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A "Hypergolic, Full Flow, and Closed Catalyst" cycle rocket engine

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  • Left side:
  1. All hydrazine goes through the centrifugal fuel pump
  2. All hydrazine undergoes thermal decomposition
  3. Out of it comes hot hydrogen gas and hot nitrogen gas
  4. All hot hydrogen gas and hot nitrogen gas goes through the centrifugal fuel turbine
  5. All hot hydrogen gas and hot nitrogen gas goes out the centrifugal fuel turbine and into the combustion chamber
  • Right side:
  1. All nitrogen tetroxide goes through the centrifugal oxidizer pump
  2. All nitrogen tetroxide undergoes thermal decomposition
  3. Out of it comes hot oxygen gas and hot nitrogen gas
  4. All hot oxygen gas and hot nitrogen gas goes through the centrifugal oxidizer turbine
  5. All hot oxygen gas and hot nitrogen gas goes out the centrifugal oxydizer turbine and into the combustion chamber
  • Center:
  1. When the hot hydrogen and hot oxygen meet, they ignite

Similar engines:

  • Proton's engine was a hypergolic and oxydizer rich closed cycle engine.

  • The RD-270 was a hypergolic full flow staged combustion engine.

I do not remember having seen anything exactly like my proposal.

Are there any references on this design or other similar designs?

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