CN111412086A - Weldless injector for liquid rocket engine - Google Patents
Weldless injector for liquid rocket engine Download PDFInfo
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- CN111412086A CN111412086A CN202010435607.8A CN202010435607A CN111412086A CN 111412086 A CN111412086 A CN 111412086A CN 202010435607 A CN202010435607 A CN 202010435607A CN 111412086 A CN111412086 A CN 111412086A
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- hole
- nozzle
- oxygen
- oxygen nozzle
- fuel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
Abstract
The invention discloses a weldless liquid rocket engine injector, which comprises a fixed disk, a panel, an oxygen nozzle buckling device, an ignition tube and a fuel nozzle, wherein the fixed disk is provided with a first groove butted with an oxygen cavity and a second groove butted with the fuel cavity, the ignition tube is arranged in the center of the fixed disk, the bottom of the first groove is provided with a plurality of first through holes which are arranged in a plurality of concentric circles, the bottom of the second groove is provided with the oxygen nozzle, the oxygen nozzle is provided with an oxidant flow passage, the oxygen nozzle buckling device is arranged in the first through holes, the oxygen nozzle buckling device is provided with a communicating channel for communicating the oxygen cavity with the oxidant flow channel, the panel is provided with a second through hole, the panel is buckled on the second groove to form a fuel cavity, the other side of the panel is a combustion chamber, and the fuel nozzle penetrates through the second through hole and is fixed on the oxygen nozzle. Therefore, the injector is prevented from having more welding lines, the welding process is prevented from being complex, the cavity fleeing risk of the welding lines is avoided, and the injector cannot be disassembled for maintenance.
Description
Technical Field
The invention relates to the technical field of rocket engine injectors, in particular to a weldless liquid rocket engine injector.
Background
The liquid rocket engine injector is used for injecting an oxidant and fuel into a combustion chamber in a specific mode to complete the processes of atomization, evaporation and mixed combustion.
The injector consists of an oxidant nozzle, a fuel nozzle, a panel, a middle sole and other parts. The injectors of the combustion device of the domestic current main engine are connected in a welding mode, the number of welding seams of a single nozzle is at least more than 2, and for a thrust chamber of the main engine of the liquid rocket, the number of the welding seams of the whole injector reaches hundreds or even thousands.
The large number of welds poses two problems: 1. the welding seams among the nozzles and between the nozzles and other parts are brazed, all the welding seams must be formed by one-time brazing, the manufacturing process is complex, and the whole assembly is scrapped if one welding seam is unqualified; 2. the pressure tightness test cannot be carried out on the welding seams between the nozzles and the welding seams between the second bottom and the connecting ring, and the oxygen cavity and the fuel cavity have the risk of explosion caused by cavity channeling; 3. the fuel nozzle and the panel are connected by flanging riveting or brazing, and once the injector is formed, the nozzle is accidentally damaged in the subsequent process or the test process, or the nozzle cannot be replaced when the scheme of the nozzle is intentionally adjusted, so that the whole injector is scrapped.
Therefore, how to provide a weldless injector for a liquid rocket engine to avoid the problems that the injector has many welding seams, the welding process is complicated, the welding seams have cavity channeling risks, and the disassembly and maintenance are impossible is a technical problem to be solved urgently by technical personnel in the field at present.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a weldless injector for a liquid rocket engine, so as to avoid a large number of welding seams of the injector, avoid a complex welding process, avoid a cavity channeling risk in the welding seams, and avoid the failure of disassembly and maintenance.
