CN117189422A - Annular throat type expansion bias flow spray pipe with adjustable center bolt position and rocket engine - Google Patents
Annular throat type expansion bias flow spray pipe with adjustable center bolt position and rocket engine Download PDFInfo
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- CN117189422A CN117189422A CN202311125607.8A CN202311125607A CN117189422A CN 117189422 A CN117189422 A CN 117189422A CN 202311125607 A CN202311125607 A CN 202311125607A CN 117189422 A CN117189422 A CN 117189422A
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- 239000007921 spray Substances 0.000 title claims abstract description 90
- 238000002485 combustion reaction Methods 0.000 claims abstract description 40
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 238000007789 sealing Methods 0.000 claims abstract description 5
- 125000004122 cyclic group Chemical group 0.000 claims description 5
- 239000003380 propellant Substances 0.000 description 14
- 238000000926 separation method Methods 0.000 description 8
- 230000008859 change Effects 0.000 description 5
- 239000002737 fuel gas Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000007423 decrease Effects 0.000 description 3
- 230000033001 locomotion Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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Abstract
The invention relates to the field of rocket engines, in particular to a circular throat type expansion bias flow spray pipe with an adjustable center bolt position and a rocket engine, comprising the following components: a spray pipe; the central bolt is arranged in the spray pipe, the cylinder section of the central bolt penetrates out of the head part of the combustion chamber of the spray pipe and is used for being connected with the linear driving mechanism, and the central bolt is connected with the head part of the combustion chamber through the movable sealing ring. The device provides the working efficiency of the spray pipe.
Description
Technical Field
The invention relates to the field of rocket engines, in particular to a circular throat type expansion bias flow spray pipe with an adjustable center bolt position and a rocket engine.
Background
The reusable carrier rocket needs to realize stepless adjustment of thrust under a larger thrust-changing ratio in order to realize accurate control of the track in the landing recovery process. At present, the thrust adjustment method of the engine mainly comprises two methods: one is to adjust the mass flow rate of the propellant fed into the thrust chamber, thereby changing the combustion chamber pressure to effect a thrust change; another is to adjust the mass flow rate of the propellant fed to the thrust chamber while adjusting the throat area so that the combustion chamber pressure remains suitably constant. In the former method, to reduce the propellant mass flow rate, the injector pressure drop is reduced. This will deteriorate the mixing quality of the propellant, cause an unsuitable liquid impingement state and poor atomization, lead to a reduction in combustion efficiency and specific impulse, and sometimes cause unstable combustion.
The latter thrust regulation method may be implemented by a throat-bolt engine. The throat bolt type engine drives the throat bolt to move back and forth in the spray pipe through the servo mechanism, and the throat area of the spray pipe is changed to finish thrust adjustment. When the throat bolt retreats towards the direction of the combustion chamber, the pressure of the combustion chamber is reduced by increasing the throat area, so that the thrust is reduced; when the throat bolt advances towards the direction of the spray pipe, the reduction of the throat area increases the pressure of the combustion chamber, so that the thrust is increased. For the liquid rocket engine, the stepless adjustment of the thrust under a larger variable thrust ratio can be realized by simultaneously adjusting the throat bolt position and the propellant mass flow rate. However, the change of the throat bolt position continuously changes the position and the area of the throat part of the spray pipe, so that the non-traditional throat vibration and flow separation phenomenon occur in the spray pipe, as the throat bolt moves towards the throat part, the included angle between the main flow direction passing through the throat part and the engine axis is increased, an annular blocking area is formed at the original throat part, flow separation occurs at the tail end of the throat bolt and in the expansion section of the spray pipe, and the flow separation is often accompanied with strong unsteady and asymmetric side loads and fluid-solid coupling phenomenon of the flow field, so that the specific flushing of the engine is reduced, and the spray pipe structure and rocket orbit entering precision are endangered.
Therefore, it is desirable to provide a throat-type expansion bias flow nozzle with an adjustable center pin position and a rocket engine to solve the above-mentioned problems.
