Knowledge for Tomorrow CMC Rocket Thrust Chamber Technology Status and Perspectives M. Ortelt, H. Hald, D. Koch [email protected]German Aerospace Center (DLR) Institute of Structures and Design AIRBUS DS – Space Systems - 6 th R&T DAYS, Paris, 19.11.2015, Session 3, WG2 Technologies for Future Liquid Propulsion DLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 1
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Knowledge for Tomorrow
CMC Rocket Thrust Chamber TechnologyStatus and Perspectives
- Decoupling of single components – no bonding- Decoupling of mechanical and thermal loads- Specific hybrid interface technologies- Selective inner liner design
Features
DLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 3
- Standard CFD systems (FLUENT, CFX, …) are constructive (pure flow coupling)- Ongoing tool-development for ‚structure-flow-coupling‘ (TAU)- Investigations on materials out-flow homogeneity
Functional aspectsDLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 4
System analysis of transpiration cooling
0%
2%
4%
6%
8%
10%
12%
1 10 100 1000 10000 100000
Coolan
t ratio [‐]
Vacuum thrust [kN]
Tw = 800 K dc = 50 mm
dc = 100 mm
dc = 200 mm
dc = 440 mm
dc = 1000 mm
0%
2%
4%
6%
8%
10%
12%
1 10 100 1000 10000 100000
Coolan
t ratio [‐]
Vacuum thrust [kN]
Tw = 1200 K dc = 50 mm
dc = 100 mm
dc = 200 mm
dc = 440 mm
dc = 1000 mm
- Comparison of chamber size (scaling)- 50 mm chamber demonstration
- O/F = 5.5 (injector)- Contraction ratio 6.25- Characteristic chamber length l*=1.84 m- 7 % coolant ratio- Damage free operation- Amount of coolant depends on
- Hotgas conditions, As, T- D + p required coolant ratio
- Further coolant ratio reduction potential- Chamber length can be shortened
High operational efficiency predicted
DLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 5
DLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 6
Processing of Ceramic Matrix Composites (DLR-ST, BT)
• Autoclave30 bar, 350 °C
• Warm Press 350°C
• RTM 300°C• Pyrolysis, LSI, 2000°C• Machining Center
DLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 7
Thrust chamber – potential CMC derivativesInitial C/C model material LOX-sensitive!Other derivatives damage free after efficiently cooled and non-cooled operation:
Oxipol AvA-Z-ISC C/SiCN C/C (CVI)
10 35 18 7
2.3 2.6 1.6 1.6
Density kg/cm3
Open porosity [%] (porosity + permeability kd / kf adaptable by manufacturing process)
DLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 8
CMC thrust chamber – Components
Co-axial injector
Applied injectorsystems forcyl. 50 mm
Porous metal injector
Porous CMC injector
Elements of
oxide
CMC
for
the
LOX
injectionIntegrated ‚BlackEngine‘ demonstrator, cyl. 50 mm
C/C-SiC face-plate
Inner liner segment
DLR-ST-IBT > M. Ortelt / H. Hald / D. Koch > Presentation > AIRBUS DS – Space Systems - 6th R&T DAYS > Paris > France, 19.11.2015 • Chart 9