NozzleAblative Typeby Various

Typical Specifications

Erosion Rate
0.1u20130.5 mm/s at throat
Char Temperature
~2,500u00b0C
Material Density
1.4u20131.9 g/cmu00b3 (composites)

Operating Principle

Heat from combustion gases causes the inner surface of the nozzle to decompose through pyrolysis, creating a cool gas boundary layer and char layer that insulate the structural wall. Material is consumed progressively during the burn.

An ablative nozzle uses a sacrificial liner material that absorbs heat by charring, melting, and vaporizing during engine operation. The ablation process carries heat away from the structural wall, providing thermal protection without active cooling. Ablative nozzles are simpler and lighter than regeneratively cooled designs but are single-use. They are common in solid rocket motors and some low-cost liquid engines.

Materials

Carbon-phenolicSilica-phenolicCarbon-carbonGraphiteEPDM rubber (insulation)

Used In Engines

Common Failure Modes

Excessive erosion (throat area increase reduces performance), uneven ablation, structural failure of char layer, delamination

Recent Innovations

Carbon-phenolic composites for high erosion resistance, silica-phenolic for lower-heat areas, 3D-woven carbon-carbon preforms

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