CN113982787B - Scaling method of gas-liquid pintle injector - Google Patents
Scaling method of gas-liquid pintle injector Download PDFInfo
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- CN113982787B CN113982787B CN202111413976.8A CN202111413976A CN113982787B CN 113982787 B CN113982787 B CN 113982787B CN 202111413976 A CN202111413976 A CN 202111413976A CN 113982787 B CN113982787 B CN 113982787B
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The invention provides a scaling method of a gas-liquid pintle injector, which solves the problem that the prior ground-level high-thrust engine directly carries out test research on a full-size pintle injectorThe problems of time and labor waste exist. The method comprises the steps of 1) determining that the thrust of a scale member of a thrust chamber is reduced to 1/n of the thrust of a prototype member of the thrust chamber according to the thrust reduction scale number n required by the thrust chamber; 2) Determining the structural size parameters of a gas-liquid pintle injector scale-reducing piece to meet the following requirements: the number of radial holes at the end of the reduced scale piece is 1/n of the number of radial holes at the end of the gas-liquid pintle injector prototype piece, the aperture of the radial holes at the end of the reduced scale piece is the same as that of the radial holes at the end of the gas-liquid pintle injector prototype piece, and the circumferential seam width a of the end of the reduced scale piece 1 Width a of circumferential seam with the end of prototype part of gas-liquid pintle injector 0 Same, reduced scale pin head diameter dh 1 Diameter dh of pintle head of gas-liquid pintle injector prototype 0 The following conditional expressions are satisfied:
wherein the value of n satisfies the condition: dh 0 ＞(n‑1)a 0 And N is 0 Can be divided exactly by n.
Description
Technical Field
The invention relates to a scaling technology of an injector, in particular to a scaling method of a gas-liquid pintle injector.
Background
The pintle injector has a better application prospect in a high-transformation-ratio engine, and for a ground-level high-thrust engine at present, the full-size pintle injector is directly subjected to experimental research, so that the research of the full-size pintle injector wastes time and labor.
In the development process of an engine, the application of the scaling technology can save a large amount of cost and period, and can effectively reduce the development risk, so that scientific scaling of the pintle injector is urgent, but no research literature about the scaling technology of the pintle injector is found at present.
Disclosure of Invention
The invention provides a scaling method of a gas-liquid pintle injector, and aims to solve the technical problems that time and labor are wasted when the prior ground-level high-thrust engine is used for directly carrying out test research on a full-size pintle injector.
In order to achieve the purpose, the technical scheme provided by the invention is as follows:
the scaling method of the gas-liquid pintle injector is characterized by comprising the following steps of:
1) Selecting a gas-liquid pintle injector prototype piece and a thrust chamber prototype piece matched with the gas-liquid pintle injector prototype piece for use, and determining that the thrust of a thrust chamber reduced scale piece is reduced to 1/n of the thrust chamber prototype piece on the premise of determining that the chamber pressure of the thrust chamber reduced scale piece is consistent with the chamber pressure of the thrust chamber prototype piece according to the reduction proportion number n of the thrust required by the thrust chamber;
2) Determining the structural size parameters of a gas-liquid pintle injector scale-reducing piece so as to meet the following conditional expression:
a. number N of end radial holes of scale-reducing piece of gas-liquid pintle injector 1 The number N of radial holes at the end of the gas-liquid pintle injector prototype 0 1/n of (1);
b. end head radial hole aperture d of gas-liquid pintle injector scale piece 1 The diameter d of the end radial hole of the gas-liquid pintle injector prototype piece 0 The same;
c. end circumferential seam width a of gas-liquid pintle injector scale piece 1 The width a of the circular seam of the end of the gas-liquid pintle injector prototype 0 The same;
d. pintle head diameter dh of gas-liquid pintle injector scale piece 1 Diameter dh of pintle head of gas-liquid pintle injector prototype 0 The following conditional expressions are satisfied:
wherein the value of n satisfies the barA piece: dh 0 ＞(n-1)a 0 And N is 0 Which can be divided by n.
