High-temperature fuel gas elbow pipe structure

Abstract

The invention discloses a high-temperature fuel gas elbow pipe structure, belongs to the technical field of solid rocket engines, and solves the problem of short working time of an elbow pipe due to ablation leakage at a part splicing gap in a high-temperature and high-pressure fuel gas environment. The high-temperature fuel gas elbow pipe structure comprises a spray pipe shell, a filler block, a pressing ring and an O-shaped ring. The filler block and the pressing ring are cylindrical, a first transverse circular hole and a second vertical circular hole are formed in the spray pipe shell, the filler block is installed in the first circular hole, and the pressing ring is installed in the second circular hole. Only one butt joint face is arranged between the lining block and the pressing ring which form the fuel gas flow channel in the spray pipe shell, under the limited structural size, through the long circular section shape design of the butt joint face fuel gas flow channel and the arrangement of the transition guide block and the arc structure, the large effective sealing area is achieved, the ablation performance of the bent pipe structure is improved, and the service life of the bent pipe structure is prolonged. And the working time of the gas elbow pipe structure in a high-temperature and high-pressure gas environment is prolonged.

Description

Technical Field

[0001] The invention belongs to the technical field of solid rocket engines, and in particular relates to a high-temperature fuel gas bent pipe structure. Background Art

[0002] A solid rocket engine is a chemical rocket engine that uses solid propellant. It is also called a solid propellant rocket engine. After the solid propellant is ignited, it burns in the combustion chamber, converting chemical energy into heat energy, producing high-temperature and high-pressure combustion products. The combustion products flow through the nozzle, where they expand and accelerate, and the heat energy is converted into kinetic energy, which is discharged from the nozzle at high speed to generate thrust.

[0003] In general, a straight pipe connection should be used as much as possible from the combustion chamber to the nozzle to reduce energy loss. However, there are also cases where the gas nozzle is located on the side of the aircraft to adjust the aircraft's attitude, and the gas needs to make a 90° turn from the combustion chamber to the nozzle. In the prior art, the pipes inside the outer shell that come into contact with the gas are spliced ​​together by multiple high-temperature resistant non-metallic parts. There are many splicing gaps, and there is no good structural sealing design at the splicing gaps. In this case, the corners are prone to ablation and leakage under the scouring of high-temperature and high-pressure gas. Therefore, the thermal protection structure of the high-temperature gas elbow needs to improve the splicing parts and splicing gaps to optimize the ablation and leakage problems of the gas elbow. Summary of the invention

[0004] In view of the above analysis, the present invention aims to provide a high-temperature gas elbow structure to solve the problem of short working time of the elbow due to ablation and leakage at the joint gap of parts in a high-temperature and high-pressure gas environment.

[0005] The purpose of the present invention is mainly achieved through the following technical solutions:

[0006] The present invention provides a high-temperature gas elbow structure, comprising a nozzle shell, a liner, a pressure ring and an O-ring; the liner and the pressure ring are both cylindrical, and the interior of the nozzle shell has a first horizontal circular opening and a second vertical circular opening, the liner is installed in the first circular opening, and the pressure ring is installed in the second circular opening, the liner is provided with a first horizontal gas flow channel and a vertical cylindrical sleeve groove, the pressure ring is provided with a second vertical gas flow channel, and the first gas flow channel is connected to the second gas flow channel.

[0007] Furthermore, when the pressure ring is installed in the second circular opening, one end of the pressure ring contacts the groove wall of the cylindrical sleeve groove, and the pressure ring can fix the relative position between the liner block and the nozzle housing.

[0008] Furthermore, a limiting ring is provided on the outer side of the pressure ring, a fixing groove is provided on the surface of the nozzle housing, and the annular groove wall of the fixing groove and the limiting ring form an O-ring installation groove. The O-ring is installed in the installation groove for end face sealing.