In order to achieve the purpose, the invention provides the following technical scheme:
a weldless injector for liquid rocket engine comprises a fixed disk, a panel, an oxygen nozzle buckling device, an ignition tube and a fuel nozzle, wherein,
the upper end surface of the fixed disk is provided with a first groove for butting with the oxygen cavity, the lower end surface of the fixed disk is provided with a second groove for butting with the fuel cavity, the groove wall of the first groove is a connecting ring for connecting with the injector shell,
the ignition tube is arranged in the center of the fixed disc, an ignition agent cavity is arranged in the ignition tube, two ends of the ignition agent cavity are respectively communicated with the external igniter and the combustion chamber,
a plurality of first through holes are formed in the bottom of the first groove and are arranged in a plurality of concentric circles, an oxygen nozzle is processed at the bottom of the second groove, an oxidant flow channel is formed in the oxygen nozzle, the first through holes are communicated with the oxidant flow channel and are coaxially arranged,
the oxygen nozzle and the fixed disk are of an integrated structure,
the oxygen nozzle buckling device is arranged in the first through hole, a communicating channel is arranged on the oxygen nozzle buckling device to communicate the oxygen cavity with the oxidant runner,
the panel is provided with a second through hole, the panel is buckled on the second groove to form the fuel cavity, the other side of the panel is a combustion chamber, the fuel nozzle passes through the second through hole and is fixed on the oxygen nozzle,
the fuel nozzle is provided with a third through hole along the axis of the fuel nozzle, an annular boss is arranged in the third through hole, one or more radial through holes are arranged on the wall body of the fuel nozzle and between the annular boss and the nozzle of the fuel nozzle, an internal thread is arranged in the third through hole and on one side of the annular boss far away from the nozzle of the fuel nozzle,
the excircle of oxygen nozzle is the step structure, including big circular outer wall and little circular outer wall, have on the big circular outer wall with the external screw thread that the internal thread cooperation was used, little circular outer wall passes behind the annular boss with have the clearance between the inner wall in third through hole.
Preferably, the oxygen nozzle buckling device is an oxygen nozzle top cover, the oxygen nozzle top cover comprises a counter bore used as a rotational flow chamber, one or more tangential holes are arranged on the wall body of the oxygen nozzle top cover and communicated with the counter bore,
when the oxygen nozzle top cover is placed in the first through hole, the counter bore is communicated with the oxidant flow passage, and the tangential hole is exposed in the first groove and communicated with the oxygen cavity.
Preferably, the tangential hole is in threaded connection with the first through hole,
the rotational flow direction of the tangential hole is consistent with the screwing direction of the threaded connection.
Preferably, the number of the tangential holes is 2 to 6.
Preferably, the oxygen nozzle buckling device is an oxygen nozzle ring, the oxygen nozzle ring comprises an orifice and a fourth through hole which are communicated, the orifice and the fourth through hole are coaxially arranged, and the fourth through hole is communicated with the oxidant flow channel.
Preferably, the bottom of the first through hole is a tapered hole, the tapered hole is communicated with the oxidant flow passage,
the major diameter of the taper hole is smaller than the diameter of the first through hole, and a limiting plane used for limiting the oxygen nozzle buckling device is arranged between the first through hole and the taper hole.
Preferably, the oxygen nozzle fastening device is in threaded connection with the first through hole.
Preferably, the number of the first through holes is 1 to 10.
Preferably, the second through hole is an inverted T-shaped through hole, and includes a small-diameter hole located at one side of the fuel cavity and a large-diameter hole located at one side of the combustion chamber,
the fuel nozzle is of an inverted T-shaped structure and is matched with the inverted T-shaped through hole for use.
Preferably, the ignition tube and the fixed disc are of an integrated structure.
