阅读说明：本技术 固体火箭发动机喷管与燃烧室的连接套筒 (Connecting sleeve for solid rocket engine jet pipe and combustion chamber ) 是由 吴喆昊 张斐 刘元敏 王峰 郭峰 袁新钊 于 2020-12-20 设计创作，主要内容包括：一种固体火箭发动机喷管与燃烧室的连接套筒,是由两个结构相同的半卡环对合而成的圆环。各半卡环的内圆周表面有与所述喷管壳体外圆周表面凸台嵌合的卡槽,通过该卡槽将该半卡环卡装在燃烧室壳体端面外圆周表面与喷管壳体端面的外圆周表面上,从而实现所述燃烧室壳体与喷管壳体的快速连接。本发明对发动机燃烧室与喷管的连接部位进行了改进,并通过密封环实现连接部位的密封。本发明通过对发动机喷管与燃烧室连接结构形式进行改进,实现了发动机总装工艺难度的降低,实现了喷管与燃烧室的快速连接,降低了发动机生产和装配成本。(A connecting sleeve for a solid rocket engine nozzle and a combustion chamber is a circular ring formed by folding two semi-snap rings with the same structure. The inner circumferential surface of each half snap ring is provided with a clamping groove which is embedded with a boss on the outer circumferential surface of the spray pipe shell, and the half snap rings are clamped on the outer circumferential surface of the end surface of the combustion chamber shell and the outer circumferential surface of the end surface of the spray pipe shell through the clamping grooves, so that the combustion chamber shell and the spray pipe shell are quickly connected. The invention improves the connection part of the engine combustion chamber and the spray pipe, and realizes the sealing of the connection part through the sealing ring. According to the invention, the connecting structure form of the engine spray pipe and the combustion chamber is improved, so that the difficulty of the engine assembly process is reduced, the spray pipe and the combustion chamber are quickly connected, and the production and assembly cost of the engine is reduced.)

1. A connecting sleeve for a solid rocket engine nozzle and a combustion chamber is characterized in that a connecting piece is a circular ring formed by folding two semi-snap rings with the same structure; the inner circumferential surface of each semi-snap ring is provided with a clamping groove which is embedded with a boss on the outer circumferential surface of the spray pipe shell, and the semi-snap rings are clamped on the outer circumferential surface of the end surface of the combustion chamber shell and the outer circumferential surface of the end surface of the spray pipe shell through the clamping grooves, so that the combustion chamber shell and the spray pipe shell are quickly connected.

2. A solid rocket engine nozzle-to-combustor adapter sleeve as recited in claim 1, wherein said adapter has an inside diameter equal to an outside diameter of said annular projection on said outer circumferential surface of said nozzle housing; the outer diameter of the connecting piece is the same as that of the spray pipe shell; the width a of draw-in groove is 8mm, and degree of depth h is 8 mm.

3. A solid rocket engine nozzle-to-combustor adapter sleeve as claimed in claim 1 wherein the outer circumferential surface of the nozzle housing attachment end is formed with a groove, and the height of the groove wall on one side of the nozzle housing adjacent to the combustor housing is less than the height of the groove wall on the other side; the inner surface of the groove forms a side wall matching surface of the semi-clamping ring groove; the width of the groove wall close to one side of the combustion chamber shellThe surface of the groove wall forms a semi-snap ring groove matching surface; the end face of the connecting end of the spray pipe shell is provided with an axial annular bump which is a butt-joint limiting ring of the spray pipe shell; and two screw holes are symmetrically processed on the other end surface of the connecting end of the spray pipe shell, and the two screw holes are respectively corresponding to the screw holes on one semi-clamping ring.

4. A solid rocket engine nozzle-combustor adapter sleeve as claimed in claim 1, wherein a groove is formed between the outer circumferential surfaces of the connection ends of the combustor housing, and the height of the groove wall on one side of the nozzle housing adjacent to the groove is smaller than the height of the groove wall on the other side of the nozzle housing; the inner surface of the groove forms a matching surface of the combustion chamber shell and the semi-clamping ring groove; the width of the groove wall close to one side of the spray pipe shellThe surface of the groove wall forms a matching surface of the semi-snap ring groove.