[0009] Furthermore, the groove wall of the cylindrical sleeve groove of the liner includes a first docking plane and two first sleeve cylindrical surfaces, the second docking plane of the pressure ring fits with one of the first docking planes, and the second sleeve cylindrical surface of the pressure ring fits with the two first sleeve cylindrical surfaces. The hole at the second docking plane of the pressure ring is a first oblong, the maximum horizontal length of the oblong is the major axis a, the maximum vertical length of the oblong is the minor axis b, the hollow part of the first docking plane is a second oblong, and the first oblong and the second oblong are similar oblongs. The outlet of the second gas flow channel inside the pressure ring is an arc structure.

[0010] Furthermore, similar oblongs are oblongs with the same shape but different sizes.

[0011] Furthermore, the arc structure guides the flow of the gas and strengthens the gas flow bends that are prone to ablation and leakage.

[0012] Furthermore, the material of the lining block is a high temperature resistant composite material.

[0013] Furthermore, the high temperature resistant composite material is a carbon fiber / phenolic composite material.

[0014] Furthermore, the material of the pressure ring is refractory metal.

[0015] Furthermore, the refractory metal is molybdenum.

[0016] Furthermore, the refractory metal is tungsten.

[0017] Furthermore, the liner block is manufactured by integral molding.

[0018] Furthermore, the pressure ring is manufactured by cutting.

[0019] Furthermore, the axis where the first circular opening is located intersects perpendicularly with the axis where the second circular opening is located.

[0020] Furthermore, the cylindrical surfaces of the lining block and the pressure ring are coated with epoxy glue, and the butt joint surface of the pressure ring that is butt jointed with the lining block is coated with epoxy glue.

[0021] Furthermore, a transition guide block is provided at the end of the first gas channel in the liner block, and the transition guide block has the functions of reinforcement and guidance. The liner block and the transition guide block are integrally formed.

[0022] Furthermore, the curved surface of the transition guide block is fitted with the curved surface of the arc structure at the outlet of the second gas flow channel.

[0023] Furthermore, the cylindrical surface of the liner, the cylindrical surface of the pressure ring and the second butt joint plane of the pressure ring are covered with epoxy glue.

[0024] A method for assembling a high-temperature gas elbow structure, assembling the high-temperature gas elbow structure, comprising:

[0025] Step 1: Preparation before assembly.

[0026] Step 2: Installation and adjustment of the lining block.

[0027] Step 3: Installation and adjustment of the pressure ring.

[0028] Step 4: Installation of the O-ring.

[0029] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0030] A) The high-temperature gas elbow structure provided by the present invention has a nozzle shell, a liner and a pressure ring structure, and the liner and the pressure ring are vertically docked and installed inside the shell. Each part is processed independently, the processing and assembly process is simple, and it has good feasibility and implementation.

[0031] B) In the high-temperature gas elbow structure provided by the present invention, the first docking plane of the liner and the second docking plane of the pressure ring are in contact, and the liner and the pressure ring that constitute the gas flow path in the nozzle shell have only one docking surface. At the same time, through the oblong cross-sectional shape design of the gas flow path of the docking surface and the provision of the transition guide block and the arc structure, a larger effective sealing area is achieved within the limited structural dimensions of the liner and the pressure ring, thereby improving the anti-ablation performance of the elbow structure and increasing the working time of the gas elbow structure in a high-temperature and high-pressure gas environment.

[0032] Other features and advantages of the present invention will be described in the following description, and part of them will become obvious from the description, or will be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures particularly pointed out in the written description and the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The drawings are only for the purpose of illustrating particular embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like components throughout the drawings.

[0034] Figure 1 It is a schematic cross-sectional structure diagram of the high-temperature fuel gas elbow structure of the present invention.

[0035] Figure 2It is a schematic diagram of the cross-sectional structure of the nozzle shell of the high-temperature fuel gas elbow structure of the present invention.

[0036] Figure 3 It is a schematic diagram of the cross-sectional structure of the liner block of the high-temperature fuel gas elbow structure of the present invention.

[0037] Figure 4 It is a schematic diagram of the cross-sectional structure of the pressure ring of the high-temperature fuel gas elbow structure of the present invention.

[0038] Figure 5 It is a structural schematic diagram of a liner block of a high-temperature fuel gas elbow structure of the present invention.

