阅读说明：本技术 一种推力室及火箭发动机 (Thrust chamber and rocket engine ) 是由 彭小波 张玺 刘岳曦 高翔宇 鲍启林 于 2020-08-13 设计创作，主要内容包括：本发明涉及航空航天技术领域,具体涉及一种推力室及火箭发动机。推力室,包括：推力室头部；推力室身部,包括推力室内壁、与推力室内壁间隔设置的推力室外壁、冷却通道及处于推力室内壁内的燃烧腔；喷注器,设于推力室头部靠近推力室身部的一端,包括喷注器本体,及设于喷注器本体上、相互独立设置的燃料喷注结构和氧化剂喷注结构,燃料喷注结构包括靠近推力室内壁设置的边缘喷注结构及沿燃烧腔的延伸方向设置的中部喷注结构,氧化剂喷注结构与中部喷注结构相邻设置。由于靠近推力室内壁设置的边缘喷注结构向靠近推力室内壁处喷注燃料,而无氧化剂喷注,能够在靠近推力室内壁处形成低温保护层,防止高温燃气直接作用于推力室内壁,降低损坏。(The invention relates to the technical field of aerospace, in particular to a thrust chamber and a rocket engine. A thrust chamber, comprising: a thrust chamber head; the thrust chamber body comprises a thrust chamber inner wall, a thrust chamber outer wall, a cooling channel and a combustion chamber, wherein the thrust chamber outer wall and the thrust chamber inner wall are arranged at intervals; the injector is arranged at one end, close to the body part of the thrust chamber, of the head part of the thrust chamber, and comprises an injector body, a fuel injection structure and an oxidant injection structure, wherein the fuel injection structure and the oxidant injection structure are arranged on the injector body and are mutually independent, the fuel injection structure comprises an edge injection structure and a middle injection structure, the edge injection structure is arranged close to the inner wall of the thrust chamber, the middle injection structure is arranged along the extending direction of the combustion chamber, and the oxidant injection structure and the middle injection structure are arranged adjacently. Because the fuel is spouted to the edge spouting structure that is close to thrust chamber inner wall setting to being close to thrust chamber inner wall department, and do not have the oxidant to spout, can form the low temperature protective layer near thrust chamber inner wall department, prevent that high temperature gas direct action from reducing the damage in the thrust chamber inner wall.)

1. A thrust chamber, comprising:

a thrust chamber head (1);

the thrust chamber body is connected below the thrust chamber head (1) and comprises a thrust chamber inner wall (3), a thrust chamber outer wall (2) arranged at an interval with the thrust chamber inner wall (3), a cooling channel positioned between the thrust chamber inner wall (3) and the thrust chamber outer wall (2) and a combustion chamber (5) positioned in the thrust chamber inner wall (3), and the cooling channel is filled with a cooling medium;

the injector is arranged at one end, close to the body part of the thrust chamber, of the head part (1) of the thrust chamber and comprises an injector body, and a fuel injection structure and an oxidant injection structure which are arranged on the injector body and are mutually independent, the fuel injection structure and the oxidant injection structure are both communicated with the combustion chamber (5), the fuel injection structure comprises an edge injection structure and a middle injection structure, the edge injection structure is arranged close to the inner wall (3) of the thrust chamber, the middle injection structure is arranged along the extending direction of the combustion chamber (5), and the oxidant injection structure and the middle injection structure are arranged adjacently.

2. The thrust chamber according to claim 1, characterized in that said edge injection structure is arranged towards said thrust chamber inner wall (3).

3. The thrust chamber of claim 1, wherein said fuel injection structure comprises:

a fuel flow path provided on the body;

one end of the fuel nozzle is communicated with the fuel flow path, the other end of the fuel nozzle is communicated with the combustion cavity (5), and the fuel nozzle comprises an edge nozzle (6) which is arranged close to the inner wall (3) of the thrust chamber and a middle nozzle which is arranged along the extending direction of the combustion cavity (5);

and/or, the oxidant injection structure comprises:

an oxidizer flow path provided in the body;

and one end of the oxidant nozzle is communicated with the oxidant flow path, the other end of the oxidant nozzle is communicated with the combustion chamber (5), and the oxidant nozzle is arranged adjacent to the middle jetting structure.

4. The thrust chamber of claim 3, wherein the fuel flow path comprises:

a first main flow path (7) adapted at one end to be connected to a fuel source;

a plurality of first branch flow paths (9) having one ends connected to the first main flow path (7) and the other ends connected to the fuel nozzles;

and/or, the oxidant flow path comprises:

a second primary flowpath (8) adapted at one end for connection to the source of oxidant;

and a plurality of second branch channels (10) having one end connected to the second main channel (8) and the other end connected to the oxidizer nozzle.

5. The thrust chamber according to claim 4, characterized in that, as a section taken perpendicular to the height of said thrust chamber head (1), the orifice diameter of said oxidant nozzle arranged near the edge of the section is smaller than the orifice diameter of said oxidant nozzle arranged in the middle of the section.

6. The thrust chamber of any of claims 1-5, wherein said cooling medium is a low temperature supercritical fluid.

7. The thrust chamber of claim 6, wherein said cooling medium is supercritical liquid methane.

8. The thrust chamber according to any one of claims 1 to 5, characterized in that said thrust chamber head (1), said thrust chamber body and said injector are integrally formed.

9. The thrust chamber according to claim 8, characterized in that said thrust chamber head (1), said thrust chamber body and said injector are integrally formed by an additive manufacturing process.

10. A rocket engine comprising a thrust chamber as defined in any one of claims 1 to 9.