CN116927979A - Needle bolt injector based on gas-liquid double-component propellant variable thrust engine - Google Patents
Needle bolt injector based on gas-liquid double-component propellant variable thrust engine Download PDFInfo
- Publication number
- CN116927979A CN116927979A CN202311103628.XA CN202311103628A CN116927979A CN 116927979 A CN116927979 A CN 116927979A CN 202311103628 A CN202311103628 A CN 202311103628A CN 116927979 A CN116927979 A CN 116927979A
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- Prior art keywords
- pintle
- liquid
- gas
- propellant
- injector
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- 239000007788 liquid Substances 0.000 title claims abstract description 130
- 239000003380 propellant Substances 0.000 title claims abstract description 74
- 238000002485 combustion reaction Methods 0.000 claims abstract description 32
- 238000007789 sealing Methods 0.000 claims abstract description 30
- 238000002347 injection Methods 0.000 claims abstract description 29
- 239000007924 injection Substances 0.000 claims abstract description 29
- 238000004891 communication Methods 0.000 claims abstract description 8
- 230000000903 blocking effect Effects 0.000 claims description 9
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 5
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 3
- 230000008859 change Effects 0.000 claims description 3
- 238000000889 atomisation Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 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 discloses a pintle injector based on a gas-liquid double-component propellant variable thrust engine, which comprises an injector main body, a pintle and a pintle rod; the injector body is arranged on an injection end face of a combustion chamber of the variable thrust engine; the injector body has a central cavity and an injection orifice; the pintle comprises a pintle body and a pintle tail end which are integrally arranged; an annular gas collecting cavity is formed between the pintle body and the inner wall surface of the central cavity; a circular seam type gas nozzle is formed between the pintle body and the inner wall surface of the injection hole; a plurality of liquid nozzles are uniformly distributed on the side wall of the pintle body in the combustion chamber along the circumferential direction; the periphery of the head of the pintle rod is coaxially provided with a sealing plug; the sealing plug is uniformly provided with a plurality of liquid communication holes along the circumferential direction; the outer wall surface of the sealing plug is in sealing sliding connection with the inner wall surface of the liquid propellant runner where the liquid nozzle is located. The invention can be used for variable thrust adjustment of gas-liquid double-component propellant, can avoid influencing the flow field of a combustion chamber, and ensures the speed and the integrity of an injection liquid column.
Description
Technical Field
The invention relates to the field of design of pintle variable thrust engines, in particular to a pintle injector based on a gas-liquid double-component propellant variable thrust engine.
Background
The variable thrust rocket engine can realize optimal thrust control and has unique advantages in space missions such as manned aerospace, space meeting butt joint, orbital maneuver, planetary soft landing detection and the like. In order to ensure that the engine can maintain high performance operation over a wide range of flow rates, variable thrust engines typically employ special injector, combustion chamber and nozzle configurations and designs, with injector design technology being one of the core technologies of variable thrust engines. When the flow of the propellant changes in a large range, the pintle injector can keep the injection pressure drop of the propellant in a reasonable range by adjusting the injection area, so that the engine can keep higher combustion efficiency when the thrust is adjusted in a large range.
For liquid propellants, the liquid flow is proportional to the square root of the area and pressure drop. Therefore, when the flow is required to be regulated in a large range and the pressure drop is kept in a reasonable range, only the area is required to be regulated.
For a gas propellant, its gas flow is related to the area and the pressure ratio upstream and downstream.
Therefore, the existing pintle injector is mainly aimed at two liquid propellants and cannot be applied to rocket engines containing gas propellants. However, in the present two-component liquid rocket engines, an expansion cycle or a partial afterburning cycle is adopted to improve the fuel supply efficiency, and two propellants are required to enter the combustion chamber in a gaseous state and a liquid state respectively.
For this reason, there is a need to develop a pintle injector that can be directed to gas-liquid two-component propellants.
In addition, the existing pintle injector of the liquid-liquid double-component propellant has the following defects in the use process, and needs to be improved:
1. the liquid injection area is adjusted by axial movement of the pintle head positioned in the combustion chamber, thereby adjusting the liquid flow. In the adjusting mode, the pintle head is positioned in the combustion chamber, so that when the pintle head moves axially, the flow field of the combustion chamber is disturbed, the heating condition of the pintle head is changed, and the pintle head is not protected against heat.