[0039] Figure 6 It is a structural schematic diagram of the pressure ring of the high-temperature fuel gas elbow structure of the present invention.

[0040] Figure 7 It is a structural schematic diagram of a pressure ring of an existing common structure.

[0041] Figure 8a It is a schematic cross-sectional structure diagram of the joint between a pressure ring and a liner block of an existing common structure.

[0042] Figure 8b yes Figure 8a Cross-sectional view at AA in the middle.

[0043] Fig. 9 It is a top view of the pressure ring of the high-temperature gas elbow structure of the present invention.

[0044] Fig.10a It is a schematic cross-sectional structure diagram of the butt joint between the pressure ring and the liner block of the present invention.

[0045] Fig.10b yes Fig.10a Cross-sectional view at AA in the middle.

[0046] Fig.11 It is a schematic diagram of the ablation of a high-temperature gas elbow structure in the prior art after working for 1 second in a gas environment with a pressure of 11 MPa and a temperature of 2240K.

[0047] Fig.12 It is a schematic diagram of the ablation of the high-temperature gas elbow structure of the present invention after working for 2 seconds in a gas environment with a pressure of 11 MPa and a temperature of 2240K.

[0048] Fig.13 It is a schematic structural diagram of the first arc surface and the second arc surface in Example 3 of the present invention.

[0049] Reference numerals:

[0050] 1. Nozzle housing, 2. Liner, 3. Pressure ring, 4. O-ring;

[0051] 11. first circular opening, 12. second circular opening, 13. fixing groove, 14. engine docking surface;

[0052] 21. First fuel gas flow channel, 22. Transition guide block, 23. Cylindrical sleeve groove;

[0053] 231. first docking plane, 232. first sleeve cylindrical surface;

[0054] 31. Limiting ring, 32. Arc structure, 33. Second gas flow channel, 34. Second docking plane, 35. Second sleeve cylindrical surface;

[0055] 321. First arc surface, 322. Second arc surface. DETAILED DESCRIPTION

[0056] Preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present invention and are used to explain the principles of the present invention together with the embodiments of the present invention.

[0057] Embodiment 1

[0058] This embodiment provides a high-temperature gas elbow structure. Figure 1 , including a nozzle housing 1, a liner 2, a pressure ring 3 and an O-ring 4; the liner 2 and the pressure ring 3 are both cylindrical, such as Figure 2 As shown, the nozzle housing 1 has a first horizontal circular opening 11 and a second vertical circular opening 12. A liner 2 is installed in the first circular opening 11, and a pressure ring 3 is installed in the second circular opening 12. Figure 3 As shown, the liner block 2 is provided with a transverse first gas flow channel 21 and a vertical cylindrical sleeve groove 23. Figure 4 As shown, a vertical second gas flow channel 33 is opened in the pressure ring 3, and the first gas flow channel 21 is connected to the second gas flow channel 33.

[0059] The opening diameter of the first circular opening 11 of the nozzle housing 1 is consistent with the diameter of the cylindrical body of the liner 2, and a small clearance fit is adopted.

[0060] The diameter of the cylindrical sleeve groove 23 in the liner 2, the diameter of the second circular opening 12 of the nozzle housing 1 and the cylindrical body of the pressure ring 3 are consistent, and all adopt a small clearance fit.

[0061] Preferably, when the pressure ring 3 is installed in the second circular opening 12 of the nozzle housing 1 , one end of the pressure ring 3 contacts the groove wall of the cylindrical sleeve groove 23 , and the pressure ring 3 can fix the relative position between the liner 2 and the nozzle housing 1 .

[0062] The liner block 2 is installed on the first circular opening 11 of the nozzle housing 1, and one end of the pressing ring 3 contacts the groove wall of the cylindrical sleeve groove 23 of the liner block 2 when the pressing ring 3 is installed in the second circular opening 12 of the nozzle housing 1. Figure 5 As shown, the groove wall of the cylindrical sleeve groove 23 of the liner 2 includes a first docking plane 231 and two first sleeve cylindrical surfaces 232, the second docking plane 34 of the pressure ring 3 is in contact with one of the first docking planes 231, and the second sleeve cylindrical surface 35 of the pressure ring 3 is in contact with the two first sleeve cylindrical surfaces 232. The pressure ring 3 limits the ability of the liner 2 to move in the rotation direction of the axis of the first circular opening 11, so that the liner 2 can be relatively fixed to the nozzle housing 1 without the need for additional single-end fixing.

