Integrated welding connection thrust chamber structure

Abstract

The invention relates to an integrally welded thrust chamber structure, which is characterized in that the inner wall of a combustion chamber is welded with the inner wall of a spray pipe through electron beams, and the outer wall of the combustion chamber and the outer wall of the spray pipe are respectively welded with a connecting ring, so that the combustion chamber is welded with an extension section of the spray pipe; the flow equalizing effect is achieved through the middle annular cavity, the fuel collector is welded to the combustion chamber, and the fuel inlet flange serves as a fuel inlet and is welded to the fuel collector. A spray pipe inlet collector is omitted, the layout is compact, the structure is simple, and the overall weight of the thrust chamber is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace design and relates to a thrust chamber structure with integrated welding connection. Background Art

[0002] The thrust chamber is a device that converts energy into thrust in a liquid rocket engine and is one of the key components of a liquid rocket engine. The thrust chamber is mainly composed of a head, a combustion chamber, and a nozzle extension. The propellant is sprayed and atomized in the head, and burns in the combustion chamber to produce high-temperature and high-speed combustion gas. The combustion gas is accelerated by the contraction and expansion of the nozzle extension, converting the chemical energy of the propellant into gas kinetic energy, thereby generating huge thrust.

[0003] At present, the thrust chamber combustion chamber and nozzle extension section of the hydrogen-oxygen rocket engine are connected by flanges. Collectors and flanges are provided on the combustion chamber and the nozzle extension section. Not only are they heavy, but they also require separate pipelines to introduce the propellant into the collector, and the layout is relatively complicated.

[0004] Therefore, it is necessary to propose a thrust chamber solution with a simpler structure to simplify the layout and reduce weight. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose an integrated welded thrust chamber structure. Compared with the prior art, the combustion chamber and the nozzle extension section are welded and connected, the combustion chamber cooling channel and the nozzle cooling channel are directly connected, the structure is simple, the layout is compact, and the overall weight of the thrust chamber is reduced.

[0006] The solution of the present invention is:

[0007] An integrated welded thrust chamber structure comprises a head, a combustion chamber, a nozzle extension section, a fuel inlet flange, a nozzle outlet flange, a nozzle outlet pipeline, a head inlet flange, and a fuel collector;

[0008] The combustion chamber comprises an inner wall of the combustion chamber and an outer wall of the combustion chamber, wherein the inner wall of the combustion chamber is a milling groove structure with a combustion chamber cooling channel, and the nozzle extension section comprises an inner wall of the nozzle and an outer wall of the nozzle, wherein the inner wall of the nozzle is a milling groove structure with a nozzle cooling channel; a butt boss is extended from the inner wall of the combustion chamber and the inner wall of the nozzle at the butt joint, and the two butt bosses are connected by electron beam welding; the connecting ring is a T-shaped ring forging, and the outer wall of the combustion chamber and the outer wall of the nozzle are respectively connected to the connecting ring by electron beam welding; after the inner wall of the combustion chamber and the inner wall of the nozzle, the outer wall of the combustion chamber, the outer wall of the nozzle and the connecting ring are welded, an annular cavity is formed in the middle, and the annular cavity is used to evenly flow the fuel;

[0009] The head is welded to the combustion chamber; the tail of the nozzle extension section is connected to one end of the nozzle outlet pipeline through the nozzle outlet flange, and the other end of the nozzle outlet pipeline is connected to the head through the head inlet flange; the fuel collector is welded to the combustion chamber, and the fuel inlet flange serves as the fuel inlet and is welded to the fuel collector.

[0010] Preferably, the fuel collector is located close to the nozzle extension.

[0011] Preferably, the direction of the butt weld between the inner wall of the combustion chamber and the inner wall of the nozzle is perpendicular to the generatrix of the inner wall of the combustion chamber.

[0012] Preferably, the butt boss on the inner wall of the combustion chamber and the butt boss on the inner wall of the nozzle are designed to be thickened, with the thickness being 0.5 to 1 mm.

[0013] Preferably, a rounded corner is provided at the connection between the combustion chamber inner wall docking boss and the combustion chamber cooling channel.

[0014] Preferably, a rounded corner is provided at the connection between the nozzle inner wall docking boss and the nozzle cooling channel.

[0015] Preferably, the outer wall of the combustion chamber and the connecting ring are connected by electron beam welding as follows:

[0016] An outer wall locking bottom boss is processed at the joint between the outer wall of the combustion chamber and the connecting ring, and the bottom of the connecting ring is directly inserted into the outer wall locking bottom boss and then connected by electron beam welding.

[0017] Preferably, the inner wall of the combustion chamber is made of copper alloy material, and the outer wall of the combustion chamber is made of GH4169 or high-strength steel material.

[0018] Preferably, the inner wall of the nozzle and the outer wall of the nozzle are made of the same stainless steel material.

