Grk Introduction

8/20/2019 Grk Introduction

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Research Training Group 1095/2: Aero-Thermodynamic Design of a Scramjet Propulsion System

Aero-Thermodynamic Design of a Scramjet

Propulsion System:The graduate school GRK 1095/2 funded by the

“ Deutsche Forschungsgemeinschaft“ (DFG)

B. Weigand

Universität Stuttgart

Institut für Thermodynamik der Luft- und Raumfahrt


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1. Introduction

2. Research Training Group - GRK 1095/2

- Basic concept

- Structure of the GRK

- Educational-program

3. Selected results

- Project group A: “Aero-thermodynamical analysis”

- Project group B: “Combustion”

- Project group C: “Nozzle flow and system analysis”

4. Conclusion and Outlook

Contents


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Startschub: ca. 12 MN

Nutzlast: 6,5 to

Brennstoff: LH2 26 to, LOx 132 to


Nutzlast: 6,5 to



Startgewicht: 2000 to

Nutzlast: 28 to



Startgewicht: 2000 to

Nutzlast: 28 to


Ariane 5

Ariane 5 Space Shuttle

Space Shuttle

Introduction


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Ramjet: - No moving parts; ram compression

- Compression of the soaked up mass flow by reducing the flow speed tosubsonic velocity inside the intake → subsonic combustion

- Mach number range: 2 ÷ 6

But: Increase of airspeed M∞>6

a) increasing shock losses inside the intake

b) increasing stagnation temperature at the entry of the combustion

chamber → increasing dissociation

Way out: - Reducing the flow speed inside the inlet to 30 - 50 % of the airspeed

- Supersonic flow inside combustion chamber

⇒ supersonic combustion

- Mach number range: 5 ÷ ~25

Scramjet: Supersonic Combustion Ramjet

Introduction – What is a “Scramjet”?


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Introduction – Examples

Hyper X-43

f irst stage

combined

engine, scramjet

second

stage

Sänger*-concept

*germ. aerospace-engineer, 1905-1964


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1. Introduction


- Basic concept

- Structure of the GRK- Educational-program

3. Selected results

- Project group A: “Aero-thermodynamical analysis”- Project group B: “Combustion”


4. Conclusion and outlook

Contents


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Ltot>1000 mmdm/dt: =1.45 kg/s

LF=450 ÷ 500 mmρ∞=1.801⋅10-2 kg/m3

h=228 mmT∞=226.7 K

b≈76 mmp∞=11.7 hPa

α2≈19°M=8

α1≈7,5°H=30 km

Geometry:Inflow data:

Topic: Aero-thermodynamic design of a scramjet propulsion system for futurereusable space transportation systems and hypersonic flight

Basic Concept

2D / 3D-inlet

with double ramp

Combustion chamber

with strut Injector

SERN-Nozzle

Isolator

- Group A: Aero-thermodynamical analysis

- Group B: Combustion

- Group C: Nozzle flow and system analysis


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Group A: Aero-thermodynamic investigations

A1: Experimental investigations of the boundary layer transition of a double ramp configuration.

A2: Experimental investigation of the shock boundary layer interaction of a double ramp

configuration at different inflow conditions.

A3: Design and characterization of a 3D scramjet inlet.

A4: Experimental investigation of the internal flow conditions of a scramjet engine.

A5: Investigation of 3D flow structures caused by side wall effects of a scramjet engine.

A6: Numerical simulations of the unsteady effects in a scramjet intake.

A7: Computational analysis of the relaminarisation in hypersonic intake flows.

A8: Numerical investigation of the sensitivity on the design of a hypersonic intake.

Structure and sub-projects


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Group B: Combustion

B1: Experimental investigations of the fuel injection and mixing and stability of a supersonic

combustor.

B2: Numerical investigation of a supersonic combustion chamber for different flight conditions.

B3: Thermal and mechanical investigations of a central injector in a scramjet combustor.

B4: Numerical investigation of the turbulence-chemical reaction interaction and the emission

production in a scramjet combustor.

B5: Unsteady simulations of supersonic combustion chambers.

B6: Development of a numerical efficient combustion model for the interaction between

chemical reaction and turbulence for LES.

B7: Shock-boundary layer interaction for reactive flows.