[0063] When installing the liner block 2 and the pressure ring 3, epoxy glue is applied to the outer cylindrical surface of the liner block 2, the outer cylindrical surface of the pressure ring 3 and the second docking plane 34 of the pressure ring 3. After the liner block 2 and the pressure ring 3 are installed, the epoxy glue is cured to achieve the bonding and fixation of the liner block 2, the pressure ring 3 and the nozzle shell 1.

[0064] The second butting plane 34 and the second sleeve cylindrical surface 35 are as follows: Figure 6 shown.

[0065] Preferably, a limiting ring 31 is provided outside the pressure ring 3, a fixing groove 13 is provided on the surface of the nozzle housing 1, and the annular groove wall of the fixing groove 13 and the limiting ring 31 form a mounting groove for the O-ring 4. The O-ring 4 is installed in the mounting groove for end face sealing.

[0066] The nozzle housing 1 is used to be connected to a solid propellant rocket engine. After the engine docking surface 14 at the bottom of the nozzle housing 1 is fitted and fixed to the gas outlet end surface of the solid propellant rocket engine, the O-ring 4 is pressed to form an end face seal.

[0067] When the solid propellant rocket engine ejects high-temperature combustion gas, it passes through the pressure ring 3 and the liner block 2 of the bent pipe structure at one time, and finally ejects from the end of the liner block 2.

[0068] Preferably, a transition guide block 22 is provided at the end of the first gas channel in the liner block 2. The transition guide block 22 has the functions of reinforcement and guidance. The liner block 2 and the transition guide block 22 are integrally formed.

[0069] Preferably, the curved surface of the transition guide block 22 is fitted with the curved surface of the arc structure 32 at the outlet of the second gas flow channel 33 .

[0070] The pressure ring 3 is connected to the gas outlet of the solid propellant rocket engine. The arc structure 32 at the outlet of the second gas flow channel 33 inside the pressure ring 3 and the transition guide block 22 of the first gas flow channel inside the liner 2 play a turning and guiding role for the high-temperature gas.

[0071] Preferably, the material of the lining block 2 is a high temperature resistant composite material.

[0072] Preferably, the high temperature resistant composite material is a carbon fiber / phenolic composite material.

[0073] The liner block 2 plays a role of heat insulation and ablation resistance. The liner block 2 is relatively long and has a large contact area with the shell 1. The use of non-metallic high-temperature resistant composite materials has a good heat insulation effect.

[0074] Preferably, the material of the pressure ring 3 is refractory metal.

[0075] Preferably, the refractory metal is molybdenum.

[0076] Preferably, the refractory metal is tungsten.

[0077] The pressure ring 3 is located at the gas outlet, where the temperature is relatively higher. The gas expansion accelerates further and the temperature will drop. At the same time, the front arc structure 32 is most seriously eroded by the gas. Therefore, refractory metals such as molybdenum or tungsten with stronger ablation resistance are selected.

[0078] Preferably, the liner block 2 is manufactured by integral molding.

[0079] Preferably, the pressure ring 3 is manufactured by cutting.

[0080] Preferably, the axis of the first circular opening 11 and the axis of the second circular opening 12 intersect perpendicularly.

[0081] Preferably, Figure 7 As shown, the hole at the second docking plane of the pressure ring 3 docking with the liner 2 is a first oblong, the maximum horizontal length of the oblong is the major axis a, the maximum vertical length of the oblong is the minor axis b, the hollow part of the first docking plane 231 of the liner 2 is a second oblong, and the first oblong and the second oblong are similar oblongs.

[0082] The area of ​​the first oblong shape is not less than the area of ​​the second oblong shape.