The invention provides a weldless liquid rocket engine injector, which comprises a fixed disc, a panel, an oxygen nozzle buckling device, an ignition tube and a fuel nozzle, wherein,
the upper end surface of the fixed disk is provided with a first groove for butting with the oxygen cavity, the lower end surface of the fixed disk is provided with a second groove for butting with the fuel cavity, the groove wall of the first groove is a connecting ring for connecting with the injector shell,
the ignition tube is arranged in the center of the fixed disc, an ignition agent cavity is arranged in the ignition tube, two ends of the ignition agent cavity are respectively communicated with the external igniter and the combustion chamber,
a plurality of first through holes are formed in the bottom of the first groove and are arranged in a plurality of concentric circles, an oxygen nozzle is processed at the bottom of the second groove, an oxidant flow channel is formed in the oxygen nozzle, the first through holes are communicated with the oxidant flow channel and are coaxially arranged,
the oxygen nozzle and the fixed disk are of an integrated structure,
the oxygen nozzle buckling device is arranged in the first through hole, a communicating channel is arranged on the oxygen nozzle buckling device to communicate the oxygen cavity with the oxidant runner,
the panel is provided with a second through hole, the panel is buckled on the second groove to form the fuel cavity, the other side of the panel is a combustion chamber, the fuel nozzle passes through the second through hole and is fixed on the oxygen nozzle,
the fuel nozzle is provided with a third through hole along the axis of the fuel nozzle, an annular boss is arranged in the third through hole, one or more radial through holes are arranged on the wall body of the fuel nozzle and between the annular boss and the nozzle of the fuel nozzle, an internal thread is arranged in the third through hole and on one side of the annular boss far away from the nozzle of the fuel nozzle,
the excircle of oxygen nozzle is the step structure, including big circular outer wall and little circular outer wall, have on the big circular outer wall with the external screw thread that the internal thread cooperation was used, little circular outer wall passes behind the annular boss with have the clearance between the inner wall in third through hole.
According to the non-welding seam liquid rocket engine injector provided by the invention, an oxidant in the oxygen cavity enters the oxidant runner through the communication channel on the oxygen nozzle buckling device and is injected into a combustion chamber along the oxygen nozzle. The fuel enters the annular gap-shaped gap between the oxygen nozzle and the fuel nozzle through the radial through holes on the fuel nozzle, and is mixed with the oxidant flowing out of the center of the oxygen nozzle at the outlet of the annular gap and sprayed into the combustion chamber for combustion.
The welding seam-free injector for the liquid rocket engine provided by the invention has the advantages that the oxygen cavity and the fuel cavity are completely isolated, and the possibility of channeling oxidant and fuel is avoided.
According to the welding-seam-free injector for the liquid rocket engine, all parts are fixedly connected without adopting a welding mode, and the parts are connected in a threaded mode, so that the replaceability of parts is realized, and the maintainability of the injector is improved.
Therefore, the injector is prevented from having more welding lines, the welding process is prevented from being complex, the cavity fleeing risk of the welding lines is avoided, and the injector cannot be disassembled for maintenance.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a weldless liquid rocket engine injector provided in an embodiment of the present invention;
FIG. 2 is an enlarged view of C of FIG. 1;
FIG. 3 is a schematic structural diagram of a fixing tray according to an embodiment of the present invention;
FIG. 4 is a schematic top view of a fixing plate according to an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a panel according to an embodiment of the present invention;
FIG. 6 is a schematic structural view of an oxygen nozzle tip cap according to an embodiment of the present invention;
FIG. 7 is a schematic sectional view A-A of FIG. 6;
FIG. 8 is a schematic structural diagram of a fuel nozzle provided by an embodiment of the present invention;
FIG. 9 is a schematic cross-sectional view B-B of FIG. 8;
fig. 10 is a schematic structural view of an oxygen nozzle ring provided in an embodiment of the present invention.
In the above FIGS. 1-10:
the fuel nozzle comprises a fixed disc 1, a connecting ring 101, a middle sole 102, an oxygen nozzle 103, an oxygen nozzle mounting hole 104, a fuel nozzle mounting surface 105, an ignition tube 106, an oxidant flow channel 107, a fuel cavity 108, a panel 2, an inverted T-shaped through hole 201, an oxygen nozzle top cover 3, a tangential hole 301, a swirl chamber 302, a fuel nozzle 4, a radial through hole 401, an annular boss 402, an outer boss 403, a gap 404, a third through hole 405, an oxygen nozzle ring 5 and a throttle hole 501.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 10, fig. 1 is a schematic structural diagram of a weldless liquid rocket engine injector according to an embodiment of the present invention; FIG. 2 is an enlarged view of C of FIG. 1; FIG. 3 is a schematic structural diagram of a fixing tray according to an embodiment of the present invention; FIG. 4 is a schematic top view of a fixing plate according to an embodiment of the present invention; FIG. 5 is a schematic structural diagram of a panel according to an embodiment of the present invention; FIG. 6 is a schematic structural view of an oxygen nozzle tip cap according to an embodiment of the present invention; FIG. 7 is a schematic sectional view A-A of FIG. 6; FIG. 8 is a schematic structural diagram of a fuel nozzle provided by an embodiment of the present invention; FIG. 9 is a schematic cross-sectional view B-B of FIG. 8; fig. 10 is a schematic structural view of an oxygen nozzle ring provided in an embodiment of the present invention.
