CN112610362A - Engine thrust control method and variable thrust engine - Google Patents
Engine thrust control method and variable thrust engine Download PDFInfo
- Publication number
- CN112610362A CN112610362A CN202011505233.9A CN202011505233A CN112610362A CN 112610362 A CN112610362 A CN 112610362A CN 202011505233 A CN202011505233 A CN 202011505233A CN 112610362 A CN112610362 A CN 112610362A
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- Prior art keywords
- engine
- gas
- thrust
- laval nozzle
- throat part
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Classifications
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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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
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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
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention discloses an engine thrust control method and a variable thrust engine, wherein the effective flow area of gas in a throat part of a thrust chamber is indirectly changed by adjusting and changing the throat part flow coefficient of the gas in the thrust chamber at the throat part of the thrust chamber by using gas, and the variable thrust engine capable of changing thrust is designed by the method. The invention has simple and reliable design principle and reasonable structure, can effectively change the flow coefficient of the throat part of the thrust chamber of the rocket engine and change the effective flow area of the fuel gas in the throat part of the thrust chamber, thereby achieving the purpose of changing the thrust of the engine.
Description
Technical Field
The invention relates to a thrust control method of an engine and a thrust chamber structure, in particular to a throat part of a thrust chamber, which can be used for manned, lunar exploration, kinetic energy weapons and other aspects and belongs to the technical field of aerospace power.
Background
The thrust of the rocket engine is shown as (formula 1)
F＝Pc*At*CF(formula 1)
Wherein: f is engine thrust; pcEngine room pressure, positively correlated with engine flow; a. thetIs the flow area of the engine throat; cFAnd the thrust coefficient of the spray pipe.
According to the formula (1), the variable thrust rocket engine has the following ways:
(1) changing engine room pressure by adjusting engine flow;
(2) the effective flow area of the fuel gas at the throat part is adjusted;
(3) the nozzle expansion ratio is adjusted to change the thrust coefficient.
The methods (1) and (2) can both realize the purpose of continuously adjusting the thrust in a large range, and (3) can only realize step-type adjustment of the thrust of the engine due to the influence of the envelope size, the weight and the like of the engine.
The continuously variable thrust regulating engine which is applied in practice at present realizes variable thrust regulation by regulating the flow of the engine. Adjusting thrust by adjusting engine flow has several problems:
1) the adjustment of the linearity difference is difficult to achieve accurate control;
2) the combustion efficiency of the engine is easily affected, and the performance of the engine is reduced.
And the thrust is adjusted by changing the effective flow area of the gas throat of the engine, so that high-precision adjustment is easy to realize and atomization and combustion in the combustion chamber are not influenced. In the variable thrust engine of control throat area of current, all adopt the pintle formula mode of regulation, but throat temperature is high, and receives high-speed gas to erode, and throat regulation pintle receives gas to erode and erode easily, and the structure is complicated, and difficult regulation control, current material is difficult to satisfy the requirement that reaches accurate control under so abominable condition.
Disclosure of Invention
In order to solve the above problems, the present invention aims to provide an engine thrust control method and a variable thrust engine, which achieve the purpose of indirectly controlling the engine thrust.
In order to achieve the purpose, the invention adopts the following technical scheme:
the engine comprises a Laval nozzle, an air film is formed at the throat position of the Laval nozzle, the axial effective flow cross section area of fuel gas at the throat position is changed by controlling the thickness of the air film, and the thrust of the engine is further controlled.
Preferably, the gas film is a layer of annular gas film tightly attached to the surface of the inner wall of the throat part of the laval nozzle.
Preferably, the thickness of the gas film is adjusted by controlling the magnitude of the gas pressure.
Preferably, the gas forming the gas film has a temperature lower than the temperature of the combustion gas at the throat of the laval nozzle.
A variable thrust engine comprises a Laval nozzle, and a gas injection hole is formed in the throat part of the Laval nozzle.
Preferably, the gas injection holes are tangential to the inner wall surface of the throat part of the laval nozzle. It should be noted that, since the gas injection hole has an inner diameter, the tangency is to approximate the gas injection hole to a straight line tangent to the inner contour line of the throat section, when the inner diameter of the gas injection hole is larger, it can be understood that the surface of the gas injection hole includes a tangent line tangent to the throat section of the laval nozzle, and the axis of the gas injection hole is parallel to the tangent line, which aims to eject the gas flow injected from the gas injection hole along the tangent direction of the throat section, that is, the gas flow injected from the gas injection hole forms a circular flow gas film along the inner wall of the throat region.
Preferably, the gas injection holes are multiple, and the multiple gas injection holes are distributed along a ring shape in the same plane, and the plane is perpendicular to the axis of the Laval nozzle.