Disclosure of Invention
The invention provides a circular throat type expansion bias flow spray pipe with an adjustable center bolt position, which is characterized in that the center bolt of the circular throat type expansion bias flow spray pipe is connected with a linear driving mechanism of a rocket engine by arranging the circular throat type expansion bias flow spray pipe with the adjustable center bolt, so that the problems of jeopardy of a spray pipe structure and rocket in-orbit precision caused by the reduction of specific impulse of the engine in the prior art are solved.
The invention discloses a circular throat type expansion bias flow spray pipe with an adjustable center bolt position, which adopts the following technical scheme: comprising the following steps:
a spray pipe;
the central bolt is arranged in the spray pipe, the cylinder section of the central bolt penetrates out of the head part of the combustion chamber of the spray pipe and is used for being connected with the linear driving mechanism, and the central bolt is connected with the head part of the combustion chamber through the movable sealing ring.
Preferably, the throat area of the nozzle is:
A t ＝πr C x(sin 3 θ+2sinθ)
wherein A is t Representing the throat area of the nozzle;
x represents the relative distance between the spray pipe and the center bolt;
r C representing the distance from the throat of the spray pipe to the axis of the engine at the corresponding position C of the center bolt;
θ represents the airflow deflection angle of the nozzle.
Preferably, the throat of the nozzle at the corresponding position C of the center bolt is: and (3) taking the intersection point of the extension line of the inner wall surface of the constant diameter section of the spray pipe and the central bolt as the throat part of the spray pipe at the corresponding position C of the central bolt.
Preferably, the relative distance between the nozzle and the center pin is: the distance between the corresponding position C of the central bolt and the intersection point B and BC of the extension line of the inner wall surface of the spray pipe expansion section in the direction parallel to the axis of the engine is the relative distance.
Preferably, the jet pipe has an air flow deflection angle of: and an included angle between an extension line of the inner wall surface of the spray pipe expansion section and the direction of the axis of the engine.
A rocket engine comprises a circular throat type expansion bias flow spray pipe with an adjustable central bolt position, wherein the head part of a combustion chamber of the circular throat type expansion bias flow spray pipe is connected with a rocket body of the rocket engine, and a linear driving mechanism of the rocket engine is connected with the central bolt of the circular throat type expansion bias flow spray pipe.
The beneficial effects of the invention are as follows:
1. because the throat bolt engine using the common spray pipe usually has obvious performance loss when in work, namely the position and the area of the throat part of the spray pipe are continuously changed by changing the position of the throat bolt, so that the phenomenon of non-traditional throat vibration and flow separation occur in the spray pipe, along with the movement of the throat bolt to the throat part, the main flow direction passing through the throat part and the included angle between engine shafts are increased, an annular blocking area is formed in the original throat part, the flow separation occurs at the tail end of the throat bolt and in the expansion section of the spray pipe, and the thrust is reduced and the ablation of the separation area aggravates the bias flow action through the center bolt; in the invention, the fuel gas is sprayed to the inner wall of the spray pipe after being deflected by the central bolt, at the moment, the fuel gas flow is restrained by the inner wall surface of the spray pipe and the pneumatic boundary on the interface between the air in the spray pipe and the fuel gas, when the atmospheric pressure and the pressure of the combustion chamber change under different working conditions, the pressure ratio between the pressure of the combustion chamber and the atmospheric pressure changes, namely, when the pressure ratio becomes large, the pneumatic boundary contracts towards the inside of the spray pipe, and the air flow tends to be full of the spray pipe; when the pressure ratio is reduced, the pneumatic boundary expands towards the wall of the spray pipe, airflow tends to flow close to the inner wall of the spray pipe, and the pneumatic boundary moves adaptively along with the pressure ratio, so that the compensation of the external atmospheric pressure and the pressure of the combustion chamber is realized, the expansion loss is reduced, and the specific impulse of the engine is improved.