5. The solid rocket engine nozzle-combustor adapter sleeve of claim 4 wherein said combustor housing attachment end is machined with three steps, the first step surface being the mounting mating surface of said nozzle housing for abutting a retainer ring, and the third step surface being the mating surface of said nozzle housing attachment end face; and a gap formed by the step difference of the second-stage step is a mounting groove of the sealing ring 4.

Technical Field

The invention relates to the technical field of solid rocket engines, in particular to a connecting piece of a solid rocket engine jet pipe and a combustion chamber, which can improve the working reliability of an engine.

Background

The connection between the engine combustion chamber and the nozzle tube is subjected to various external and internal loads during engine production and operation. In order to ensure the designed working state of the engine, the selection of the strength and the safety margin of the connection mode and the structure is particularly important and is an important component in the design process of the engine. The convenience of the connecting structure directly influences the operability and precision of the whole engine assembly; the reliability of the connecting structure directly influences the reliability and safety of the working process of the engine.

The design of the connection of the nozzle to the combustion chamber usually uses a threaded connection and a flanged connection, depending on the design requirements and constraints given by the cartridge and engine as a whole.

The design of the threaded connection comprises a sealing design, a thread large diameter design, a thread pitch design, a threaded connection effective length, a thread form angle design and the like; these parameters are typically appropriately designed with respect to the determination of the overall operating pressure and operating time of the engine. When the threaded connection is stressed axially, the strength safety margin is generally higher, but under the action of various loads on the whole engine, when the threaded connection is stressed transversely and greatly, the threaded connection is easy to fail. When the requirement for detecting the circular runout of the engine is high, the requirement for the machining precision of the threads is extremely high, and low-cost batch production is not facilitated.

The design of the flange connection comprises a flange plate design, a connecting bolt design and a related sealing design. The flange connection has a high connection reliability but a high negative quality. In the process of engine assembly, the number of the matched parts which are connected relatively is large, the types are various and trivial, the installation process is complex, and more difficulties are increased for the assembly process.

Through search, the invention creation with the special application number of 201420374761.9 discloses a clasp connecting structure of a solid rocket engine. The invention provides a snap ring connecting structure, which is convenient to assemble, disassemble and maintain for a connecting structure with a narrow assembling space, but has the problems of higher processing cost, more assembling parts and complex preparation of a matching part.

In the invention and creation of the patent application No. 201610132836.6, a pin connecting structure of a metal shell of a solid rocket engine is disclosed. The pin connecting structure is provided, the assembly and disassembly are simple, the structural reliability is high, but the requirements on the processing precision of related parts are high, and the requirements on the strength of the pin are high.

Disclosure of Invention

In order to overcome the defects of high cost, complex connecting and assembling parts and larger thrust deflection numerical value in the prior art, the invention provides a connecting sleeve for a solid rocket engine spray pipe and a combustion chamber.

The connecting piece provided by the invention is a circular ring formed by folding two half snap rings with the same structure. The inner circumferential surface of each semi-snap ring is provided with a clamping groove which is embedded with a boss on the outer circumferential surface of the spray pipe shell, and the semi-snap rings are clamped on the outer circumferential surface of the end surface of the combustion chamber shell and the outer circumferential surface of the end surface of the spray pipe shell through the clamping grooves, so that the combustion chamber shell and the spray pipe shell are quickly connected.

The inner diameter of the connecting piece is the same as the outer diameter of the annular boss on the outer circumferential surface of the spray pipe shell; the outer diameter of the connector is the same as the outer diameter of the nozzle housing. The width a of draw-in groove is 8mm, and degree of depth h is 8 mm.