B8: Prevention of thermal cocking in supersonic combustors by using staged injection..



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Group C: Nozzle flow and system analysis

C1: Aerodynamic design of a flight configuration and the related instrumentation.

C2: Numerical simulation of a nozzle flow with cooling.

C3: Experimental investigation of the expansion flow of an air breathing propulsion system under

consideration of the temperature gradient between jet and outer flow.

C4: Multi-field formulation for functionally graded high-temperature materials.

C5: Coupled simulations for the systematic design optimization of scramjets.

C6: Investigation of the thermal loads of a hypersonic propulsion system.

C7: Modeling of a scramjet propulsion system.


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Germany

Locations:

Stuttgart


Aachen

(Aix-la-Chapelle)

Köln

(Cologne)

München

(Munich)

Technische Universität München


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Speaker of the GRK 1095/2:

-Prof. Dr. B. Weigand, ITLR Stuttgart University

Project leaders:

- Stuttgart: E. Krämer, C.D. Munz, B. Kröplin, S. Staudacher, J. von Wolfersdorf,

M. Aigner, P. Gerlinger, B. Weigand

- Aachen/DLR Köln: H. Olivier, W. Schröder, A. Gülhan, M. Behr

- München: H.P. Kau, T. Sattelmayer, N. Adams

Scholars and Postdocs:

-Stuttgart (9): A.M. Schreyer, M. Banica, M. Staudenmaier, J. Vellaramkalayil, A. Hell,B. Rust, C. Messe, J. Groß, V. Shevchuk

- Aachen (4)/DLR Köln (2): O. Hohn, C. Fischer, T. Nguyen, J. Riehmer, M. Konapka,

F. Bramkamp

- München (3): D. Bruno, O. Petrache, S. Kirstein

And a lot of Associated members: U. Gaisbauer, B. Reinartz, G. Lamanna,

T. Scheuermann, T. Langener,…

Structure - Members


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combustion

aero-thermodynamic

investigations

A1, A2

A6 A4, A5

A3

A7, A8

supersonic

combustion

B1

B2 B3

B4

B5

B6B7

B8

nozzle flow and total system analysis

C1, C2, C3 C4, C5 C6, C7

Structure - interactions

very strong interaction within thedifferent sub-projects

≡

technical requirements of a

„scramjet“-propulsion system


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Standard Elements:

• Individual training program with specific courses

• Lectures by the involved scientists and guests

• Courses and lectures by international specialists

• Meetings and discussion forums

• Regular internal conferences

Special Features:• A stay abroard for all members for 6 months

• Self organised summer schools and workshops with

international specialists (by the PhD-students)

• Discussion forums with partners from industry• Integration of an external patent agent

Structure - Educational-program


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Educational-Program - Summer Schools


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1. Introduction


- Basic concept

- Structure of the GRK

- Educational-program

3. Selected results

- Project group A: “Aero-thermodynamical analysis”- Project group B: “Combustion”


4. Conclusion and outlook

Content

S l t d R lt


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static pressure field doubstatic pressure field double ramp configurationle ramp configuration

M=2.5, Re/m=9.82M=2.5, Re/m=9.82··101066

A2: A2: NumericalNumerical investigationsinvestigations of a doubleof a double rampramp configurationconfiguration withwith differentdifferent initialinitial

conditionsconditions

(Dr. Irina Fedorchenko, Institut f (Dr. Irina Fedorchenko, Institut f

üü

r Aerodynamik und Gasdynamik, Universitr Aerodynamik und Gasdynamik, Universit

ää

tt

Stuttgart,Stuttgart, Khristianovich Institute of Theoretical and Applied Mechanics SB RAS,

Novosibirsk, Russia))

Selected Results

M

Reattachment

waves

First kink

shock

Second

kink

shock

Slip

line

Joined

shock

S l t d R lt


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A7: Numerical investigation of the influence of laminar turbulent transition onhypersonic inlets (Martin Krause, Lehr- und Forschungsgebiet für Mechanik, RWTH

Aachen)

Selected Results

Cooperation shown as an example for the Project A7


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Cooperation shown as an example for the Project A7

A7

(Krause)

A3

(Häberle)

A5(Neuenhahn)