The non-welding seam liquid rocket engine injector provided by the embodiment of the invention comprises a fixed disc 1, a panel 2, an oxygen nozzle 103, an oxygen nozzle buckling device, an ignition tube 106 and a fuel nozzle 4, wherein,
the upper end surface of the fixed disk 1 is provided with a first groove for butting with the oxygen cavity, the lower end surface thereof is provided with a second groove for butting with the fuel cavity 108, the groove wall of the first groove is a connecting ring 101 for connecting with the injector shell,
the ignition tube 106 is arranged at the center of the fixed disc 1, an ignition agent cavity is arranged in the ignition tube 106, two ends of the ignition agent cavity are respectively communicated with the external igniter and the combustion chamber,
as shown in fig. 4, the bottom of the second groove is provided with an oxygen nozzle 103, the oxygen nozzle 103 is provided with an oxidant channel 107, the first through holes are communicated with the oxidant channel 107 and coaxially arranged,
the oxygen nozzle 103 and the fixed disk 1 are of an integrated structure,
the oxygen nozzle fastening device is arranged in the first through hole, a communication channel is arranged on the oxygen nozzle fastening device to communicate the oxygen cavity with the oxidant runner 107,
a second through hole is arranged on the panel 2, the panel 2 is buckled on the second groove to form a fuel cavity 108, the other side of the panel 2 is a combustion chamber, the fuel nozzle 4 passes through the second through hole and is fixed on the oxygen nozzle 103, a third through hole 405 is arranged on the fuel nozzle 4 along the axis of the fuel nozzle 4, an annular boss 402 is arranged in the third through hole 405, one or more radial through holes 401 are arranged on the wall body of the fuel nozzle 4 and between the annular boss 402 and the nozzle of the fuel nozzle 4, one side of the third through hole 405, which is far away from the nozzle of the fuel nozzle 4, of the annular boss 402 is provided with internal threads,
the outer circle of the oxygen nozzle 103 is of a stepped structure and comprises a large circular outer wall and a small circular outer wall, an external thread matched with the internal thread is arranged on the large circular outer wall, and a gap 404 is formed between the small circular outer wall and the inner wall of the third through hole 405 after the small circular outer wall penetrates through the annular boss 402.
According to the non-welding seam liquid rocket engine injector provided by the embodiment of the invention, the oxidant in the oxygen cavity enters the oxidant runner 107 through the communication channel on the oxygen nozzle buckling device and is injected into a combustion chamber along the oxygen nozzle 103. The fuel enters the annular gap 404 between the oxygen nozzle 103 and the fuel nozzle 4 through the radial through holes 401 on the fuel nozzle 4, and is mixed with the oxidant flowing out of the center of the oxygen nozzle 103 at the outlet of the annular gap and sprayed into the combustion chamber for combustion.
The welding seam-free liquid rocket engine injector provided by the embodiment of the invention realizes complete isolation between the oxygen cavity and the fuel cavity 108, and avoids the possibility of channeling oxidant and fuel.
According to the welding-seam-free injector for the liquid rocket engine, parts are not fixedly connected in a welding mode, but in a threaded connection mode, the replaceability of parts is achieved, and the maintainability of the injector is improved.
Therefore, the injector is prevented from having more welding lines, the welding process is prevented from being complex, the cavity fleeing risk of the welding lines is avoided, and the injector cannot be disassembled for maintenance.
