CN114607531B - Small-flow pintle type injector with slotted outer ring of central cylinder - Google Patents
Small-flow pintle type injector with slotted outer ring of central cylinder Download PDFInfo
- Publication number
- CN114607531B CN114607531B CN202210346209.8A CN202210346209A CN114607531B CN 114607531 B CN114607531 B CN 114607531B CN 202210346209 A CN202210346209 A CN 202210346209A CN 114607531 B CN114607531 B CN 114607531B
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- Prior art keywords
- injection
- shaft section
- propellant
- wall
- outer ring
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- 238000002347 injection Methods 0.000 claims abstract description 102
- 239000007924 injection Substances 0.000 claims abstract description 102
- 239000003380 propellant Substances 0.000 claims abstract description 61
- 238000007789 sealing Methods 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
-
- 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
Abstract
The invention provides a small-flow pintle type injector with a slotted outer ring of a central cylinder, which solves the problems that when the flow of propellant is small, the processing and the assembly of a small-size gap of the existing pintle type injector have deviation, and the injection uniformity of the propellant of the outer ring is affected. The injector comprises a central cylinder with a central propellant cavity and a shell sleeved outside the central cylinder; the outer wall of the middle part of the central cylinder is provided with an annular groove, an annular outer ring propellant cavity is formed between the inner wall of the annular groove and the inner wall of the shell, and the outer wall of the shell is provided with an outer ring propellant inlet communicated with the annular outer ring propellant cavity; the outer wall of the lower part of the shell is provided with N injection grooves which are uniformly distributed along the axial direction and are communicated with the annular outer ring propellant cavity, and the positions of the N injection grooves are in one-to-one correspondence with the positions of the N radial injection holes.
Description
Technical Field
The invention relates to a pintle type injector, in particular to a small-flow pintle type injector with a slotted outer ring of a central cylinder.
Background
The two-way propellant impact for a pintle injector is typically of the form: the central channel slotting (or round hole slotting) structure and the outer ring integral girth structure are characterized in that the central channel propellant is injected along the radial direction of the injector, the outer ring propellant is injected along the axial direction of the injector, and the combustion is completed after the two channels of propellants are impacted. However, when the flow rate of the propellant is small, if the outer ring is designed into an integral gap structure, the gap is small, and the processing and the assembly of the gap with small size have deviation, and the deviation can seriously influence the injection uniformity of the propellant of the outer ring, and finally can influence the combustion performance and the working reliability of the product.
Disclosure of Invention
The invention provides a small-flow pintle injector with a slotted outer ring, which aims to solve the technical problems that when the flow of propellant of the traditional pintle injector is smaller, the machining and the assembly of gaps with smaller sizes have deviation, the injection uniformity of the propellant of the outer ring is influenced, and further the combustion performance and the working reliability of products are influenced.
In order to achieve the above purpose, the technical scheme provided by the invention is as follows:
a small-flow pintle type injector with a slotted outer ring of a central cylinder comprises the central cylinder with a central propellant cavity and a shell sleeved outside the central cylinder; the outer wall of the upper end of the central cylinder is provided with a central propellant inlet communicated with a central propellant cavity, the lower end of the central cylinder is provided with N radial injection holes which are uniformly distributed in the circumferential direction and communicated with the central propellant cavity, and N is an integer greater than 2, and the central propellant cylinder is characterized in that:
An annular groove is formed in the outer wall of the middle of the central cylinder, an annular outer ring propellant cavity is formed between the inner wall of the annular groove and the inner wall of the shell, and an outer ring propellant inlet communicated with the annular outer ring propellant cavity is formed in the outer wall of the shell;
The outer wall of the lower part of the shell is provided with N injection grooves which are uniformly distributed along the axial direction and are communicated with the annular outer ring propellant cavity, and the positions of the N injection grooves are in one-to-one correspondence with the positions of the N radial injection holes.
Further, N is an even number;
the N injection grooves comprise N/2 first injection grooves and N/2 second injection grooves, and the first injection grooves and the second injection grooves are staggered along the circumferential direction of the shell;
The first injection groove has a groove width greater than that of the second injection groove, and the first injection groove has a groove depth less than that of the second injection groove.
Further, the cross section of the radial injection hole is circular;
The groove width of the second injection groove is equal to the diameter of the radial injection hole.
Further, N is 8.
Further, a sealing ring is arranged between the inner wall of the upper part of the shell and the outer wall of the central cylinder.