[0083] The liner 2 and the pressure ring 3 are two parts that directly contact the gas. The two parts are spliced ​​to form a 90° gas flow channel. The butt joint is a weak point that causes gas ablation leakage. Therefore, the sealing design of the butt joint of the two parts is the key to the gas elbow structure. Figure 7 As shown, if the pressure ring 3 adopts the existing common cylindrical structure pressure ring, then Figure 8a It can be seen from the cross-sectional structure diagram of the conventional pressure ring and the liner block that in the X-direction cross section, the sealing sections on both sides of the gas flow channel are Lx11 and Lx12 respectively. Figure 8bAs shown, in the cross section in the Y direction, the sealing sections on both sides of the gas flow channel are Ly11 and Ly12 respectively. It can be seen that in the cross section in the Y direction, since the overlap length between the second docking plane 34 of the pressure ring 3 and the first docking plane 231 of the liner 2 is too short, the formed sealing sections Ly11 and Ly12 are very small, and this part is most prone to ablation leakage, so the arc structure 32 is set to transitionally increase the length of the sealing sections Ly11 and Ly12.

[0084] like Fig. 9 As shown, in order to obtain the maximum relative length of the sealing segments Ly11 and Ly12, when the diameter of the gas flow channel of the liner block 2 is determined, the opening length b of the pressure ring 3 in the Y direction can be equal to the length d of the gas flow channel of the liner block 2 in the Y direction (greater than d will not increase the sealing length, but also make the outlet smaller), and the sealing length formed by the remaining length c of the single side of the pressure ring 3 in the Y direction and the first docking plane 231 of the liner block 2 is Ly21 and Ly22, as shown in FIG. Fig.10a and Fig.10b As shown. Due to the provision of the arc structure 32, the gas outlet of the second docking plane 34 of the pressure ring 3 becomes smaller. The smaller gas flow path will affect the smoothness of the gas ejection, generate shock waves and even affect the combustion chamber pressure. Therefore, the opening length of the second docking plane 34 of the pressure ring 3 in the X direction needs to be increased, so that the opening area on the second docking plane 34 of the pressure ring 3 is not less than the opening area of ​​the first docking plane 231 of the liner 2. The increased X-direction opening length is a, thereby forming an oblong opening shape. The shape of the opening on the second docking plane 34 of the pressure ring 3 is as shown Fig. 9 shown.

[0085] Preferably, a transition guide block 22 is provided at the end of the first gas channel in the liner block 2. The transition guide block 22 has the functions of reinforcement and guidance. The liner block 2 and the transition guide block 22 are integrally formed.

[0086] Preferably, the curved surface of the transition guide block 22 is fitted with the curved surface of the arc structure 32 at the outlet of the second gas flow channel 33 .

[0087] Preferably, Fig.11 As shown in FIG. 1 , a schematic diagram of the ablation of the high-temperature gas elbow structure in the prior art after working for 1 second in a gas environment with a pressure of 11 MPa and a temperature of 2240 K shows that the butt joint surface in the high-temperature gas elbow has been burned through, such as Fig.12 As shown in the figure, the ablation diagram of the high-temperature gas elbow structure of the present invention after working for 2s in a gas environment with a pressure of 11MPa and a temperature of 2240K. It can be observed that the butt joint surface in the high-temperature gas elbow is not burned through and has no obvious ablation after a longer working time, that is, the present invention has better anti-ablation performance when facing the same high-pressure and high-temperature environment.

[0088] Example 2

[0089] This embodiment is a method for assembling a high-temperature gas elbow structure. The elbow structure of Embodiment 1 is assembled. The specific steps are as follows:

[0090] Step 1: Preparation before assembly;

[0091] Apply epoxy glue to the cylindrical surface of the lining block 2, the cylindrical surface of the pressing ring 3 and the second butt joint plane 34 of the pressing ring 3;

[0092] Step 2: Installation and adjustment of lining block 2;

[0093] The liner block 2 is pushed into the first circular opening 11 of the nozzle housing 1. After the liner block 2 is pushed in, it is rotated and the position of the liner block 2 is observed from the second circular opening 12 until the first sleeve cylindrical surface 232 of the cylindrical sleeve groove 23 of the liner block 2 is aligned with the wall surface of the second circular opening 12 of the nozzle housing 1, and the installation of the liner block 2 is completed.