In order to further optimize the scheme, the oxygen nozzle buckling device is an oxygen nozzle top cover 3, the oxygen nozzle top cover 3 comprises a counter bore as a cyclone chamber 302, one or more tangential holes 301 are arranged on the wall body of the oxygen nozzle top cover 3 and are communicated with the counter bore,
when the oxygen nozzle top cover 3 is placed in the first through hole, the counter bore is in communication with the oxidant flow passage 107 and the tangential hole 301 is exposed in the first recess in communication with the oxygen chamber.
Oxidant enters the cyclone chamber 302 through the tangential holes 301, one side of each tangential hole 301 is tangent to the wall surface of the cyclone chamber 302, and the oxidant in the oxygen cavity enters the cyclone chamber 302 through the tangential holes 301 of the oxygen nozzle top cover 3 and is sprayed into the combustion chamber along the center of the oxygen nozzle 103 in a rotating mode. Wherein, the number of the tangential holes 301 is 2-6, and 4 is the best.
In order to further optimize the scheme, the tangential hole 301 is in threaded connection with the first through hole, and the rotational flow direction of the tangential hole 301 is consistent with the screwing direction of the threaded connection. When in work, the self-tightening and anti-loosening can be realized under the action of fluid pressure.
In order to further optimize the scheme, the oxygen nozzle buckling device is an oxygen nozzle ring 5, the oxygen nozzle ring 5 comprises a throttling hole 501 and a fourth through hole which are communicated, the throttling hole 501 and the fourth through hole are coaxially arranged, and the fourth through hole is communicated with the oxidant flow channel 107.
The oxygen nozzle buckling device can be an oxygen nozzle top cover 3 and can also be an oxygen nozzle ring 5. Specifically, the oxygen nozzle top cover 3 may be used when a centrifugal oxygen nozzle scheme is used. When a straight oxygen nozzle scheme is used, an oxygen nozzle ring 5 is employed.
In order to further optimize the above scheme, the bottom of the first through hole is a tapered hole, the tapered hole is communicated with the oxidant flow channel 107, the major diameter of the tapered hole is smaller than the diameter of the first through hole, and a limiting plane for limiting the oxygen nozzle fastening device is arranged between the first through hole and the tapered hole. The oxygen nozzle buckling device is in threaded connection with the first through hole. The limiting plane can enable the oxygen nozzle buckling device to penetrate into the limiting position.
Wherein the number of turns of the first through hole is 1-10 turns.
In order to further optimize the above solution, the second through hole is an inverted T-shaped through hole 201, and includes a small diameter hole located on one side of the fuel cavity 108 and a large diameter hole located on one side of the combustion chamber, and the fuel nozzle 4 is an inverted T-shaped structure and is used in cooperation with the inverted T-shaped through hole 201.
Wherein, the ignition tube 106 and the fixed disc 1 are of an integrated structure.
The non-welding seam liquid rocket engine injector provided by the embodiment of the invention can be used in the field of aerospace rocket engines and is suitable for combustion devices such as thrust chambers, fuel gas generators, precombustion chambers and the like. The injector aims to solve the problems that the injector of the existing liquid rocket engine has many welding lines, complex welding process, cavity channeling risk in the welding lines and can not be detached and maintained.
The non-welding seam liquid rocket engine injector provided by the embodiment of the invention comprises a middle bottom ring, namely a fixed disc 1, a panel 2, an oxygen nozzle top cover 3 and a fuel nozzle 4.
The fixed disk 1 is in an H-shaped disk structure, the middle of the fixed disk is a middle sole 102 for separating an oxygen cavity and a fuel cavity, and the outer side of the disk is a connecting ring 101 for connecting a panel and an injector shell.
The oxygen nozzle mounting holes 104, namely the first through holes, are formed in one side of the oxygen cavity of the midsole 102, the oxygen nozzles 103 are formed in one side of the fuel cavity of the midsole 102, the oxygen nozzle mounting holes 104 correspond to the oxygen nozzles 103 in a one-to-one mode, and the central axes of the oxygen nozzle mounting holes and the oxygen nozzles are overlapped.
The bottom of the oxygen nozzle mounting hole 104 is provided with a tapered hole which is communicated with an oxidant flow passage 107 in the oxygen nozzle 103, the diameter of the tapered hole is smaller than the inner diameter of the oxygen nozzle mounting hole 104, and a limit plane is formed at the bottom.