2. When the outer pintle sleeve is used for adjusting the pintle area, the pressure of the combustion chamber needs to be overcome, so that the liquid propellant is easily attached to the edge wall of the pintle sleeve when passing through the outer pintle sleeve, and the ejection speed of the liquid propellant and the integrity of an ejected liquid column are affected.
Disclosure of Invention
The invention aims to solve the technical problems of the prior art, and provides a pintle injector based on a gas-liquid double-component propellant variable-thrust engine, which can be used for the variable-thrust adjustment of the gas-liquid double-component propellant, can avoid influencing the flow field of a combustion chamber and can ensure the speed and the integrity of an injected liquid column.
In order to solve the technical problems, the invention adopts the following technical scheme:
a pintle injector based on a gas-liquid double-component propellant variable thrust engine comprises an injector body, a pintle and a pintle rod.
The injector body is arranged on an injection end face of a combustion chamber of the variable thrust engine; the injector body has a central cavity and an injection orifice; wherein the injection hole is communicated with the central cavity and the combustion chamber; the injector body side wall is provided with a propellant gas inlet passage communicating with the central chamber.
The pintle is coaxially inserted in the center of the injector body and comprises a pintle body and a pintle tail end which are integrally arranged.
The tail end of the pintle is connected with the tail end of the central cavity of the injector body in a sealing way; the center of the tail end of the pintle is provided with a liquid collecting cavity, and the side wall of the tail end of the pintle is provided with a liquid propellant inlet channel communicated with the liquid collecting cavity.
The pintle body is coaxially inserted into the central cavity and the injection hole, and the head of the pintle body extends into the combustion chamber; an annular gas collecting cavity is formed between the pintle body and the inner wall surface of the central cavity; a circular seam type gas nozzle is formed between the pintle body and the inner wall surface of the injection hole.
The center of the pintle body is provided with a liquid propellant runner communicated with the liquid collecting cavity.
The side wall of the pintle body positioned in the combustion chamber is uniformly provided with a plurality of liquid nozzles along the circumferential direction.
The needle bolt rod is coaxially inserted into the liquid collecting cavity and the liquid propellant runner; the tail end of the pintle rod is in sealed sliding connection with the inner wall surface of the liquid collecting cavity positioned at the upstream of the liquid propellant inlet channel; the periphery of the head of the pintle rod is coaxially provided with a sealing plug; the sealing plug is uniformly provided with a plurality of liquid communication holes along the circumferential direction; the outer wall surface of the sealing plug is in sealing sliding connection with the inner wall surface of the liquid propellant runner where the liquid nozzle is located.
The pintle rod can slide along the axial direction under the action of an external driving device, so that each liquid nozzle can be partially or completely sealed and blocked, and the flow rate of the liquid propellant can be regulated.
Each liquid nozzle is a rectangular nozzle, and the length and the width of the rectangular nozzle are respectively L and B; the injection area of each liquid nozzle is B x L * The method comprises the steps of carrying out a first treatment on the surface of the Wherein L is * For the length of each liquid nozzle which is not sealed and blocked, and 0 is less than or equal to L * <L。
Let the total number of liquid nozzles be n and the outer diameter of the head of the pintle rod be D z Then n and B are chosen to satisfy the following formula:
wherein a is the minimum value of the blocking ratio, b is the maximum value of the blocking ratio, and 0 < a < b < 1.
a＝0.3，b＝0.7。
The pintle body comprises a hollow cylindrical rod part and a hemispherical head part which are integrally arranged.
The liquid nozzles are uniformly distributed on the periphery of the head of the hollow cylindrical rod part along the circumferential direction, and the distance between each liquid nozzle and the head plane of the hollow cylindrical rod part is L m L is then m The range of the values is as follows: 0.4mm<L m <1mm。
The center of the hemispherical head is provided with a liquid propellant buffer cavity.
The longitudinal section of the liquid propellant buffer cavity is in an inverted triangle shape.
Under the condition that the circumferential seam area of the gas nozzle is kept unchanged, the flow change of the gas propellant is realized by adjusting the pressure ratio of the combustion chamber and the gas collecting cavity.
The tail end of the pintle comprises a tail end large cylindrical part and a tail end small cylindrical part which are integrally arranged.
The tail end small cylinder part is connected with the tail part of the central cavity of the injector main body in a sealing way; the large cylindrical end part is arranged on the outer end face of the injector body, and the liquid propellant inlet channel is arranged on the side wall of the large cylindrical end part.
Each liquid communication hole on the sealing plug is a sector hole, the thickness of a connecting rib between two adjacent sector holes is not less than 3mm, and the sum of the flow area areas of all the sector holes is A, so that A is more than B and L.