[0019] Preferably, when the thrust chamber is working, all the fuel enters the fuel collector from the fuel inlet flange, and then a part of the fuel flows upstream along the combustion chamber cooling channel to cool the combustion chamber, and the other part flows downstream after flowing evenly through the annular cavity, and cools the nozzle extension section along the nozzle cooling channel; the fuel for cooling the nozzle extension section passes through the nozzle outlet flange, along the nozzle outlet pipeline, enters the head inlet flange, and then enters the head fuel cavity to merge with the fuel for cooling the combustion chamber, and finally all of the fuel participates in the chemical reaction to generate thrust.

[0020] The beneficial effects of the present invention compared with the prior art are:

[0021] (1) The present invention designs an integrated welded thrust chamber structure, so that the combustion chamber and the nozzle extension section are connected by welding, which has a simple structure and can effectively reduce the weight of the thrust chamber;

[0022] (2) The boss at the joint between the inner wall of the combustion chamber and the inner wall of the nozzle extension section of the present invention is partially thickened to ensure the inner wall strength of the joint. At the same time, after welding, the inner wall of the combustion chamber and the inner wall of the nozzle directly and smoothly transition to avoid the ablation problem caused by the presence of steps;

[0023] (3) The combustion chamber cooling channel of the present invention is directly connected to the cooling channel of the nozzle extension section, and the inlet collector of the nozzle extension section is eliminated. The fuel enters the annular cavity formed by the connecting ring, which can further improve the flow uniformity, simplify the flow path, improve the compactness of the thrust chamber layout, simplify the structure, and reduce the overall weight of the thrust chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the overall structure and flow path;

[0025] Figure 2 A partial view of the welding connection between the combustion chamber and the nozzle. DETAILED DESCRIPTION

[0026] The present invention will be further described below in conjunction with the accompanying drawings.

[0027] The present invention provides a thrust chamber structure with integrated welding connection, such as Figure 1 As shown, the structure mainly includes a head 1, a combustion chamber 2, a nozzle extension section 3, a fuel inlet flange 4, a nozzle outlet flange 10, a nozzle outlet pipeline 20, and a head inlet flange 30.

[0028] The head 1 is welded to the combustion chamber 2, and the combustion chamber 2 is welded to the nozzle extension 3 through a connecting ring 48. The tail of the nozzle extension 3 is connected to one end of the nozzle outlet pipeline 20 through the nozzle outlet flange 10, and the other end of the nozzle outlet pipeline 20 is connected to the head 1 through the head inlet flange 30; the fuel collector 5 is welded to the combustion chamber 2, and the fuel inlet flange 4 is welded to the fuel collector 5 as a fuel inlet.

[0029] like Figure 2 The figure shows a partial view of the welding connection between the combustion chamber and the nozzle extension. The combustion chamber 2 is mainly composed of two parts: the combustion chamber inner wall 42 and the combustion chamber outer wall 41. The combustion chamber inner wall 42 is a milling groove structure with a combustion chamber cooling channel 50. The nozzle extension 3 is mainly composed of two parts: the nozzle inner wall 44 and the nozzle outer wall 45. The nozzle inner wall 44 is a milling groove structure with a nozzle cooling channel 51.

[0030] The combustion chamber inner wall 42 is usually made of copper alloy with good thermal conductivity, and the nozzle inner wall 44 is usually made of stainless steel. The combustion chamber inner wall 42 and the nozzle inner wall 44 extend a short section at the joint to form a combustion chamber inner wall butt boss 55 and a nozzle inner wall butt boss 56. The two bosses extend by a length of about 2 to 3 mm. Electron beam welding is usually used to form a butt weld 43 between the combustion chamber inner wall and the nozzle inner wall. The weld direction is perpendicular to the combustion chamber inner wall generatrix. In order to ensure the weld quality of the butt weld 43 between the combustion chamber inner wall and the nozzle inner wall, the combustion chamber inner wall butt boss 55 and the nozzle inner wall butt boss 56 are both thickened to a thickness of about 1.5 mm to 2 mm, and the thickening amount is about 0.5 to 1 mm. In order to reduce stress concentration, the combustion chamber inner wall butt boss 55 and the nozzle inner wall butt boss 56 are provided with fillets at the connection with the cooling channel, and the fillets are usually R1 to 2 mm.

[0031] The combustion chamber outer wall 41 is usually made of high-strength GH4169 or high-strength steel (S-06 or S-03), the nozzle outer wall 45 is usually made of the same stainless steel as the nozzle inner wall 44, and the connecting ring 48 is usually made of the same material as the combustion chamber outer wall 41, and the connecting ring 48 is a T-shaped ring forging. The combustion chamber outer wall 41 and the nozzle outer wall 45 are respectively connected by electron beam welding with the connecting ring 48 to form a butt weld 49 between the connecting ring and the combustion chamber outer wall and a butt weld 46 between the connecting ring and the nozzle outer wall. In order to ensure the effective connection strength of the weld between the combustion chamber outer wall 41 and the combustion chamber inner wall 42, the combustion chamber outer wall 42 retains a small section of the combustion chamber outer wall locking bottom boss 60 with a length of about 5 mm and a thickness of about 1 mm, and the bottom of the connecting ring 48 is directly inserted into the combustion chamber outer wall locking bottom boss 60.