The center hole of the oxygen nozzle 103 is a straight hole and is an oxidant flow channel 107, the excircle of the oxygen nozzle 103 is in a step shape, the outer wall of a large circle is provided with threads, and the outer wall of a small circle is smooth.
The center of the middle sole 102 has hollow circular tubes at both sides of the oxygen chamber and the fuel chamber, and the central axes of the hollow circular tubes at both sides are aligned to form an ignition tube 106.
The oxygen nozzle mounting holes 104 on the fixed disk 1 are arranged in concentric circles, the number of circles of each oxygen nozzle is determined according to the distance between the oxygen nozzles, the number of circles of each oxygen nozzle is determined according to the thrust of an engine, and the number of circles of each oxygen nozzle can be 1-10 circles. In this embodiment, the number of nozzle turns is exemplified by 4 turns.
The panel 2 is a disc structure, the disc is provided with inverted T-shaped through holes 201, and the number and the positions of the inverted T-shaped through holes 201 correspond to the oxygen nozzles 103 on the midsole 102. One side of the fuel cavity is provided with a small hole, and one side of the combustion chamber is provided with a large hole.
The oxygen nozzle top cover 3 is a centrifugal nozzle, the counter bore is a swirl chamber 302, a tangential hole 301 is formed near the bottom of the counter bore, and oxidant enters the swirl chamber 302 through the tangential hole 301. One side of the tangential holes 301 is tangent to the wall surface of the swirl chamber 302, the number of the tangential holes 301 of a single oxygen nozzle top cover 3 is 2-6, the tangential holes are uniformly distributed around the center of the swirl chamber 302, and the swirl direction is consistent with the screwing direction of the screw thread. The outer wall of the oxygen nozzle top cover 3 is provided with external threads on one side close to the outlet of the swirl chamber 302 for connecting with the oxygen nozzle mounting hole 104.
The fuel nozzle 4 is an inverted T-shaped structure, an inner boss, namely an annular boss 402, is arranged in the middle of the inner through hole, the upper portion of the annular boss 402 is a threaded hole, the lower portion of the annular boss 402 is a unthreaded hole, radial through holes 401 which are axially and uniformly distributed are arranged at a section close to the annular boss 402, and the number of the radial through holes 401 is more than 4. An outer boss 403 is arranged at the lower part of the outer side of the fuel nozzle 4, and an inverted T-shaped structure is formed.
The welding seam-free liquid rocket engine injector provided by the embodiment of the invention has the following effects:
(1) the oxidant in the oxygen chamber enters the cyclone chamber 302 through the tangential holes 301 of the oxygen nozzle top cover 3 and is sprayed into the combustion chamber along the center of the oxygen nozzle 3 in a rotating mode. The fuel enters the annular gap between the oxygen nozzle 103 and the fuel nozzle 4 through the radial through holes 401 on the fuel nozzle 4, and is mixed with the oxidant flowing out from the center of the oxygen nozzle 3 at the outlet of the annular gap and sprayed into the combustion chamber for combustion.
(2) The oxygen nozzle 103 is integrally designed with the midsole 102, the connecting ring 101 and the ignition tube 106, so that the oxygen cavity and the fuel cavity 108 are completely isolated, and the possibility of oxidizing agent and fuel channeling is avoided.
(3) The oxygen nozzle top cover 3, the fuel nozzle 4 and the fixed disc 1 are in threaded connection, so that the replaceability of parts is realized, and the maintainability of the injector is improved.
(4) The rotational flow direction of the tangential hole 301 in the oxygen nozzle top cover 3 is consistent with the screwing direction of the threaded connection, and self-tightening and anti-loosening are realized under the action of fluid pressure during working.
(5) The oxygen nozzle top cover 3 is a centrifugal nozzle and is changed into a direct-current nozzle by replacing an oxygen nozzle ring 5, so that the weldless liquid rocket engine injector provided by the embodiment of the invention can adapt to a direct-current scheme and a centrifugal scheme or a direct-current and centrifugal mixed injection scheme.