The invention has the following beneficial effects:
the needle bolt rod for adjusting the needle bolt area is positioned in the injector main body, and the injector main body is provided with no movable part in the combustion chamber, so that the disturbance influence on the combustion chamber can be reduced when the thrust force adjusting area is changed. Meanwhile, when the pintle rod is moved, the pressure of the combustion chamber does not need to be overcome, so that the influence of the pintle on the ejection speed and the integrity of the ejected liquid column can be reduced.
Drawings
FIG. 1 shows a three-dimensional cross-sectional view of a pintle injector of a gas-liquid two-component propellant variable thrust engine of the present invention.
FIG. 2 shows an enlarged, partial three-dimensional cross-sectional view of a needle bar portion sealing off a liquid nozzle in accordance with the present invention.
FIG. 3 shows a cross-sectional view of a pintle injector of the present invention based on a gas-liquid two-component propellant variable thrust engine.
FIG. 4 shows an enlarged partial cross-sectional view of the needle bar portion sealing off the liquid nozzle of the present invention.
Fig. 5 shows an enlarged schematic view of the encircled area in fig. 4.
The method comprises the following steps:
10. an injector body; 11. a propellant gas inlet passage;
20. a pintle;
21. the tail end of the pintle; 211. a liquid collection cavity; 212. a liquid propellant inlet passage;
22. a pintle body; 221. a liquid propellant channel; 222. a liquid nozzle;
23. an air collection cavity; 24. a gas nozzle; 25. a pintle sealing ring;
30. a pintle lever; 31. sealing the plugs; 32. a liquid communication hole; 33. and a needle bolt rod sealing ring.
Detailed Description
The invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it should be understood that the terms "left", "right", "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and "first", "second", etc. do not indicate the importance of the components, and thus are not to be construed as limiting the present invention. The specific dimensions adopted in the present embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.
As shown in fig. 1 and 3, a pintle injector based on a gas-liquid two-component propellant variable thrust engine includes an injector body 10, a pintle 20, and a pintle stem 30.
The injector body is arranged on an injection end face of a combustion chamber of the variable thrust engine; the injector body has a central cavity and an injection orifice; wherein the injection hole is communicated with the central cavity and the combustion chamber; the injector body side wall is provided with a propellant gas inlet passage 11 communicating with the central chamber.
The pintle is coaxially inserted in the center of the injector body and includes integrally disposed pintle body 22 and pintle tail 21.
The center of the tail end of the pintle is provided with a liquid collecting cavity 211.
The pintle tail end preferably includes an integrally disposed tail end large cylindrical portion and tail end small cylindrical portion.
The small cylindrical end portion is preferably sealingly connected to the end portion of the central chamber of the injector body by a pintle seal 25.
The rear large cylindrical portion is mounted on the outer end face of the injector body, and a liquid propellant inlet passage 212 is provided in the side wall of the rear large cylindrical portion.
The pintle body is coaxially inserted into the central cavity and the injection hole, and the head of the pintle body extends into the combustion chamber; an annular gas collecting cavity 23 is formed between the pintle body and the inner wall surface of the central cavity; a circular slit type gas nozzle 24 is formed between the pintle body and the inner wall surface of the injection hole. The invention sets the circumferential seam area of the gas nozzle according to the flow required by the gas propellant.
The gas flow is related to the area and the pressure ratio upstream and downstream due to the gas propellant. When the area is fixed, the flow rate of the gas is related to the pressure ratio upstream and downstream. Thus, the injection area of the propellant gas can be kept constant as long as a certain pressure drop is maintained when the thrust force is changed. The invention realizes the flow change of the gas propellant by adjusting the pressure ratio of the combustion chamber and the gas collecting cavity under the condition that the circumferential seam area of the gas nozzle is kept unchanged.
The center of the pintle body is provided with a liquid propellant flow passage 221 communicated with the liquid collecting cavity.
The pintle body preferably includes an integrally disposed hollow cylindrical shaft portion and a hemispherical head portion.
The side wall of the pintle body (i.e. the side wall of the hollow cylindrical rod part) positioned in the combustion chamber is uniformly provided with a plurality of liquid nozzles 222 along the circumferential direction.
As shown in FIGS. 2 and 4, the distance between each liquid nozzle and the head plane of the hollow cylindrical rod portion is preferably L m L is then m The range of the values is as follows: 0.4mm<L m <1mm。L m The arrangement of the device can ensure that the lower end of the liquid outlet is as close as possible, and simultaneously eliminates the uneven lower plane or the poor sealing caused by a round angle.