AX

(Bosco)

A2 und A8(PostDocs)

A6

(Lörcher)

C2

(Meiss)

C6

(Fuhrmann)

C7

(Schütte)

C4

(Leetsch)

B1(Scheuermann)

B4(Rust)

B8

(Maier)

B2

(Rosenko)

Selected Results


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B1: Experimental investigation of the design of a subersonic combustion chamber

(Tobias Scheuermann, Institut für Thermodynamik der Luft- und Raumfahrt, Universität

Stuttgart)

Selected Results

modified geometry of the

combustion chamber

Strong and weak combustion –normalized wall pressure

distribution for different equivalence ratios (Φ)

Selected Results


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Distribution of

hydrogen

2.5 cm 5 cm10 cm

20 cmXH2

Lobed strut injector

B5: Numerical investigation of the turbulent chemistry interaction

(B. Rust, Institut für Verbrennungstechnik der LRT, Universität Stuttgart)

Selected Results

Selected Results


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Selected Results

B6: Turbulence-Chemistry Interaction

(Henrik Förster, Lehrstuhl A für Thermodynamik, TU München)

Example of an in situ tabel for a 3Dthermodynamic state variable. Between

the cells, the results can be interpoated.

Ignition delay time for a Hydrogen-air mixture, directly calculated and interpolated

from 36 cells.

Selected Results


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C1: Experimental investigation of a scramjet nozzle (Christian Hirschen, DLR, Abteilung Windkanäle des Instituts für Aerodynamik und Strömungstechnik)

Selected Results

Schlieren picture with air (left) und argon (right) for p0,D = 3,2 bar

→ Influence of the ratio of the specific heats

Selected Results


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C2: Simulation of the interaction between nozzle flow and outside flow

(Jan Hendrik Meiß, Aerodynamisches Institut, RWTH Aachen)

SERN (grid)Single Expansion

Ramp Nozzle

Mach number distribution, M=7 (left), M=4 (right)

Selected Results

C6 & C7: GRK-Design Tools (T Fuhrmann G Schütte)


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C6 & C7: GRK Design Tools (T. Fuhrmann, G. Schütte)

31

~ E

Inlet-2D Euler

- Perfect gas

Combustor -1D Streamline

- Chemical kinetics

Nozzle-2D Euler

- Perfect gas

47

~ E

0

~ X

Inlet G

9

~ E

31 X 47 X 9 X

Combustor G

Combustor S ~ Nozzle

G

9

~ X

C6

C7

Cooperation shown as an example for the Projects C6 & C7


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B4

Düsendruckverhältnis Π, -

S c h u b b e i w e r t c f g , -

S c h u b v e k t o r w i n k e l β

f , °

200 400 600 800 10000.9

0.92

0.94

0.96

0.98

3.5

4

4.5

5

cfg,x

βf

Cooperation shown as an example for the Projects C6 & C7

C6 C7

A3

A7

B1B8

C1

C2

C4

A6

Summary


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• Research Training Group GRK 1095 – started April 2005

• Involved institutions: RWTH Aachen, DLR Köln, TU München and


• Comprehensive educational program

• Integration of international experts in scramjet technology / international

scientific exchange

• High level of integration and networking between all members and

institutions within Germany and with foreign partners

• First results demonstrate the efficiency of the philosophy

• Upgrading of the national know how and continuation of the long „scramjet

history“ in Germany

• Strict focus on hydrogen combustion with lobed strut injectors

Summary

Summary - Outlook


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• Aim for the first project stage (4.5 years): development of a successfull

design of a scramjet propulsion system with focus on a lobed strut injector

concept

• Verification of the functionality in tests associated project: wind tunnel test of a scramjet propulsion system (GA1332/1, financed by DFG)

⇒ Project GRK 1095/1 has been evaluated by DFG in 2009.

Because of the very good achievements, the project got elongated by

another 4,5 years, starting from 1.10.2009

Summary Outlook

Acknowledgement


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All members of the Graduate School GRK

1095 would like to thank the Deutsche

Forschungsgemeinschaft (DFG) for thesupport and the financing of the presented

scramjet research activities.

Acknowledgement

Grk Introduction

Documents

Transcript of Grk Introduction