When the non-welding seam liquid rocket engine injector provided by the embodiment of the invention is assembled, the oxygen nozzle top cover 3 (when a centrifugal oxygen nozzle scheme is used) or the oxygen nozzle ring 5 (when a direct-current oxygen nozzle scheme is used) is screwed into the oxygen nozzle mounting hole 104 on the fixed plate 1 from one side of the oxygen cavity, the opening end surface of the nozzle is in contact with the bottom surface of the hole, and the mounting and screwing torque is controlled to be 8-12 N.m.
The panel 2 is put into the fixed disk 1 from one side of the combustion chamber, the central hole of the panel 2 is in step surface butt joint with the ignition tube 106, the outer circle of the panel 2 is embedded into the step on the groove wall of the second groove, and the step surface butt joint is also performed, and the panel 2 is rotated, so that the inverted T-shaped through hole 201 is aligned with the oxygen nozzle 103.
The fuel nozzle 4 is screwed into the fuel nozzle mounting surface 105 of the oxygen nozzle 103 from the fuel chamber 108 side, and the annular boss 402 is brought into abutment with the end surface of the fuel nozzle mounting surface 105, and the tightening torque is controlled to 8 to 10 n.m.
The atomization characteristic parameters of the centrifugal oxygen nozzle are adjusted by changing the sizes of d2 and d3 of the oxygen nozzle top cover 3 as shown in FIGS. 6 and 7, the retraction depth of the nozzle is adjusted by changing the size of L2 of the fuel nozzle 4 as shown in FIG. 8, and the combustion characteristic of the nozzle is further changed, and the width of the annular gap of the fuel nozzle 4 is adjusted by changing the size of d1 of the fuel nozzle 4, so that the flow resistance characteristic of the fuel nozzle 4 is changed.
The non-welding seam liquid rocket engine injector provided by the embodiment of the invention has the advantages that the nozzle or the panel 2 is ablated in the working process, and when the scheme needs to be adjusted, the fuel nozzle 4 can be detached and replaced by a new fuel nozzle 4 or a new panel 2.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A weldless injector for liquid rocket engine is composed of a fixed disk, a panel, an oxygen nozzle fastener, an igniting tube and a fuel nozzle,
the upper end surface of the fixed disk is provided with a first groove for butting with the oxygen cavity, the lower end surface of the fixed disk is provided with a second groove for butting with the fuel cavity, the groove wall of the first groove is a connecting ring for connecting with the injector shell,
the ignition tube is arranged in the center of the fixed disc, an ignition agent cavity is arranged in the ignition tube, two ends of the ignition agent cavity are respectively communicated with the external igniter and the combustion chamber,
a plurality of first through holes are formed in the bottom of the first groove and are arranged in a plurality of concentric circles, an oxygen nozzle is processed at the bottom of the second groove, an oxidant flow channel is formed in the oxygen nozzle, the first through holes are communicated with the oxidant flow channel and are coaxially arranged,
the oxygen nozzle and the fixed disk are of an integrated structure,
the oxygen nozzle buckling device is arranged in the first through hole, a communicating channel is arranged on the oxygen nozzle buckling device to communicate the oxygen cavity with the oxidant runner,
the panel is provided with a second through hole, the panel is buckled on the second groove to form the fuel cavity, the other side of the panel is the combustion chamber, the fuel nozzle passes through the second through hole and is fixed on the oxygen nozzle,
the fuel nozzle is provided with a third through hole along the axis of the fuel nozzle, an annular boss is arranged in the third through hole, one or more radial through holes are arranged on the wall body of the fuel nozzle and between the annular boss and the nozzle of the fuel nozzle, an internal thread is arranged in the third through hole and on one side of the annular boss far away from the nozzle of the fuel nozzle,
the excircle of oxygen nozzle is the step structure, including big circular outer wall and little circular outer wall, have on the big circular outer wall with the external screw thread that the internal thread cooperation was used, little circular outer wall passes behind the annular boss with have the clearance between the inner wall in third through hole.