Further, the method also comprises the step 3): and calculating the Reynolds number and the jet flow momentum ratio of the gas-liquid pintle ejector ruler-reducing piece, and verifying the structural size parameters of the gas-liquid pintle ejector ruler-reducing piece.
Further, the value of n is: n is more than 1 and less than or equal to 10.
Compared with the prior art, the invention has the advantages that:
the invention carries out scale design on the gas-liquid pintle injector, ensures that the gas-liquid pintle injector (scale piece) after the scale design and the full-size gas-liquid pintle injector (prototype piece) have the same jet flow crushing and atomizing processes, carries out test research on the scale piece, can effectively improve the test efficiency and reduce the test cost.
Drawings
FIG. 1 is a schematic view of a gas-liquid pintle injector;
wherein the reference numbers are as follows:
1-central cylinder, 2-outer cover, 3-liquid injection cavity, 4-gas injection cavity and 5-end radial hole.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples.
As shown in fig. 1, the conventional gas-liquid pintle injector includes a central cylinder 1 and an outer cap 2 coaxially disposed outside the central cylinder 1; the inner cavity of the central cylinder 1 is used as a liquid injection cavity 3, and the side wall of the lower end of the central cylinder 1 is provided with an end head radial hole 5; a distance exists between the outer cover 2 and the central cylinder 1 to form a circular seam, and the circular seam is used as a gas injection cavity 4; the liquid propellant is sprayed out from the end head radial hole 5 through the liquid spraying cavity 3 and meets the gas propellant flowing out from the gas spraying cavity 4, so that atomized combustion is generated, and the thrust is provided for the thrust chamber. The existing experimental research on the gas-liquid pintle injector is full-scale, so that a reduced-scale technology is needed to facilitate the experimental research on the gas-liquid pintle injector. However, for a gas-liquid pintle injector, since the injection state of the gaseous propellant is influenced by the environmental pressure, if a reduced-scale mode of the conventional pintle injector is adopted, the reynolds number of the gaseous propellant after the reduction of the scale, the jet momentum ratio of the injector and the like cannot meet similar requirements.
The invention carries out the scale reduction design on the gas-liquid pintle injector and ensures that the flowing, atomizing and burning states of the scale reduction gas-liquid pintle injector have the similarity with the full-size injector.
A scaling method of a gas-liquid pintle injector comprises the following steps:
1) The method comprises the steps of selecting a gas-liquid pintle injector prototype piece and a thrust chamber prototype piece matched with the gas-liquid pintle injector prototype piece, setting a scale as n, determining that the thrust of the thrust chamber scale piece is reduced to 1/n of the thrust chamber prototype piece according to the reduction scale number n of the thrust required by a thrust chamber, changing the flow rate of a propellant of the gas-liquid pintle injector to 1/n under the condition of unchanged specific impulse, and keeping a mixing ratio k (the ratio of the flow rate of the oxidant to the flow rate of a fuel) unchanged, wherein the flow rates of the gas propellant (oxidant) and the liquid propellant (fuel) are changed to 1/n of the corresponding flow rate of the prototype piece.
In addition, the chamber pressure of the thrust chamber scale member should be consistent with that of the thrust chamber prototype member, and the following considerations are mainly made: the chamber pressure of the thrust chamber is kept constant, and the density of the gaseous propellant can be kept constant, so that the application of similar criteria is greatly facilitated.
2) The scale design rule of the gas-liquid pintle injector is to keep the jet flow Reynolds number and the jet flow momentum ratio consistent, so that the consistency of the jet flow crushing and atomizing processes can be ensured. The gas-liquid pintle injector generally adopts a beam-shaped radial jet flow as an inner ring jet flow (liquid propellant) and an annular seam-shaped axial jet flow as an outer ring jet flow (gas propellant). The main structural parameters of the gas-liquid pintle injector comprise an end diameter dh, an end radial hole aperture d, an end radial hole number N and an end circumferential seam width a, wherein the end diameter dh is far larger than the end circumferential seam width a in general;
for the inner ring of the gas-liquid pintle injector, the flow formula of the liquid propellant is as follows:
in the formula (I), the compound is shown in the specification,
is the flow rate of the liquid propellant, p f Is the density, v, of a liquid propellant f The speed of the liquid propellant, d is the diameter of the end radial hole, and N is the number of the end radial holes. As the flow of the liquid propellant is changed into 1/n of the original piece, the number of the radial holes at the end head of the retractable ruler of the gas-liquid pintle injector needs to be reduced to 1/n of the original piece, and the density, the speed and the radial hole diameter of the end head of the liquid propellant are kept unchanged.