Further, the central cylinder comprises a first shaft section, a second shaft section, a third shaft section and a fourth shaft section which are coaxially and fixedly connected in sequence from top to bottom;
the outer diameters of the first shaft section, the second shaft section and the fourth shaft section are sequentially reduced;
The shell is sleeved on the second shaft section, and the upper end face of the shell is contacted with the lower end face of the first shaft section;
the annular groove is formed in the second shaft section;
the radial injection hole is formed in the fourth shaft section;
The third shaft section is of a conical structure, the large end of the third shaft section is connected with the lower end of the second shaft section, and the small end of the third shaft section is connected with the small end of the fourth shaft section.
Compared with the prior art, the invention has the advantages that:
1. According to the pintle type injector, the propellant outer ring is designed into the slotting structure of the outer wall of the central cylinder, so that the height dimension of slotting gaps can be greatly increased, and the injection uniformity can be well ensured.
2. The pintle type injector adopts a central cylinder outer wall grooving structure, is different from a traditional integral slit structure, has flexible design of an outer ring grooving structure, and can adjust the size and the number of grooves according to design requirements.
3. In order to weaken the impact momentum of the first injection groove, the width of the first injection groove is designed to be larger than the diameter of the radial injection hole, the depth dimension is smaller than that of the second injection groove, when the first injection groove and the radial injection hole are impacted, the momentum of the radial injection hole is relatively stronger, the impact forms a larger fog fan opening angle, and the edge jet flow of the first injection groove which is not impacted by the radial injection hole leaks downwards along the axial direction; in order to strengthen the impact momentum of the second injection groove, the width of the second injection groove is equal to the diameter of the radial injection hole, the depth dimension is larger than that of the first injection groove, when the second injection groove impacts with the radial injection hole, the momentum of the radial injection hole is weaker, and the impact forms a smaller fog fan opening angle; the first injection groove and the second injection groove are impacted to form different impact fog fans, so that a spatial impact fog field distribution gradient is formed, and the method is beneficial to strengthening propellant blending and improving combustion performance.
Drawings
FIG. 1 is a schematic illustration of a small flow pintle injector slotted in the outer ring of the center barrel of the present invention;
FIG. 2 is a schematic view of the structure of a central cylinder in an embodiment of the present invention;
FIG. 3 is a cross-sectional view taken along A-A of FIG. 2;
FIG. 4 is a schematic view showing the impact of the propellant from the first slot and the radial jet holes in the present embodiment;
FIG. 5 is a schematic view showing the impact of the propellant from the second slot with the radial jet holes in the present embodiment;
Wherein, the reference numerals are as follows:
1-a shell, 11-an annular outer ring propellant cavity, 12-an outer ring propellant inlet;
2-central cylinder, 21-radial injection hole, 22-annular groove, 23-first injection groove, 24-second injection groove, 25-central propellant cavity, 26-central propellant inlet, 201-first shaft section, 202-second shaft section, 203-third shaft section, 204-fourth shaft section.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, the small-flow pintle injector with a slotted outer ring of a central cylinder comprises a central cylinder 2 with a central propellant cavity 25 and a shell 1 sleeved outside the central cylinder 2; the outer wall of the upper end of the central cylinder 2 is provided with a central propellant inlet 26 communicated with a central propellant cavity 25, the lower end of the central cylinder is provided with N radial injection holes 21 which are uniformly distributed in the circumferential direction and are communicated with the central propellant cavity 25, and N is an integer greater than 2; an annular groove 22 is formed in the outer wall of the middle part of the central cylinder 2, an annular outer ring propellant cavity 11 is formed between the inner wall of the annular groove 22 and the inner wall of the shell 1, and an outer ring propellant inlet 12 communicated with the annular outer ring propellant cavity 11 is formed in the outer wall of the shell 1; the outer wall of the lower part of the shell 1 is provided with N injection grooves which are uniformly distributed along the axial direction and are communicated with the annular outer ring propellant cavity 11, and the positions of the N injection grooves are in one-to-one correspondence with the positions of the N radial injection holes 21. In the small-flow pintle type injector, the propellant outer ring is designed into a slotting structure on the outer wall of the central cylinder 2, so that the height dimension of slotting gaps can be greatly increased, and the injection uniformity can be well ensured.