2. The Weldless liquid rocket engine injector of claim 1, wherein said oxygen nozzle locking means is an oxygen nozzle cap, said oxygen nozzle cap includes a counter bore as a swirl chamber, said oxygen nozzle cap has one or more tangential holes in its wall that communicate with said counter bore,
when the oxygen nozzle top cover is placed in the first through hole, the counter bore is communicated with the oxidant flow passage, and the tangential hole is exposed in the first groove and communicated with the oxygen cavity.
3. The weldless liquid rocket engine injector according to claim 2, wherein said tangential bore is threadedly connected to said first through bore,
the rotational flow direction of the tangential hole is consistent with the screwing direction of the threaded connection.
4. The weldless liquid rocket engine injector according to claim 2, wherein the number of said tangential holes is 2-6.
5. The weldless liquid rocket engine injector of claim 1, wherein said oxygen nozzle locking device is an oxygen nozzle ring comprising communicating orifice holes and fourth through holes, said orifice holes and said fourth through holes being coaxially arranged, said fourth through holes being in communication with said oxidant flow passage.
6. The weldless liquid rocket engine injector according to claim 1, wherein the bottom of said first through hole is a tapered hole, said tapered hole communicating with said oxidizer flow passage,
the major diameter of the taper hole is smaller than the diameter of the first through hole, and a limiting plane used for limiting the oxygen nozzle buckling device is arranged between the first through hole and the taper hole.
7. The weldless liquid rocket engine injector according to claim 1, wherein said oxygen nozzle snap fitting is threadably connected to said first through hole.
8. The weldless liquid rocket engine injector according to claim 1, wherein the number of said first through holes is 1-10.
9. The weldless liquid rocket engine injector according to claim 1, wherein said second through-hole is an inverted T-shaped through-hole including a small diameter hole at a side of said fuel cavity and a large diameter hole at a side of said combustion chamber,
the fuel nozzle is of an inverted T-shaped structure and is matched with the inverted T-shaped through hole for use.
10. The weldless liquid rocket engine injector of claim 1, wherein said squib and said holding pan are of a unitary construction.
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| CN202010435607.8A CN111412086A (en) | 2020-05-21 | 2020-05-21 | Weldless injector for liquid rocket engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113787305A (en) * | 2021-09-01 | 2021-12-14 | 西安远航真空钎焊技术有限公司 | Processing method of air heater injector |
| CN113790109A (en) * | 2021-09-08 | 2021-12-14 | 西安航天动力研究所 | Support plate injector connecting and sealing structure suitable for composite engine |
| CN114136650A (en) * | 2021-11-05 | 2022-03-04 | 新乡航空工业(集团)有限公司 | Gas-liquid two-phase flow mixing test box device |
| CN114876669A (en) * | 2022-03-31 | 2022-08-09 | 中国人民解放军战略支援部队航天工程大学 | Coaxial model engine for researching tangential unstable combustion of rocket engine |
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2020
- 2020-05-21 CN CN202010435607.8A patent/CN111412086A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113787305A (en) * | 2021-09-01 | 2021-12-14 | 西安远航真空钎焊技术有限公司 | Processing method of air heater injector |
| CN113790109A (en) * | 2021-09-08 | 2021-12-14 | 西安航天动力研究所 | Support plate injector connecting and sealing structure suitable for composite engine |
| CN113790109B (en) * | 2021-09-08 | 2022-11-18 | 西安航天动力研究所 | Support plate injector connecting and sealing structure suitable for composite engine |
| CN114136650A (en) * | 2021-11-05 | 2022-03-04 | 新乡航空工业(集团)有限公司 | Gas-liquid two-phase flow mixing test box device |
| CN114876669A (en) * | 2022-03-31 | 2022-08-09 | 中国人民解放军战略支援部队航天工程大学 | Coaxial model engine for researching tangential unstable combustion of rocket engine |
| CN114876669B (en) * | 2022-03-31 | 2024-01-02 | 中国人民解放军战略支援部队航天工程大学 | Coaxial model engine for researching tangential unstable combustion of rocket engine |
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