Preferably, the gas injection holes are distributed in different planes, the gas injection holes in the same plane are distributed along a ring shape, and the planes are perpendicular to the axis of the Laval nozzle. The gas jet holes in different planes can form gas films with different thicknesses, the effective sectional areas of the gas films with different thicknesses are adjusted at different positions along the axial direction of the Laval nozzle, a multistage combined type regulation and control structure is formed, for example, when two gas jet hole planes exist, two-stage adjusting sections are formed, the adjusting precision is higher, and the adjusting mode is more flexible.
Preferably, the number of gas injection holes or the hole diameter is different in different planes. By introducing the number and the aperture parameters, the adjustment mode is increased, and the mode of controlling the thickness of the air film by pressure singly is avoided.
Preferably, the variable thrust engine further comprises a gas communication cavity, and the gas communication cavity is located in the throat part of the laval nozzle and is communicated with the plurality of gas injection holes in the same plane. When a plurality of gas communicating cavities exist, different communicating cavities can be connected with gas sources with different temperatures.
The invention relates to a method for adjusting the continuous variable thrust of an engine, which indirectly changes the effective flow area of the throat part of gas in a thrust chamber by adjusting and changing the flow coefficient of the throat part of the thrust chamber by using gas at the throat part of the thrust chamber.
Compared with the prior art, the invention leads gas to generate tangential circulation in the throat area, thereby changing the flow coefficient of the gas at the throat part at the upstream of the throat part, namely the effective axial flow sectional area of the gas at the throat part, and further achieving the aim of indirectly controlling the thrust of the engine.
Drawings
FIG. 1 is a schematic view of a Laval nozzle of the present invention;
FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;
FIG. 3 is a cross-sectional view taken along line B-B of FIG. 2;
FIG. 4 is a perspective view of the Laval nozzle of the present invention;
FIG. 5 is an axial plan sectional view of FIG. 4;
fig. 6 is a radial plan sectional view of fig. 4.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
The method for controlling the thrust of the engine comprises the following steps: the effective flow cross section area of the throat part of the thrust chamber is indirectly changed by adjusting and changing the gas flow coefficient of the throat part of the thrust chamber by using gas.
As shown in fig. 1 to 6, the present invention is a simple and adjustable variable thrust engine structure. A circle of cold air adjusting tangential holes 2 are arranged at the throat part of the Laval nozzle 1 (in the sectional plane of the drawing, a generatrix on the cylindrical surface of the cylindrical hole is tangent to the inner wall surface of the throat part, and the axis of the gas injection hole is parallel to the generatrix, so that the tangential holes 2 are perpendicular to the radius R in the drawing 3, the axis of the gas injection hole is basically perpendicular to the section radius of the throat part of the Laval nozzle (the radius refers to the radius line at the intersection point of the axis of the gas injection hole and the section line of the throat part, and is not the radius R), the distance between the axis of the injection hole and the throat part axis of the nozzle is spatially larger than 0 and smaller than or equal to the section radius of the throat part (when the inner diameter of the injection hole is small enough, the distance is approximately equal to the section radius of the throat part), the tangential injection holes are formed in. Due to the blocking of the annular gas film, the effective sectional area of the gas flowing axially at the throat is reduced. The pressure of the gas entering the throat part from the throat part tangential hole 2 is increased, the formed gas film is thickened, the axial flow effective sectional area of the throat part is reduced, and the thrust of the engine is reduced; on the contrary, the pressure of the introduced gas is reduced, the formed gas film is thinned, the axial flow effective sectional area of the throat part is increased, and the thrust of the engine is increased. The tangential air flow of throat that lets in can also be effectual carries out thermal protection to engine throat and spray tube, improves the reliability of engine work.
As another option, two circles of cold air adjusting tangential holes 2 are arranged at the throat part of the Laval nozzle 1, the number, the pore diameter and the temperature of the introduced gas of the two circles of cold air adjusting tangential holes 2 are different, two gas films with different properties are formed, and the axial effective cross-sectional area of the throat part for gas circulation is controlled by changing the pressure of the tangential holes 2 in different circles.
Claims (10)
1. A thrust control method for an engine comprising a laval nozzle (1), characterized in that: an air film is formed at the throat part of the Laval nozzle (1), the axial effective flow cross section area of the fuel gas at the throat part is changed by controlling the thickness of the air film, and the thrust of the engine is further controlled.
2. The engine thrust control method according to claim 1, characterized in that: the air film is a layer of annular air film which is tightly attached to the surface of the inner wall of the throat part of the Laval nozzle (1).
3. The engine thrust control method according to claim 1, characterized in that: the thickness of the gas film is adjusted by controlling the magnitude of the gas pressure.
4. The engine thrust control method according to claim 1, characterized in that: the gas temperature forming the gas film is lower than the temperature of the combustion gas at the throat position of the Laval nozzle (1).
5. A variable thrust engine comprising a laval nozzle (1), characterized in that: the throat part of the Laval nozzle (1) is provided with a gas jet hole.
6. The variable thrust engine of claim 5, wherein: the gas jet hole is tangent to the inner wall surface of the throat part of the Laval nozzle (1).