[0094] Step 3: Installation and posture adjustment of the pressure ring 3;

[0095] Push the pressing ring 3 into the second circular opening 12 of the nozzle housing 1, and observe the length of the pressing ring 3 extending out of the nozzle housing 1 to determine whether the pressing ring 3 enters the cylindrical sleeve groove 23 of the liner 2. If the pressing ring 3 is flush with the nozzle housing 1, the installation of the pressing ring 3 is complete. If the pressing ring 3 has a portion extending out of the nozzle housing 1, slightly rotate the liner 2 left and right while pushing the pressing ring 3 until the pressing ring 3 is completely entered into the nozzle housing 1.

[0096] After the pressure ring 3 is installed in the nozzle housing 1, the pressure ring 3 is rotated until the first oblong shape at the second docking plane 34 of the pressure ring 3 coincides with the second oblong shape of the docking plane of the liner 2, thereby completing the posture adjustment of the pressure ring 3.

[0097] Step 4: Installation of O-ring 4;

[0098] The O-ring 4 is pressed into the installation groove between the limiting ring 31 and the fixing groove 13 .

[0099] Example 3

[0100] This embodiment 3 is based on the embodiment 1, and the arc structure 32 in the embodiment 1 is improved. Fig.13 The arc surface of the arc structure 32 includes a first arc surface 321 and a second arc surface 322. The first arc surface 321 is a concave surface, and the second arc surface 322 is a convex surface. The concave surface structure of the first arc surface 321 serves to guide the high-temperature combustion gas to accelerate the turn, and the convex surface structure of the second arc surface 322 serves to enhance the anti-ablation performance.

[0101] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A high-temperature gas elbow structure, characterized in that: The nozzle shell (1) comprises a nozzle housing (1), a liner (2), a pressure ring (3) and an O-ring (4); the liner (2) and the pressure ring (3) are both cylindrical; the nozzle shell (1) has a first transverse circular opening (11) and a second vertical circular opening (12); the liner (2) is installed in the first circular opening (11); the pressure ring (3) is installed in the second circular opening (12); the liner (2) is provided with a first transverse gas flow channel (21) and a vertical cylindrical sleeve groove (23); the pressure ring (3) is provided with a second vertical gas flow channel (33); the first gas flow channel (21) and the second gas flow channel (33) are connected.

2. The high-temperature gas elbow structure according to claim 1, characterized in that: When the pressure ring (3) is installed in the second circular opening (12), one end of the pressure ring (3) contacts the groove wall of the cylindrical sleeve groove (23), and the pressure ring (3) can fix the relative position between the liner (2) and the nozzle shell (1).

3. The high-temperature gas elbow structure according to claim 1, characterized in that: A limiting ring (31) is provided on the outside of the pressure ring (3), and a fixing groove (13) is provided on the surface of the nozzle housing (1). The annular groove wall of the fixing groove (13) and the limiting ring (31) form a mounting groove for the O-ring (4), and the O-ring (4) is installed in the mounting groove for end face sealing.

4. The high-temperature gas elbow structure according to claim 1, characterized in that: The material of the lining block (2) is a high temperature resistant composite material.

5. The high-temperature gas elbow structure according to claim 4, characterized in that: The high temperature resistant composite material is a carbon fiber / phenolic composite material.

6. The high-temperature gas elbow structure according to claim 1, characterized in that: The material of the pressure ring (3) is refractory metal.

7. The high-temperature gas elbow structure according to claim 6, characterized in that: The refractory metal is molybdenum.

8. The high-temperature gas elbow structure according to claim 1, characterized in that: The lining block (2) is manufactured by integral molding.

9. The high-temperature gas elbow structure according to claim 1, characterized in that: The cylindrical surface of the lining block (2), the cylindrical surface of the pressing ring (3) and the second docking plane (34) of the pressing ring (3) are covered with epoxy glue.

10. A method for assembling a high-temperature gas elbow structure, characterized in that: Assemble the high-temperature gas elbow structure described in any one of claims 1 to 9.

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