Chamber

Brief Description of Activities:

Sub-project K focuses on the practical application of developed methods and concepts. Moreover it engages in measures for the conception of VDS and the clearance of the demonstrator-thrust chamber. Therefore sub-project K is completed by those sub-programs that concentrate on the development and improvement of methods and concepts, which can be applied for the previously mentioned tasks. Sub-programs: K1: Experimental and Numeric Surveys of Combustion and Heat Transmission in Rocket Thrust Chambers K2: Study of Dual Bell Nozzles under Application-oriented Conditions K3: Experimental Examination of Injector-Wall-Interdependency in a 2D Model of a Rocket Combustion Chamber.

For detailed information on the sub-projects and their particular activities you are welcome to visit the SFB TR40 homepage.


  last changed 20.06.2016
TU_Icon_E_Mail_1_17x17_RGB pagetop