US 12,281,627 B2
Rocket engine systems with a supercritical coolant
Andrew Thomas Duggleby, Friendswood, TX (US)
Assigned to Venus Aerospace Corp., Houston, TX (US)
Filed by Venus Aerospace Corp., Houston, TX (US)
Filed on Jan. 6, 2023, as Appl. No. 18/151,385.
Application 18/151,385 is a continuation in part of application No. 17/561,621, filed on Dec. 23, 2021.
Claims priority of provisional application 63/130,586, filed on Dec. 24, 2020.
Prior Publication US 2024/0093662 A1, Mar. 21, 2024
Int. Cl. F02K 9/00 (2006.01); F02K 9/64 (2006.01)
CPC F02K 9/00 (2013.01) [F02K 9/64 (2013.01)] 26 Claims
OG exemplary drawing
 
1. A rocket engine system comprising:
a thrust chamber including walls that define an interior surface and a combustion section which is fluidically coupled to an output section;
a coolant source containing a coolant;
a heat exchanger configured to:
receive a first flow of said coolant at a first temperature at a first heat exchanger inlet;
direct said first flow of said coolant through a first coolant outlet line to said thrust chamber;
receive a second flow of said coolant at a second temperature returned from said thrust chamber via a second heat exchanger inlet;
exchange heat between said second flow of said coolant at said second temperature and said first flow of said coolant at said first temperature; and
direct said second flow of said coolant through a second coolant outlet line to at least one port connected to said interior surface of said thrust chamber;
wherein said heat exchanger is disposed at a distance from the thrust chamber, said heat exchanger being connected to said thrust chamber by said first coolant outlet line and said second coolant outlet line;
wherein said at least one port is configured to apply said coolant to said interior surface to achieve a film cooling of said interior surface.
 
16. A rocket engine system comprising:
a thrust chamber including walls that define an interior surface and a combustion section which is fluidically coupled to an output section;
a coolant source containing water;
a heat exchanger configured to:
receive a first flow of said water at a first temperature at a first heat exchanger inlet;
direct said first flow of said water through a first coolant outlet line to said thrust chamber;
receive a second flow of said water at a second temperature returned from said thrust chamber via a second heat exchanger inlet;
exchange heat between said second flow of said water at said second temperature and said first flow of said water at said first temperature; and
direct said second flow of said water through a second coolant outlet line to at least one port connected to said interior surface of said thrust chamber;
wherein said heat exchanger is disposed at a distance from the thrust chamber, said heat exchanger being connected to said thrust chamber by said first coolant outlet line and said second coolant outlet line;
wherein said at least one port is configured to apply said water to said interior surface to achieve a film cooling of said interior surface.