The center of the hemispherical head is provided with a liquid propellant buffer cavity, and further, the longitudinal section of the liquid propellant buffer cavity is preferably in an inverted triangle shape.
As shown in fig. 5, each liquid nozzle is preferably a rectangular spout, the length and width of which are L and B, respectively; the injection area of each liquid nozzle is B x L * The method comprises the steps of carrying out a first treatment on the surface of the Wherein L is * For the length of each liquid nozzle which is not sealed and blocked, and 0 is less than or equal to L * <L。
As shown in fig. 2 and 4, the pintle rod is coaxially inserted into the liquid collecting cavity and the liquid propellant flow passage; the tail end of the pintle rod is in sealed sliding connection with the inner wall surface of the liquid collecting cavity positioned at the upstream of the liquid propellant inlet passage preferably through a pintle rod sealing ring 33; the periphery of the head of the pintle rod is coaxially provided with a sealing plug 31; the sealing plug is uniformly provided with a plurality of liquid communication holes 32 along the circumferential direction; the outer wall surface of the sealing plug is in sealing sliding connection with the inner wall surface of the liquid propellant runner where the liquid nozzle is located.
Further, each liquid communication hole on the sealing plug is a fan-shaped hole, the thickness of a connecting rib between two adjacent fan-shaped holes is not less than 3mm, and the sum of the flow area areas of all the fan-shaped holes is A, so that A is more than B.
The pintle rod can slide along the axial direction under the action of an external driving device, so that each liquid nozzle can be partially or completely sealed and blocked, and the flow rate of the liquid propellant can be regulated.
Let the total number of liquid nozzles be n and the outer diameter of the head of the pintle rod be D z Then n and B are chosen to satisfy the following formula:
wherein a is the minimum value of the blocking ratio, b is the maximum value of the blocking ratio, and 0 < a < b < 1.
The values of the blocking ratios a and b reflect the contact blending ratio or degree of the liquid propellant, and when the total outlet area of the liquid nozzle is fixed, the blocking ratio is increased, the thickness of a liquid film can be reduced, the blending effect of the propellant is enhanced, and the mixing combustion performance is improved. The blocking ratio is reduced, the atomization cone angle is increased, and the reaction area is increased. In addition, adjust fixed length pintle pole, adjust the area reduction, improve the precision of adjusting the area.
In this embodiment, a=0.3 and b=0.7 are preferable, that is, the following formula needs to be satisfied:
when the liquid film is smaller than 0.3, the liquid film is in a high working condition, the atomization cone angle is too large, the liquid drop particle size is large, and the combustion effect is poor.
When the length of the liquid nozzle is more than 0.7, the distance between the liquid nozzles is too small, the strength is insufficient, the whole adjusting length is reduced by 2 times, and the error of the adjusting area is increased.
Aiming at the characteristics of gas-liquid double components, only the liquid injection area is adjusted, the gas injection area is not adjusted, and the complexity and design difficulty of the pintle are reduced. The variable flow rate is met, the injection pressure drop of the two propellants is ensured to be kept in a reasonable range, and good atomization effect and high combustion efficiency are obtained.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the equivalent changes belong to the protection scope of the present invention.
Claims (10)
1. Needle bolt injector based on gas-liquid double-component propellant becomes thrust engine, its characterized in that: comprises an injector body, a pintle and a pintle rod;
the injector body is arranged on an injection end face of a combustion chamber of the variable thrust engine; the injector body has a central cavity and an injection orifice; wherein the injection hole is communicated with the central cavity and the combustion chamber; the side wall of the injector body is provided with a gas propellant inlet channel communicated with the central cavity; the pintle is coaxially inserted in the center of the injector body and comprises a pintle body and a pintle tail end which are integrally arranged;
the tail end of the pintle is connected with the tail end of the central cavity of the injector body in a sealing way; the center of the tail end of the pintle is provided with a liquid collecting cavity, and the side wall of the tail end of the pintle is provided with a liquid propellant inlet channel communicated with the liquid collecting cavity;
the pintle body is coaxially inserted into the central cavity and the injection hole, and the head of the pintle body extends into the combustion chamber; an annular gas collecting cavity is formed between the pintle body and the inner wall surface of the central cavity; a circular seam type gas nozzle is formed between the pintle body and the inner wall surface of the injection hole; the center of the pintle body is provided with a liquid propellant runner communicated with the liquid collecting cavity;
a plurality of liquid nozzles are uniformly distributed on the side wall of the pintle body in the combustion chamber along the circumferential direction;
the needle bolt rod is coaxially inserted into the liquid collecting cavity and the liquid propellant runner; the tail end of the pintle rod is in sealed sliding connection with the inner wall surface of the liquid collecting cavity positioned at the upstream of the liquid propellant inlet channel; the periphery of the head of the pintle rod is coaxially provided with a sealing plug; the sealing plug is uniformly provided with a plurality of liquid communication holes along the circumferential direction; the outer wall surface of the sealing plug is in sealing sliding connection with the inner wall surface of the liquid propellant runner where the liquid nozzle is positioned;
the pintle rod can slide along the axial direction under the action of an external driving device, so that each liquid nozzle can be partially or completely sealed and blocked, and the flow rate of the liquid propellant can be regulated.