[0032] After the combustion chamber inner wall 42 is welded with the nozzle inner wall 44, the combustion chamber outer wall 41, the nozzle outer wall 45 and the connecting ring 48, an annular cavity 47 is formed in the middle. In order to ensure the strength here, the axial length of the annular cavity 47 is controlled to be 4 to 6 mm. The downstream fuel enters the annular cavity 47 along the combustion chamber cooling channel 50, and after being evenly distributed here, it enters the nozzle cooling channel 51 and finally flows into the head fuel cavity.

[0033] When the thrust chamber is working, the fuel flow direction is as follows Figure 1 As shown by the middle arrow, all the fuel enters the fuel collector 5 from the fuel inlet flange 4, and then part of the fuel flows upstream along the combustion chamber cooling channel 50 to cool the combustion chamber 2, and the other part flows downstream along the nozzle cooling channel 51 to cool the nozzle extension 3. The fuel for cooling the nozzle extension 3 passes through the nozzle outlet flange 10, along the nozzle outlet pipeline 20, and enters the head inlet flange 30, and then enters the head fuel cavity to merge with the fuel for cooling the combustion chamber 2, and finally all participate in the chemical reaction to generate thrust.

[0034] The present invention designs an integrated welded thrust chamber structure, wherein the inner wall of the combustion chamber and the inner wall of the nozzle are connected by electron beam welding, and the outer wall of the combustion chamber and the outer wall of the nozzle are respectively welded to the connecting ring, thereby realizing the welding connection between the combustion chamber and the nozzle extension section, and the combustion chamber cooling channel is directly connected to the nozzle cooling channel through the middle annular cavity, thereby realizing the effect of equal flow, and at the same time eliminating the nozzle inlet collector, thereby having a compact layout, a simple structure, and reducing the overall weight of the thrust chamber.

[0035] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. An integrated welded thrust chamber structure, characterized in that: It includes a head, a combustion chamber, a nozzle extension section, a fuel inlet flange, a nozzle outlet flange, a nozzle outlet pipeline, a head inlet flange, and a fuel collector; The combustion chamber comprises an inner wall of the combustion chamber and an outer wall of the combustion chamber, wherein the inner wall of the combustion chamber is a milling groove structure with a combustion chamber cooling channel, and the nozzle extension section comprises an inner wall of the nozzle and an outer wall of the nozzle, wherein the inner wall of the nozzle is a milling groove structure with a nozzle cooling channel; a butt boss is extended from the inner wall of the combustion chamber and the inner wall of the nozzle at the butt joint, and the two butt bosses are connected by electron beam welding; the connecting ring is a T-shaped ring forging, and the outer wall of the combustion chamber and the outer wall of the nozzle are respectively connected to the connecting ring by electron beam welding; after the inner wall of the combustion chamber and the inner wall of the nozzle, the outer wall of the combustion chamber, the outer wall of the nozzle and the connecting ring are welded, an annular cavity is formed in the middle, and the annular cavity is used to evenly flow the fuel; The head is welded to the combustion chamber; the tail of the nozzle extension section is connected to one end of the nozzle outlet pipeline through the nozzle outlet flange, and the other end of the nozzle outlet pipeline is connected to the head through the head inlet flange; the fuel collector is welded to the combustion chamber, and the fuel inlet flange serves as the fuel inlet and is welded to the fuel collector.

2. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: The fuel collector is located close to the nozzle extension.

3. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: The direction of the butt weld between the inner wall of the combustion chamber and the inner wall of the nozzle is perpendicular to the generatrix of the inner wall of the combustion chamber.

4. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: The butt boss on the inner wall of the combustion chamber and the butt boss on the inner wall of the nozzle are designed to be thickened, with the thickness being 0.5 to 1 mm.

5. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: A rounded corner is arranged at the connection between the combustion chamber inner wall docking boss and the combustion chamber cooling channel.

6. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: A rounded corner is arranged at the connection between the nozzle inner wall butt boss and the nozzle cooling channel.

7. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: The outer wall of the combustion chamber and the connecting ring are connected by electron beam welding as follows: An outer wall locking bottom boss is processed at the joint between the outer wall of the combustion chamber and the connecting ring, and the bottom of the connecting ring is directly inserted into the outer wall locking bottom boss and then connected by electron beam welding.

8. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: The inner wall of the combustion chamber is made of copper alloy, and the outer wall of the combustion chamber is made of GH4169 or high-strength steel.

9. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: The inner wall of the nozzle and the outer wall of the nozzle are made of the same stainless steel material.

10. The thrust chamber structure with integrated welding connection according to claim 1, characterized in that: When the thrust chamber is working, all the fuel enters the fuel collector from the fuel inlet flange, and then a part of the fuel flows upstream along the combustion chamber cooling channel to cool the combustion chamber, and the other part flows downstream after flowing through the annular cavity, and cools the nozzle extension section along the nozzle cooling channel; the fuel for cooling the nozzle extension section passes through the nozzle outlet flange, along the nozzle outlet pipeline, into the head inlet flange, and then enters the head fuel cavity to merge with the fuel cooling the combustion chamber, and finally all of them participate in the chemical reaction to generate thrust.

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