The outer circumferential surface of the connecting end of the jet pipe shell is provided with a groove, and the height of the groove wall at one side close to the combustion chamber shell is smaller than that of the groove wall at the other side. The inner surface of the groove forms a side wall matching surface of the semi-clamping ring groove; the width of the groove wall close to one side of the combustion chamber shellThe surface of the groove wall forms a matching surface of the semi-snap ring groove. At the same timeThe end face of the connecting end of the pipe shell is provided with an axial annular bump which is a butt-joint limiting ring of the spray pipe shell. And two screw holes are symmetrically processed on the other end surface of the connecting end of the spray pipe shell, and the two screw holes are respectively corresponding to the screw holes on one semi-clamping ring.

A groove is formed between the outer circumferential surfaces of the connecting ends of the combustion chamber shell, and the height of the groove wall on one side, close to the spray pipe shell, of the groove is smaller than that of the groove wall on the other side. The inner surface of the groove forms a matching surface of the combustion chamber shell and the semi-clamping ring groove; the width of the groove wall close to one side of the spray pipe shellThe surface of the groove wall forms a matching surface of the semi-snap ring groove.

The end of the connecting end of the combustion chamber shell is processed into three-stage steps, wherein the surface of the first-stage step is a mounting matching surface of the butt-joint limiting ring of the spray pipe shell, and the third-stage step is a matching surface of the connecting end face of the spray pipe shell. And a gap formed by the step difference of the second-stage step is a mounting groove of the sealing ring 4.

The invention improves the connection part of the engine combustion chamber and the spray pipe, adds the sealing ring groove and realizes good sealing of the connection part through the sealing ring. An annular groove is reserved outside the connecting part, and the semi-ring connecting piece is installed and then limited by a screw. According to the invention, the connecting structure form of the engine spray pipe and the combustion chamber is improved, so that the difficulty of the engine assembly process is reduced, the quick connection of the spray pipe and the combustion chamber is realized, and the production and assembly cost of the engine is reduced.

In order to verify the effect of the invention, the improved main performance parameters of the engine are measured and evaluated through a circle jump test and a ground static ignition test, and the processing cost of the jet set is counted. Compared with the existing connecting structure of the engine spray pipe and the combustion chamber, the invention has the following advantages:

1. the connecting piece and the matching structure of the invention have simpler processing process and are easier to realize the improvement of the processing precision of the matching part. Before improvement, the circle jump value of the engine is about 0.3mm, and the thrust deflection value is about 0.8 degrees; after the engine circular jump testing device is used, the circular jump value of the engine after the engine is assembled is about 0.2mm, the thrust deflection value is about 0.55 degrees, and the connection structure matching mode provided by the invention can effectively reduce the circular jump testing value of the engine and reduce the thrust deflection of the engine during working.

2. The invention seals the connecting surface through the sealing ring, improves the mounting position of the sealing ring and can avoid the damage of the sealing in the mounting process.

3. The connecting piece provided by the invention reduces the number of parts, the number of the connecting pieces of the engine combustion chamber and the spray pipe is reduced to two double-layer half clamping rings from 20 bolts, 4 operators are required to carry out assembly before improvement, and the working hours are consumed for 3 hours. After the invention is applied, 3 operators are required to carry out assembly, the working hours are consumed for 2 hours, the quick connection of the combustion chamber and the spray pipe is realized, and the labor cost is saved. The reduction of connecting parts also reduces the cost of the kit by about 2%. The overall manufacturing cost of the engine is reduced by about 10 percent through total cost accounting statistics.

Drawings

Fig. 1 is a schematic view of a prior art attachment for a model engine, where fig. 1a is a front view and fig. 1b is a side view.

Fig. 2 is a schematic view of the connection of the present invention to a model engine.

Fig. 3 is a partially enlarged view of a portion a in fig. 2.

FIG. 4 is a schematic view of a combustor casing interface.

FIG. 5 is a schematic view of the nozzle housing interface.

Fig. 6 is a schematic structural view of the connector, wherein fig. 6a is a front view and fig. 6b is a side view. Fig. 6c is a partially enlarged view of a portion B in fig. 6 a.

Fig. 7 is a structural schematic diagram of a cross section of the connector.