2. The throat area of the spray pipe of the engine is changed by moving the center bolt, so that the wide-range thrust adjustment of the throat area is realized, namely the center bolt moves along the engine axis to deviate from the motion direction of the rocket, at the moment, the relative distance between the spray pipe and the center bolt is increased, the equivalent throat area is increased, the expansion ratio of the spray pipe is reduced as the outlet area of the spray pipe is kept unchanged, the pressure of the combustion chamber is reduced under the premise that the mass flow rate of the propellant is unchanged, the thrust of the engine is reduced as the pressure of the combustion chamber is reduced, and meanwhile, the mass flow rate of the propellant is reduced when the center bolt moves, so that the larger variable thrust ratio can be achieved; when the center bolt moves along the movement direction of the rocket of the engine axis, the relative distance between the spray pipe and the center bolt is reduced, the equivalent throat area is reduced, the expansion ratio of the spray pipe is increased as the outlet area of the spray pipe is kept unchanged, the pressure of the combustion chamber is increased and the thrust of the engine is increased as the mass flow rate of the propellant is unchanged.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the general structure of an adjustable center pin position annular throat type expansion bias flow nozzle of the present invention;
FIG. 2 is a schematic diagram of the throat geometry of an adjustable center pin position annular throat type expansion bias flow nozzle of the present invention;
FIG. 3 shows the internal pressure distribution of the annular throat type expansion bias flow spray pipe with the adjustable center bolt position under different combustion chamber pressures when the annular throat type expansion bias flow spray pipe works at sea level;
FIG. 4 shows the internal pressure distribution of the nozzle at different flying heights when the annular throat type expansion bias flow nozzle with the adjustable center bolt position works under constant combustion chamber pressure;
FIG. 5 is a schematic illustration of the outline of a bell-shaped nozzle in comparative verification;
FIG. 6 is a schematic view of the nozzle plume of the annular throat type expansion bias flow nozzle with adjustable center pin position according to the present invention when the pressure and flight height of the 6MPa combustion chamber are 0km,16.7km and 30km respectively;
in the figure: 1. a spray pipe; 2. a center bolt; 3. dynamic sealing; 4. the arrow body is connected with the interface; 5. and a connecting end.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
An embodiment of the adjustable center pin position annular throat type expansion bias flow spray pipe of the invention, as shown in figure 1, comprises: the jet pipe 1 and the central bolt 2, the central bolt 2 is arranged in the jet pipe 1, the cylinder section of the central bolt is connected with a linear driving mechanism of the throat bolt type rocket engine after penetrating out of the combustion chamber head of the jet pipe, the output end of the linear driving mechanism of the throat bolt type rocket engine is connected with a connecting end 5 of the central bolt 2 extending out of the jet pipe 1, wherein the linear driving mechanism is a linear motor, and the central bolt 2 is connected with the combustion chamber head 4 through a movable sealing ring 3.
Specifically, the throat area of the nozzle 1 is:
A t ＝πr C x(sin 3 θ+2sinθ)
wherein A is t Representing the throat area of the nozzle;
x represents the relative distance between the spray pipe and the center bolt;
r C representing the distance from the throat of the spray pipe to the axis of the engine at the corresponding position C of the center bolt;
θ represents the airflow deflection angle of the nozzle;
as shown in fig. 2, the throat of the nozzle 1 at the position C corresponding to the center pin 2 is: the intersection point of the extension line of the inner wall surface of the equal-diameter section of the spray pipe and the central bolt is taken as the throat part of the spray pipe at the corresponding position C of the central bolt; the relative distance between the spray pipe and the center bolt is as follows: the corresponding position C of the central bolt is in the direction parallel to the axis of the engine, and the distance between the intersection point B and the intersection point BC of the extension line of the inner wall surface of the spray pipe expansion section is the relative distance; the airflow deflection angle of the spray pipe is as follows: and an included angle between an extension line of the inner wall surface of the spray pipe expansion section and the direction of the axis of the engine.
It should be noted that, when the center pin moves along with the linear driving mechanism, the relative distance BC between the nozzle and the center pin changes, increases or decreases, and the throat area also changes adaptively, and for this embodiment, when the relative distance between the nozzle and the center pin increases, the throat area of the nozzle also increases, and since the nozzle outlet area remains unchanged, the nozzle expansion ratio decreases accordingly, and the mass flow rate of the propellant decreases, so as to provide the engine thrust.
The embodiment also provides a rocket engine, which comprises a throat-type expansion bias flow spray pipe with an adjustable center bolt position, wherein the head of a combustion chamber of the throat-type expansion bias flow spray pipe is connected with a rocket body of the rocket engine.