For the outer ring of the gas-liquid pintle injector, the gas propellant flow formula is as follows:
in the formula (I), the compound is shown in the specification,
for flow rate of propellant gas, p 0 Density, v, of propellant gas 0 And d is the velocity of the gas propellant, dh is the diameter of the end, and a is the width of the circular seam of the end. The flow rate of the gas propellant is changed to 1/n of the original piece, and the density of the gas propellant, the speed of the gas propellant and the circumferential seam width of the pintle head are kept unchanged.
The structural parameters of the inner ring and the outer ring of the gas-liquid pintle injector are cooperatively reduced, so that the reduction ratio of the inner ring and the outer ring can be simultaneously met. Pintle head diameter dh of gas-liquid pintle injector scale piece 1 The following formula is required:
in the formula: dh 0 The diameter of the end of the gas-liquid pintle injector prototype, a 0 The width of the circular seam at the end of the prototype of the gas-liquid pintle injector.
After the structural size parameter design of the gas-liquid pintle injector scale piece is completed, the invention also comprises the following steps:
step 3) checking the applicability of the scaling criterion: calculating the jet reynolds number and the jet momentum ratio of the scale-reducing piece of the gas-liquid pintle injector;
reynolds number:
where Re is Reynolds number, mu is dynamic viscosity coefficient of propellant, d e In hydraulic diameter, mu and d of scale prototype e Keeping the same;
for the inner ring, d e D, all parameters are unchanged, and the Reynolds number criterion is met;
for the outer ring, d e =2a, it can be seen that each parameter has not changed, satisfying the reynolds number criterion.
Jet flow momentum ratio:
in the formula:
and
the flow rates of the oxidant and the fuel respectively are 1/n of the original piece, so that
Invariable, v o And v f The velocities of the oxidant and fuel, respectively, are unchanged, so the jet momentum ratio is also unchanged.
Therefore, the structural size parameters of the gas-liquid pintle injector scale-reducing component and the gas-liquid pintle injector prototype component meet the following conditional expression:
a. number N of radial holes at end head of scale-reducing piece of gas-liquid pintle injector 1 The number N of radial holes at the end of the prototype part of the gas-liquid pintle injector 0 1/n of (1);
b. end head radial hole aperture d of gas-liquid pintle injector scale piece 1 The diameter d of the end radial hole of the gas-liquid pintle injector prototype 0 The same;
c. end circumferential seam width a of gas-liquid pintle injector scale piece 1 The width a of the circular seam of the end of the gas-liquid pintle injector prototype 0 The same;
d. pintle head diameter dh of gas-liquid pintle injector scale piece 1 Diameter dh of pintle head of gas-liquid pintle injector prototype 0 The following conditional expressions are satisfied:
in summary, the structural dimensional parameters of the gas-liquid pintle injector sizing element of the present invention are set forth in table 1 below:
TABLE 1 structural dimensional parameters of gas-liquid pintle injector scale and prototype
The present embodiment provides structural parameters of a prototype of a gas-liquid pintle injector, which are specifically as follows in table 2:
TABLE 2
| End radial bore diameter d | Number of radial holes N in end | End circumferential seam width a | Needle head diameterdh |
| 1mm | 36 | 2 | 70 |
The value range of n can be 1 < n < 10, and the scaling scale number n in this embodiment is selected to be 6, so that the structural parameters of the scaling piece are as follows in table 3:
TABLE 3
| End radial bore diameter d | Number of radial holes N in end | End circumferential seam width a | Needle head diameter dh |
| 1mm | 6 | 2 | 10 |
The method starts from the flow atomization phenomenon of the gas-liquid pintle injector, analyzes key parameters influencing the flow atomization state, applies a similar principle method to carry out reduced scale design on the gas-liquid pintle injector, and ensures that the Reynolds numbers and the jet momentum ratios of jet flows of a reduced scale piece of the gas-liquid pintle injector and an original piece of the gas-liquid pintle injector are consistent, namely the jet flows are ensured to be consistent in the processes of crushing and atomizing, the method can be used for reduced scale research of the pintle injector, and can effectively improve the research efficiency.
