US 2023/0407820 A1 · COMBUSTOR INCLUDING HEAT EXCHANGE STRUCTURE AND ROCKET COMPRISING SAME

Abstract

The disclosure relates to a combustor including a heat exchange structure and a rocket including the combustor. The combustor according to an embodiment of the disclosure includes: an inner wall; an outer jacket arranged to cover an outer surface of the inner wall; a plurality of first heat exchange channels arranged between the inner wall and the outer jacket and through which a fuel introduced from a fuel tank flows; and a second heat exchange channel arranged between the inner wall and the outer jacket and through which a pressurized gas introduced from a pressurized gas tank flows.

Claims22

Dependent claims

A combustor comprising:

an inner wall;
an outer jacket arranged to cover an outer surface of the inner wall;
a plurality of first heat exchange channels arranged between the inner wall and the outer jacket and through which a fuel introduced from a fuel tank flows;
and
a second heat exchange channel arranged between the inner wall and the outer jacket and through which a pressurized gas introduced from a pressurized gas tank flows.

2 more elements

A rocket comprising an oxidant tank storing an oxidant, a fuel tank storing a fuel, a pressurized gas tank arranged in at least one of the oxidant tank and the fuel tank and storing a pressurized gas, and a combustor,

wherein the combustor comprises:
an inner wall;
an outer jacket arranged to cover an outer surface of the inner wall;
a plurality of first heat exchange channels arranged between the inner wall and the outer jacket, through which the fuel introduced from the fuel tank flows, and through which the fuel exchanging heat with the combustor is discharged to the fuel tank;
and
a second heat exchange channel arranged between the inner wall and the outer jacket, through which the pressurized gas introduced from the pressurized gas tank flows, and through which the pressurized gas exchanging heat with the combustor is discharged to the pressurized gas tank.

3 more elements

Dependencies are inferred from the claim text.

Facts

Application

18/251,617Filed 4 Nov 2021

Priority

KR 10-2020-015454618 Nov 2020

Published

21 Dec 2023

Term ends

Not estimatedThe source records don’t support an estimate.

Classification7 codes

F02K 9/62
Constructional parts; Details not otherwise provided for: combustion or thrust chambers
F02K 9/44
Using liquid or gaseous propellants: feeding propellants
F02K 9/64
Combustion or thrust chambers: having cooling arrangements
F02K 9/972
Rocket nozzles: fluid cooling arrangements for nozzles

Combustor including heat exchange structure and rocket comprising same

Life of this patent

Combustor including heat exchange structure and rocket comprising same

Life of this patent

Abstract

Claims22