As shown in fig. 2, the central cylinder 2 comprises a first shaft section 201, a second shaft section 202, a third shaft section 203 and a fourth shaft section 204 which are coaxially and fixedly connected in sequence from top to bottom; the outer diameters of the first shaft section 201, the second shaft section 202 and the fourth shaft section 204 are sequentially reduced; the shell 1 is sleeved on the second shaft section 202, and the upper end surface of the shell is contacted with the lower end surface of the first shaft section 201; the annular groove 22 is formed on the second shaft section 202; radial injection holes 21 are formed in the fourth shaft section 204; the third shaft section 203 has a tapered structure, a large end thereof is connected to the lower end of the second shaft section 202, and a small end thereof is connected to the small end of the fourth shaft section 204.
To ensure tightness of the pintle injector, a sealing ring is provided between the inner wall of the upper part of the housing 1 and the outer wall of the first shaft section 201 of the central cylinder 2.
The slotting on the outer wall of the central cylinder 2 is different from the traditional integral slot structure, the outer ring slotting structure is flexible in design, and the size and the number of the injection slots can be reasonably adjusted according to the design (the flow of the propellant) requirements.
Preferably, N is an even number, the N injection grooves include N/2 first injection grooves 23 and N/2 second injection grooves 24, and the first injection grooves 23 and the second injection grooves 24 are staggered in the circumferential direction of the housing 1.
As shown in fig. 3, in this embodiment, taking N as 8 as an example, the number of first injection grooves 23 and second injection grooves 24 is 4 uniformly distributed circumferentially, and the number of radial injection holes 21 is 8; the 8 radial injection holes 21 are designed with equal aperture phid, the first injection grooves 23 and the second injection grooves 24 are circumferentially arranged at intervals, the groove width sizes of the first injection grooves 23 and the second injection grooves 24 are w1 and w2 respectively, and the groove depth sizes are h1 and h2 respectively.
In order to weaken the impact momentum of the first injection groove 23, the embodiment designs that the width dimension w1 of the first injection groove 23 is larger than the diameter phid of the radial injection hole 21, the depth dimension h1 is relatively smaller, when the first injection groove 23 impacts with the radial injection hole 21, the momentum of the radial injection hole 21 is relatively stronger, the impact forms a larger fog fan opening angle, and the edge jet of the first injection groove 23 which is not impacted by the radial injection hole 21 leaks downwards along the axial direction, as shown in fig. 4.
The second injection groove 24 collides with the corresponding radial injection hole 21, in order to strengthen the collision momentum of the second injection groove 24, the width dimension w2 of the second injection groove 24 is equal to the diameter phid of the radial injection hole 21, the depth dimension h2 is relatively larger, and when the second injection groove 24 collides with the radial injection hole 21, the momentum of the radial injection hole 21 is relatively weaker, and the collision forms a smaller fog fan angle, as shown in fig. 5.
The working process of the pintle type injector of the embodiment comprises the following steps:
the outer ring propellant enters the annular outer ring propellant cavity 11 through the outer ring propellant inlet 12 and is sprayed out from the side injection groove of the central cylinder 2, and meanwhile, the central propellant enters the central propellant cavity 25 through the central propellant inlet 26, flows in the central propellant cavity 25 and is sprayed out from the radial injection hole 21; then the outer ring propellant and the central propellant collide and burn at the outlet position; the first injection groove 23 and the second injection groove 24 are impacted to form different impact fog fans, so that a spatial impact fog field distribution gradient is formed, and the method is beneficial to strengthening propellant blending and improving combustion performance.
The above description is only of the preferred embodiments of the present invention, and the technical solution of the present invention is not limited thereto, and any modifications made by those skilled in the art based on the main technical concept of the present invention are included in the technical scope of the present invention.