The above description is only for the preferred embodiment of the present invention and does not limit the technical solution of the present invention, and any modifications made by those skilled in the art based on the main technical idea of the present invention belong to the technical scope of the present invention.
Claims (3)
1. A scaling method of a gas-liquid pintle injector is characterized by comprising the following steps of:
1) Selecting a gas-liquid pintle injector prototype piece and a thrust chamber prototype piece matched with the gas-liquid pintle injector prototype piece for use, and determining that the thrust of a thrust chamber scale piece is reduced to 1/n of the thrust chamber prototype piece on the premise of determining that the chamber pressure of the thrust chamber scale piece is consistent with the chamber pressure of the thrust chamber prototype piece according to the reduction proportion number n of the thrust required by a thrust chamber;
2) Determining the structural dimension parameters of the gas-liquid pintle injector scale piece so as to meet the following conditional expression:
a. number N of end radial holes of scale-reducing piece of gas-liquid pintle injector 1 The number N of radial holes at the end of the gas-liquid pintle injector prototype 0 1/n of (1);
b. end head radial hole aperture d of gas-liquid pintle injector scale-reducing piece 1 The diameter d of the end radial hole of the gas-liquid pintle injector prototype piece 0 The same;
c. end circumferential seam width a of gas-liquid pintle injector scale piece 1 The width a of the circular seam of the end of the gas-liquid pintle injector prototype 0 The same;
d. pintle head diameter dh of gas-liquid pintle injector scale-reducing piece 1 The diameter dh of the pintle head of the gas-liquid pintle injector prototype 0 The following conditional expressions are satisfied:
wherein the value of n satisfies the condition: dh 0 ＞(n-1)a 0 And N is 0 Can be coveredn is divided evenly.
2. The method for reducing the size of a gas-liquid pintle injector according to claim 1, further comprising the step 3): and calculating the Reynolds number and the jet flow momentum ratio of the ruler-contracting piece of the gas-liquid pintle injector, and verifying the structural size parameters of the ruler-contracting piece of the gas-liquid pintle injector.
3. A method of reducing the size of a gas-liquid pintle injector as defined in claim 1 or 2, wherein n is selected from the group consisting of: n is more than 1 and less than or equal to 10.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20030018224A (en) * | 2001-08-27 | 2003-03-06 | 현대모비스 주식회사 | testing device of injecter for liquid fuel rocket |
| CN104990711A (en) * | 2015-06-19 | 2015-10-21 | 中国人民解放军装备学院 | Compression ration engine |
| CN112431693A (en) * | 2020-11-19 | 2021-03-02 | 北京航空航天大学 | Pin injector, rocket engine and rocket |
| CN113339160A (en) * | 2021-07-06 | 2021-09-03 | 西安航天动力研究所 | Liquid oxygen methane thrust chamber injector |
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- 2021-11-25 CN CN202111413976.8A patent/CN113982787B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20030018224A (en) * | 2001-08-27 | 2003-03-06 | 현대모비스 주식회사 | testing device of injecter for liquid fuel rocket |
| CN104990711A (en) * | 2015-06-19 | 2015-10-21 | 中国人民解放军装备学院 | Compression ration engine |
| CN112431693A (en) * | 2020-11-19 | 2021-03-02 | 北京航空航天大学 | Pin injector, rocket engine and rocket |
| CN113339160A (en) * | 2021-07-06 | 2021-09-03 | 西安航天动力研究所 | Liquid oxygen methane thrust chamber injector |
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