In the figure: 1. a combustion chamber housing; 2. a nozzle housing; 3. a connecting member; 4. a seal ring; 5. a screw; 6. the end surface of the butt joint end of the combustion chamber shell; 7. the groove matching surface of the combustion chamber semi-clamping ring; 8. the side wall matching surface of the groove of the semi-clamping ring of the combustion chamber; 9. the spray pipe is butted with a limit ring; 10. the matching surface of the groove of the spray pipe semi-clamping ring; 11. the side wall matching surface of the groove of the spray pipe semi-clamping ring; 12. a threaded bore.

Detailed Description

The embodiment is a connecting piece for connecting a solid rocket engine nozzle and a combustion chamber.

The connecting piece 3 is annular and is formed by folding two semi-snap rings with the same structure. The inner diameter of the connecting piece is the same as the outer diameter of the annular boss on the outer circumferential surface of the spray pipe shell 2; the outer diameter of the connector is the same as the outer diameter of the nozzle housing.

The inner circumferential surface of each semi-snap ring is provided with a clamping groove which is embedded with a boss on the outer circumferential surface of the spray pipe shell, and the semi-snap rings are clamped on the outer circumferential surface of the end surface of the combustion chamber shell and the outer circumferential surface of the end surface of the spray pipe shell through the clamping grooves, so that the combustion chamber shell and the spray pipe shell are quickly connected. The width a of the clamping groove is 8mm, and the depth h of the clamping groove is 8 mm.

In this embodiment, the connection end of the nozzle casing 2 is improved, and a groove is formed in the outer circumferential surface of the connection end of the nozzle casing, and the height of the groove wall on one side close to the combustion chamber casing is smaller than that of the groove wall on the other side. The inner surface of the groove forms a half snap ring groove side wall matching surface 11; the width of the groove wall close to one side of the combustion chamber shellThe surfaces of the groove walls form a half snap ring groove mating surface 10. The end face of the connection end of the nozzle shell 2 is provided with an axial annular bump which is a butt-joint limiting ring 9 of the nozzle shell. And two screw holes are symmetrically processed on the other end surface of the connecting end of the spray pipe shell, and the two screw holes are respectively corresponding to the screw holes on one semi-clamping ring.

The present embodiment also improves the connection end of the combustor casing 1, including the improvement of the outer circumferential surface of the connection end and the improvement of the end face of the connection end. Wherein:

the improvement of the outer circumferential surface of the connecting end of the combustion chamber shell is that a groove is processed between the outer circumferential surfaces of the connecting ends of the combustion chamber shell, and the height of the groove wall at one side close to the spray pipe shell 2 is smaller than that of the groove wall at the other side. The inner surface of the groove forms a matching surface 8 of the combustion chamber shell and the semi-clamping ring groove; the width of the groove wall close to one side of the spray pipe shellThe surface of the groove wall forms a half snap ring groove mating surface 7.

The improvement of the end face of the connecting end of the combustion chamber shell is that the end face 6 of the connecting end of the combustion chamber shell is processed into three-stage steps, wherein the surface of the first-stage step is a mounting matching surface of a butting limiting ring 9 of the spray pipe shell, and the third-stage step is a matching surface of the end face of the connecting end of the spray pipe shell. And a gap formed by the step difference of the second-stage step is a mounting groove of the sealing ring 4.

During operation, the sealing ring 4 is firstly placed in a sealing ring mounting groove formed by the step difference between the end face of the connecting end of the combustion chamber shell and the end face of the connecting end of the spray pipe shell.

Butting the spray pipe shell with the combustion chamber shell: the butt end face 6 of the combustion chamber shell and the butt end face of the spray pipe shell are mutually embedded, and an annular convex block on the outer circumference of the spray pipe shell and an annular convex block on the outer circumference of the combustion chamber shell are jointly combined into an annular clamping block. And clamping the two semi-clamping rings on the outer circumference of the joint of the spray pipe shell and the combustion chamber shell, and clamping the clamping grooves on the inner surfaces of the semi-clamping rings on the annular clamping blocks so as to fixedly connect the spray pipe shell and the combustion chamber shell. The connecting piece consisting of the two half clamping rings is fixedly connected with the spray pipe shell through the four screws 5, so that the spray pipe and the combustion chamber can be quickly installed.