Claims (3)
1. A small-flow pintle injector with a slotted outer ring of a central cylinder comprises a central cylinder (2) with a central propellant cavity (25) and a shell (1) sleeved outside the central cylinder (2); the outer wall of the upper end of the central cylinder (2) is provided with a central propellant inlet (26) communicated with a central propellant cavity (25), the lower end of the central cylinder is provided with N radial injection holes (21) which are uniformly distributed in the circumferential direction and are communicated with the central propellant cavity (25), and N is an integer larger than 2, and the central propellant cylinder is characterized in that:
An annular groove (22) is formed in the outer wall of the middle of the central cylinder (2), an annular outer ring propellant cavity (11) is formed between the inner wall of the annular groove (22) and the inner wall of the shell (1), and an outer ring propellant inlet (12) communicated with the annular outer ring propellant cavity (11) is formed in the outer wall of the shell (1);
The central cylinder (2) comprises a first shaft section (201), a second shaft section (202), a third shaft section (203) and a fourth shaft section (204) which are coaxially and fixedly connected in sequence from top to bottom;
The outer diameters of the first shaft section (201), the second shaft section (202) and the fourth shaft section (204) are sequentially reduced;
the shell (1) is sleeved on the second shaft section (202), and the upper end face of the shell is contacted with the lower end face of the first shaft section (201);
The annular groove (22) is formed on the second shaft section (202);
The radial injection hole (21) is formed in the fourth shaft section (204);
The third shaft section (203) is of a conical structure, the large end of the third shaft section is connected with the lower end of the second shaft section (202), and the small end of the third shaft section is connected with the small end of the fourth shaft section (204);
N injection grooves which are uniformly distributed along the axial direction and communicated with the annular outer ring propellant cavity (11) are formed in the outer wall of the lower part of the shell (1), and the positions of the N injection grooves are in one-to-one correspondence with the positions of N radial injection holes (21);
The N is an even number;
the N injection grooves comprise N/2 first injection grooves (23) and N/2 second injection grooves (24), and the first injection grooves (23) and the second injection grooves (24) are staggered along the circumferential direction of the shell (1);
the groove width of the first injection groove (23) is larger than the groove width of the second injection groove (24), and the groove depth of the first injection groove (23) is smaller than the groove depth of the second injection groove (24);
the section of the radial injection hole (21) is circular;
The groove width of the second injection groove (24) is equal to the diameter of the radial injection hole (21).
2. The center barrel outer race slotted low flow pintle injector of claim 1, wherein: and N is 8.
3. A centre barrel outer race slotted low flow pintle injector as claimed in claim 1 or claim 2, wherein: a sealing ring is arranged between the inner wall of the upper part of the shell (1) and the outer wall of the central cylinder (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210346209.8A CN114607531B (en) | 2022-03-31 | 2022-03-31 | Small-flow pintle type injector with slotted outer ring of central cylinder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210346209.8A CN114607531B (en) | 2022-03-31 | 2022-03-31 | Small-flow pintle type injector with slotted outer ring of central cylinder |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114607531A CN114607531A (en) | 2022-06-10 |
| CN114607531B true CN114607531B (en) | 2024-04-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210346209.8A Active CN114607531B (en) | 2022-03-31 | 2022-03-31 | Small-flow pintle type injector with slotted outer ring of central cylinder |
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| Country | Link |
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| CN (1) | CN114607531B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196651A (en) * | 2014-06-13 | 2014-12-10 | 中国航天科技集团公司第六研究院第十一研究所 | Adjustable coaxial double-slotting bolt type inspirator |
| CN204226048U (en) * | 2014-06-13 | 2015-03-25 | 中国航天科技集团公司第六研究院第十一研究所 | A kind of adjustable coaxial two fluting hydrant ejector filler |
| CN110259604A (en) * | 2019-06-17 | 2019-09-20 | 中国人民解放军国防科技大学 | Pintle injector |
| CN111594350A (en) * | 2020-06-12 | 2020-08-28 | 中国人民解放军战略支援部队航天工程大学 | Pintle injector with adjustable momentum ratio |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2683930B1 (en) * | 2011-03-07 | 2018-12-12 | ArianeGroup SAS | Injector for mixing two propellants comprising at least one injection element with a tricoaxial structure |
-
2022
- 2022-03-31 CN CN202210346209.8A patent/CN114607531B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196651A (en) * | 2014-06-13 | 2014-12-10 | 中国航天科技集团公司第六研究院第十一研究所 | Adjustable coaxial double-slotting bolt type inspirator |
| CN204226048U (en) * | 2014-06-13 | 2015-03-25 | 中国航天科技集团公司第六研究院第十一研究所 | A kind of adjustable coaxial two fluting hydrant ejector filler |
| CN110259604A (en) * | 2019-06-17 | 2019-09-20 | 中国人民解放军国防科技大学 | Pintle injector |
| CN111594350A (en) * | 2020-06-12 | 2020-08-28 | 中国人民解放军战略支援部队航天工程大学 | Pintle injector with adjustable momentum ratio |
Non-Patent Citations (1)
| Title |
|---|
| 高室压快响应栓式喷注器发动机技术研究;凌前程，王春民，高坤，李龙飞;第六届空天动力联合会议•液体推进技术;20211221;第1911-1919页 * |
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| Publication number | Publication date |
|---|---|
| CN114607531A (en) | 2022-06-10 |
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