Next figure shows the engine assemblage. The assemblage is made all with standard steel bolts. The engine has been calculated using MATLAB and ANSYS V13 softwares. All parts of this engine have been designed using SOLIDWORK 2012 software.
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| View of the A-1 engine. |
The choise of the material for the inner chamber wall in the thrust chamber, which is the critical location, is influenced by the hot gases resulting from burning of propellants, the maximum wall temperature, the heat transfer, and the duty cycle. A large variety of material has been used, the below table shows several copper alloys used. For high-performance, high heat transfer, regeneratively cooled thrust chambers a copper alloy with high thermal conductivity and a thin-wall design will reduce the thermal stresses. Copper is an excellent heat conductor and it will not really oxideze in fuel-rich noncorrosive gas mixture. The inner walls of A-1 engine are made of a copper alloy with small additions of Zirconium, it is called CW120C (150HB).
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| 3D view of the thrust chamber design. |
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| Table of composition of copper alloys in weight percent. |
NASA used this CuZr H150 copper alloy. This alloy called AMZIRC has the next specs:
Material designation : CuZr, CW120C (EN), C15000 (ASTM/ASME), DIN-2.1580 and C15000.
Composition : 99,85% copper and 0,15% Zr.
Hardness : 150 HB
Density : 8.900 kg/m3
Tensile strength : 400 Mpa (Estimated)0,2% proof strength : 350 Mpa (Estimated)
Elongation : 15% (Estimated)
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| Table of ultimate tensile stress of several copper alloys. |
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| Table of yield tensile stress of several copper alloys. |
Design of a regeneratively cooled thrust chamber involves consideration of gas-side heat fkux, wall structure requirenebts, coolant-side heat transfer, the effects of temperature increases on coolant propierties, manufacturing specifications and manufacturing limitations. Heat transfer in a regenerative cooled chamber can be described as the heat flow between two moving fluids, through a multilayer partition. Below figure shows this process schematically.
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| Typical temperature gradients in regenerative cooled thrust chamber of a liquid propellant engine. |
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| 3D view of the oouter jacket design. |
Injector plate
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| 3D view of the injector plate design. |
Cooling plate
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| 3D view of the cooling plate design, Kerosene side. |
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| 3D view of the cooling plate design , Oxygen side. |
Oxygen dome
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| 3D view of the Oxygen dome design. |
Thoat closeout
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| 3D view of the thoat closeout design. |
Nozzle