2. The pintle injector based on a gas-liquid two-component propellant variable thrust engine of claim 1, wherein: each liquid nozzle is a rectangular nozzle, and the length and the width of the rectangular nozzle are respectively L and B; the injection area of each liquid nozzle is B x L * The method comprises the steps of carrying out a first treatment on the surface of the Wherein L is * For the length of each liquid nozzle which is not sealed and blocked, and 0 is less than or equal to L * <L。
3. The pintle injector based on a gas-liquid two-component propellant variable thrust engine of claim 2, wherein: let the total number of liquid nozzles be n and the outer diameter of the head of the pintle rod be D z Then n and B are chosen to satisfy the following formula:
wherein a is the minimum value of the blocking ratio, b is the maximum value of the blocking ratio, and 0 < a < b < 1.
4. A pintle injector based on a gas-liquid two-component propellant variable thrust engine according to claim 3, characterized in that: a=0.3, b=0.7.
5. The pintle injector based on a gas-liquid two-component propellant variable thrust engine of claim 1, wherein:
the pintle body comprises a hollow cylindrical rod part and a hemispherical head part which are integrally arranged;
the liquid nozzles are uniformly distributed on the periphery of the head of the hollow cylindrical rod part along the circumferential direction, and the distance between each liquid nozzle and the head plane of the hollow cylindrical rod part is L m L is then m The range of the values is as follows: 0.4mm<L m <1mm。
6. The pintle injector based on the gas-liquid two-component propellant variable thrust engine of claim 5, wherein: the center of the hemispherical head is provided with a liquid propellant buffer cavity.
7. The pintle injector based on a gas-liquid two-component propellant variable thrust engine of claim 6, wherein: the longitudinal section of the liquid propellant buffer cavity is in an inverted triangle shape.
8. The pintle injector based on a gas-liquid two-component propellant variable thrust engine of claim 1, wherein: under the condition that the circumferential seam area of the gas nozzle is kept unchanged, the flow change of the gas propellant is realized by adjusting the pressure ratio of the combustion chamber and the gas collecting cavity.
9. The pintle injector based on a gas-liquid two-component propellant variable thrust engine of claim 1, wherein:
the tail end of the pintle comprises a tail end large cylindrical part and a tail end small cylindrical part which are integrally arranged;
the tail end small cylinder part is connected with the tail part of the central cavity of the injector main body in a sealing way; the large cylindrical end part is arranged on the outer end face of the injector body, and the liquid propellant inlet channel is arranged on the side wall of the large cylindrical end part.
10. The pintle injector based on a gas-liquid two-component propellant variable thrust engine of claim 2, wherein: each liquid communication hole on the sealing plug is a sector hole, the thickness of a connecting rib between two adjacent sector holes is not less than 3mm, and the sum of the flow area areas of all the sector holes is A, so that A is more than B and L.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311103628.XA CN116927979A (en) | 2023-08-30 | 2023-08-30 | Needle bolt injector based on gas-liquid double-component propellant variable thrust engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311103628.XA CN116927979A (en) | 2023-08-30 | 2023-08-30 | Needle bolt injector based on gas-liquid double-component propellant variable thrust engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116927979A true CN116927979A (en) | 2023-10-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311103628.XA Pending CN116927979A (en) | 2023-08-30 | 2023-08-30 | Needle bolt injector based on gas-liquid double-component propellant variable thrust engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116927979A (en) |
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2023
- 2023-08-30 CN CN202311103628.XA patent/CN116927979A/en active Pending
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