Specific working principle
The center bolt 2 is driven to move back and forth along the axis direction of the spray pipe 1 by the linear driving mechanism of the rocket engine, so that the throat position and throat area of the expansion bias flow spray pipe are changed, the flow direction of high-temperature fuel gas generated in the combustion chamber is deflected, and at the moment, in the working process of the engine, air flow deflected by the center bolt 2 is sprayed to the wall of the spray pipe 1, so that thrust is generated.
As shown in fig. 3, fig. 3 is a distribution of internal pressure of the nozzle under different pressures of the combustion chamber when the cyclic throat type expansion bias flow nozzle works at sea level in the embodiment, specifically, fig. 3a is a distribution of internal pressure of the nozzle under 3MPa of the pressure of the combustion chamber, fig. 3b is a distribution of internal pressure of the nozzle under 2.4MPa of the pressure of the combustion chamber, fig. 3c is a distribution of internal pressure of the nozzle under 1.8MPa of the pressure of the combustion chamber, and fig. 3d is a distribution of internal pressure of the nozzle under 1.2MPa of the pressure of the combustion chamber; when the pressure of the combustion chamber is reduced, the engine fuel gas is gradually attached to the wall surface under the action of atmospheric pressure, and no obvious flow separation occurs, so that the invention can realize the compensation of the flow change caused by the pressure change of the combustion chamber when the pressure of the combustion chamber is changed, and improve the working efficiency of the spray pipe.
As shown in FIG. 4, FIG. 4 is a graph showing the internal pressure distribution of the nozzle at different flying heights when the annular throat type expansion bias flow nozzle with the adjustable center bolt position works under the constant combustion chamber pressure, specifically, the embodiment takes the working heights of 0km, 4km and 15km as an example, wherein FIG. 4a is the internal pressure distribution of the nozzle in the embodiment when the flying height is positioned at the sea level (0 km), FIG. 4b is the internal pressure distribution of the nozzle in the embodiment when the flying height is 4km, and FIG. 4c is the internal pressure distribution of the nozzle in the embodiment when the flying height is 15km, and it can be seen from FIGS. 4 a-4 c that the internal pressure distribution of the nozzle in the embodiment is gradually full of the gas flowing along the wall when the flying height is increased, and the nozzle is always in the full expansion state, thereby delaying the moment when the nozzle enters under-expansion and improving the working efficiency of the nozzle.
As shown in fig. 5, fig. 5 is a schematic outline diagram of a bell-shaped spray pipe in comparison verification, from table 1 to table 5, table 1 is atmospheric pressure and temperature under various working conditions when the spray pipe is simulated; table 2 shows the thrust forces generated by the present invention and the bell-shaped nozzle at different heights at a combustion chamber pressure of 5 MPa; table 3 shows the thrust produced by the present invention at a height of 1km and at different mass flow rates than the bell nozzle; table 4 shows the thrust forces generated by the present invention at different combustor pressures and center pin positions; table 5 shows the thrust forces generated by the present invention at different propellant mass flow rates and center pin positions; tables 2 and 3 show that the present invention provides a certain thrust boost at different operating heights compared to bell pipes at the same combustor pressure; at the same working height and combustion chamber pressure, the invention outputs thrust force greater than the bell-shaped spray pipe and simultaneously the propellant consumption is smaller than the bell-shaped spray pipe, and tables 4 and 5 show that the invention can realize a variable thrust ratio of about 3.8 by only changing the position of the center bolt under the condition of given propellant mass flow rate; on the basis, the mass flow rate of the propellant is changed, so that the greater reasoning adjustment can be realized.