7. The variable thrust engine of claim 5, wherein: the gas injection holes are distributed in the same plane and along the ring shape, and the plane is perpendicular to the axis of the Laval nozzle (1).
8. The variable thrust engine of claim 5, wherein: the gas injection holes are distributed in different planes, the gas injection holes in the same plane are distributed along the ring shape, and the planes are perpendicular to the axis of the Laval nozzle (1).
9. A variable thrust engine according to claim 8, wherein: the number of gas injection holes or the hole diameter is different in different planes.
10. A variable thrust engine according to claim 7 or 8, wherein: the gas communicating cavity is positioned at the throat part of the Laval nozzle (1) and is communicated with the plurality of gas spraying holes in the same plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011505233.9A CN112610362A (en) | 2020-12-18 | 2020-12-18 | Engine thrust control method and variable thrust engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011505233.9A CN112610362A (en) | 2020-12-18 | 2020-12-18 | Engine thrust control method and variable thrust engine |
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| Publication Number | Publication Date |
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| CN112610362A true CN112610362A (en) | 2021-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011505233.9A Pending CN112610362A (en) | 2020-12-18 | 2020-12-18 | Engine thrust control method and variable thrust engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113028453A (en) * | 2021-04-09 | 2021-06-25 | 西北工业大学 | Rotary detonation combustion chamber with adjustable combustion chamber width |
| CN115434829A (en) * | 2022-10-17 | 2022-12-06 | 西安探火航天技术有限公司 | Reusable rocket engine nozzle assembly with variable expansion ratio |
| CN117839888A (en) * | 2024-03-05 | 2024-04-09 | 山东大学 | Ejector with adjustable throat opening |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3925982A (en) * | 1973-09-11 | 1975-12-16 | Martin Marietta Corp | Fluid-dynamic shock ring for controlled flow separation in a rocket engine exhaust nozzle |
| US4707981A (en) * | 1986-01-27 | 1987-11-24 | Rockwell International Corporation | Variable expansion ratio reaction engine |
| US20050284128A1 (en) * | 2004-06-29 | 2005-12-29 | Anderson Morris G | Rocket motor nozzle throat area control system and method |
| US7793504B2 (en) * | 2006-05-04 | 2010-09-14 | Rolls-Royce Corporation | Nozzle with an adjustable throat |
| CN102536512A (en) * | 2010-12-14 | 2012-07-04 | 波音公司 | Method and apparatus for variable exhaust nozzle exit area |
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| CN104712462A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Secondary fluid jet thrust adjusting device with changeable jet pipe |
| CN106762218A (en) * | 2017-01-05 | 2017-05-31 | 南京工业职业技术学院 | A kind of method and jet pipe for improving pulse detonation engine thrust coefficient |
| CN210264953U (en) * | 2019-07-19 | 2020-04-07 | 吉林进取空间科技有限公司 | Outer wall structure of thrust chamber body part of liquid rocket engine |
-
2020
- 2020-12-18 CN CN202011505233.9A patent/CN112610362A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3925982A (en) * | 1973-09-11 | 1975-12-16 | Martin Marietta Corp | Fluid-dynamic shock ring for controlled flow separation in a rocket engine exhaust nozzle |
| US4707981A (en) * | 1986-01-27 | 1987-11-24 | Rockwell International Corporation | Variable expansion ratio reaction engine |
| US20050284128A1 (en) * | 2004-06-29 | 2005-12-29 | Anderson Morris G | Rocket motor nozzle throat area control system and method |
| US7793504B2 (en) * | 2006-05-04 | 2010-09-14 | Rolls-Royce Corporation | Nozzle with an adjustable throat |
| CN102536512A (en) * | 2010-12-14 | 2012-07-04 | 波音公司 | Method and apparatus for variable exhaust nozzle exit area |
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| CN104712462A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Secondary fluid jet thrust adjusting device with changeable jet pipe |
| CN106762218A (en) * | 2017-01-05 | 2017-05-31 | 南京工业职业技术学院 | A kind of method and jet pipe for improving pulse detonation engine thrust coefficient |
| CN210264953U (en) * | 2019-07-19 | 2020-04-07 | 吉林进取空间科技有限公司 | Outer wall structure of thrust chamber body part of liquid rocket engine |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113028453A (en) * | 2021-04-09 | 2021-06-25 | 西北工业大学 | Rotary detonation combustion chamber with adjustable combustion chamber width |
| CN113028453B (en) * | 2021-04-09 | 2022-07-01 | 西北工业大学 | Rotary detonation combustion chamber with adjustable combustion chamber width |
| CN115434829A (en) * | 2022-10-17 | 2022-12-06 | 西安探火航天技术有限公司 | Reusable rocket engine nozzle assembly with variable expansion ratio |
| CN117839888A (en) * | 2024-03-05 | 2024-04-09 | 山东大学 | Ejector with adjustable throat opening |
| CN117839888B (en) * | 2024-03-05 | 2024-05-07 | 山东大学 | Ejector with adjustable throat opening |
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Application publication date: 20210406 |
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