Solid rocket engine combustion chamber and spray pipe sealing structure

Abstract

The utility model discloses a solid rocket engine combustion chamber and spray pipe sealing structure which comprises a combustion chamber and a spray pipe. A single-layer metal layer connecting section is arranged on the outermost side of an opening of the combustion chamber connecting end, connecting threads are machined on the inner wall of the combustion chamber metal layer connecting section, and a step-shaped butt joint groove is formed in a non-metal layer on the inner side of the combustion chamber metal layer connecting section. The outermost end of an opening of the spray pipe connecting end is a non-metal layer connecting section provided with a stepped butt joint groove, and connecting threads are machined on the outer wall of a metal layer on the inner side of the non-metal layer connecting section of the spray pipe. The metal layer connecting section of the combustion chamber is in threaded connection with the metal layer on the inner side of the non-metal layer connecting section of the spray pipe, and the non-metal layer on the inner side of the metal layer connecting section of the combustion chamber is fixedly bonded with the non-metal layer connecting section of the spray pipe through a stepped butt joint groove. According to the combustion chamber and spray pipe sealing structure, the safety and reliability of a solid rocket engine in the storage, transportation and working processes are improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to a solid rocket engine combustion chamber and nozzle sealing structure belongs to solid rocket engine sealing technical field. BACKGROUND

[0002] In order to prevent the high temperature and high pressure gas in the shell from leaking out when the solid rocket engine works, and to ensure the moisture resistance and corrosion resistance of the shell during storage and transportation, good sealing should be provided at each connecting part. Otherwise, during engine operation, the leaked gas will not only damage the interior ballistic performance of the engine, but also burn through the connecting part of the shell, causing greater accidents. At low temperatures, the moisture from the outside will form a layer of frost on the surface of the propellant, making ignition difficult; in high altitude, the pressure in the shell will be as low as the outside, also causing ignition difficulty; and during storage and transportation, the propellant is prone to moisture and deterioration. The connecting part of the solid rocket engine combustion chamber and nozzle is usually sealed by a mating surface, which can be a metal mating surface or a non-metal mating surface. The metal mating surface is sealed by an O-shaped sealing ring, and the non-metal mating surface is sealed by applying sealing glue and curing the sealing glue.

[0003] Non-metal materials generally shrink after forming, and the gap between the non-metal mating surfaces can be filled and sealed by applying sealing glue, and the sealing effect is achieved after the sealing glue is cured. However, with the generalization of high-pressure and high-gas-generation engines, the sealing effect of the existing structure is poor. UTILITY MODEL CONTENTS

[0004] The utility model aims at solving the problem of poor sealing effect of the connecting part of the existing solid rocket engine combustion chamber and nozzle, and provides a solid rocket engine combustion chamber and nozzle sealing structure.

[0005] The utility model aims at solving the problem of poor sealing effect of the connecting part of the existing solid rocket engine combustion chamber and nozzle, and provides a solid rocket engine combustion chamber and nozzle sealing structure.

[0006] The utility model relates to a solid rocket engine combustion chamber and nozzle sealing structure, which comprises a combustion chamber with an inner non-metal layer and an outer metal layer, and a nozzle with an inner non-metal layer and an outer metal layer.

[0007] The outermost part of the port of the combustion chamber connecting end is a single-layer metal layer connecting section, the inner wall of the combustion chamber metal layer connecting section is processed with connecting threads, and the non-metal layer on the inner side of the combustion chamber metal layer connecting section is provided with a stepped butt joint groove;

[0008] The outermost end of the port of the nozzle connecting end is a non-metal layer connecting section with a stepped butt joint groove, and the outer wall of the metal layer on the inner side of the nozzle non-metal layer connecting section is processed with connecting threads.

[0009] The metal layer connecting section of the combustion chamber is threadedly connected with the metal layer inside the non-metal layer connecting section of the nozzle, and the non-metal layer inside the metal layer connecting section of the combustion chamber is cemented with the non-metal layer connecting section of the nozzle through the stepped butt joint groove.

[0010] The metal layer connecting section of the combustion chamber is threadedly connected with the metal layer inside the non-metal layer connecting section of the nozzle, and the non-metal layer inside the metal layer connecting section of the combustion chamber is cemented with the non-metal layer connecting section of the nozzle through the stepped butt joint groove.

[0011] Beneficial effects

[0012] The combustion chamber and nozzle sealing structure of the utility model is simple to make, convenient to assemble and disassemble, adopts the sealing structure of the stepped butt joint surface, increases the contact area of the non-metal matching surface, thereby increasing the sealing reliability, can isolate the solid rocket engine external cold and hot gas and the combustion gas in the engine working process, and improves the safety and reliability of the solid rocket engine in the storage, transportation and working process. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 It is the butt joint schematic view of the utility model combustion chamber and nozzle sealing structure.

[0014] In the figure, 1 is a combustion chamber, and 2 is a nozzle. DETAILED DESCRIPTION

[0015] The contents of the utility model will be further described below in combination with the drawings and embodiments.

[0016] EMBODIMENT

[0017] As Figure 1 shown, the utility model relates to a solid rocket engine combustion chamber and nozzle sealing structure, which comprises a combustion chamber 1 with an inner non-metal layer and an outer metal layer and a nozzle 2 with an inner non-metal layer and an outer metal layer.

[0018] The outermost part of the mouth of the connecting end of the combustion chamber 1 is a single-layer metal layer connecting section, the inner wall of the metal layer connecting section of the combustion chamber 1 is provided with connecting threads, and the non-metal layer inside the metal layer connecting section of the combustion chamber is provided with a stepped butt joint groove.

[0019] The outermost end of the mouth of the connecting end of the nozzle 2 is a non-metal layer connecting section provided with a stepped butt joint groove, and the outer wall of the metal layer inside the non-metal layer connecting section of the nozzle 2 is provided with connecting threads.

[0020] The metal layer connecting section of the combustion chamber 1 is threadedly connected with the metal layer inside the non-metal layer connecting section of the nozzle 2, and the non-metal layer inside the metal layer connecting section of the combustion chamber is cemented with the non-metal layer connecting section of the nozzle through the stepped butt joint groove.

[0021] The metal layer connecting section of the combustion chamber is connected with the metal layer inside the non-metal layer connecting section of the nozzle through a slotted connecting sealing ring.

Claims

1. A solid rocket engine combustion chamber and nozzle sealing structure, comprising a combustion chamber with an inner nonmetallic layer and an outer metallic layer, and a nozzle with an inner nonmetallic layer and an outer metallic layer; the mouth of the combustion chamber connecting end is a single-layer metallic layer connecting section, the inner wall of the combustion chamber metallic layer connecting section is provided with connecting threads, and the nonmetallic layer on the inner side of the combustion chamber metallic layer connecting section is provided with a stepped butt joint groove; the mouth of the nozzle connecting end is a nonmetallic layer connecting section provided with a stepped butt joint groove, and the outer wall of the metallic layer on the inner side of the nozzle nonmetallic layer connecting section is provided with connecting threads; the metallic layer connecting section of the combustion chamber is threadedly connected with the metallic layer on the inner side of the nozzle nonmetallic layer connecting section, and the nonmetallic layer on the inner side of the combustion chamber metallic layer connecting section is cemented with the nonmetallic layer connecting section of the nozzle through the stepped butt joint groove. The application is characterized in that A groove connecting sealing ring is arranged between the metallic layer connecting section of the combustion chamber and the metallic layer on the inner side of the nozzle nonmetallic layer connecting section. ​ ​ 2. A seal structure for a solid rocket engine combustion chamber and nozzle as recited in claim 1, characterized by: ​

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