TABLE 1
TABLE 2
| Working conditions of | thrust/kN of the invention | Bell nozzle thrust/kN | Thrust boost amplitude |
| 1 | 3029.44 | 2873.07 | 5.442％ |
| 2 | 3032.68 | 2875.95 | 5.450％ |
| 3 | 3035.57 | 2879.31 | 5.427％ |
| 4 | 3039.14 | 2911.25 | 4.393％ |
| 5 | 3041.85 | 2945.96 | 3.255％ |
| 6 | 3043.71 | 2981.39 | 2.090％ |
TABLE 3 Table 3
TABLE 4 Table 4
| Throat area/(10) -2 m 2 ) | Output thrust/kN | Propellant mass flow rate/(kg/s) |
| 6.44 | 892.15 | 114.84 |
| 20.93 | 1018.49 | 380.57 |
| 35.42 | 1137.53 | 629.39 |
| 49.91 | 1250.39 | 875.01 |
| 64.4 | 1357.43 | 1114.38 |
TABLE 5
As shown in FIG. 6, FIG. 6 is a schematic view of nozzle plume when the nozzle is at 6MPa of combustion chamber pressure and the flight heights are respectively 0km,16.7km and 30 km; wherein FIG. 6a is a schematic view of the nozzle plume at a height of 0km, FIG. 6b is a schematic view of the nozzle plume at a height of 10km, FIG. 6c is a schematic view of the nozzle plume at a height of 16.7km, and FIG. 6d is a schematic view of the nozzle plume at a height of 30 km; therefore, when the working height is lower, the external plume is in a contracted state, the internal flow of the spray pipe still keeps clinging to the wall, and flow separation does not occur, so that the opportunity of the spray pipe entering the underexpansion mode is delayed, the spray pipe is in a complete expansion state in a long time, and the working efficiency of the spray pipe is improved.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (6)
1. A cyclic throat type expansion bias flow spray pipe with an adjustable center bolt position, which is characterized by comprising:
a spray pipe;
the central bolt is arranged in the spray pipe, the cylinder section of the central bolt penetrates out of the head part of the combustion chamber of the spray pipe and is used for being connected with the linear driving mechanism, and the central bolt is connected with the head part of the combustion chamber through the movable sealing ring.
2. The adjustable center pin position annular throat type expansion bias flow nozzle as claimed in claim 1, wherein the throat area of the nozzle is:
A t ＝r C x(sin 3 θ+2sinθ)
wherein A is t Representing the throat area of the nozzle;
x represents the relative distance between the spray pipe and the center bolt;
r C representing the distance from the throat of the spray pipe to the axis of the engine at the corresponding position C of the center bolt;
θ represents the airflow deflection angle of the nozzle.
3. The adjustable center pin position annular throat type expansion bias flow spray pipe as claimed in claim 2, wherein the throat of the spray pipe at the center pin corresponding position C is: and (3) taking the intersection point of the extension line of the inner wall surface of the constant diameter section of the spray pipe and the central bolt as the throat part of the spray pipe at the corresponding position C of the central bolt.
4. The adjustable center pin position annular throat type expansion bias flow nozzle as claimed in claim 2, wherein the relative distance between the nozzle and the center pin is: the distance between the corresponding position C of the central bolt and the intersection point B and BC of the extension line of the inner wall surface of the spray pipe expansion section in the direction parallel to the axis of the engine is the relative distance.
5. The adjustable center pin position annular throat type expansion bias flow spray pipe as claimed in claim 2, wherein the air flow deflection angle of the spray pipe is as follows: and an included angle between an extension line of the inner wall surface of the spray pipe expansion section and the direction of the axis of the engine.
6. A rocket engine, comprising: the cyclic throat expansion bias flow nozzle of any one of claims 1-5, wherein a combustion chamber head of the cyclic throat expansion bias flow nozzle is connected with a rocket body of a rocket engine, and a linear driving mechanism of the rocket engine is connected with a center bolt of the cyclic throat expansion bias flow nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311125607.8A CN117189422A (en) | 2023-09-02 | 2023-09-02 | Annular throat type expansion bias flow spray pipe with adjustable center bolt position and rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311125607.8A CN117189422A (en) | 2023-09-02 | 2023-09-02 | Annular throat type expansion bias flow spray pipe with adjustable center bolt position and rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117189422A true CN117189422A (en) | 2023-12-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311125607.8A Pending CN117189422A (en) | 2023-09-02 | 2023-09-02 | Annular throat type expansion bias flow spray pipe with adjustable center bolt position and rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117189422A (en) |
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2023
- 2023-09-02 CN CN202311125607.8A patent/CN117189422A/en active Pending
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