CN116398324A - Acoustic resonator suitable for liquid rocket engine and liquid rocket engine - Google Patents
Acoustic resonator suitable for liquid rocket engine and liquid rocket engine Download PDFInfo
- Publication number
- CN116398324A CN116398324A CN202211632667.4A CN202211632667A CN116398324A CN 116398324 A CN116398324 A CN 116398324A CN 202211632667 A CN202211632667 A CN 202211632667A CN 116398324 A CN116398324 A CN 116398324A
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- acoustic resonator
- liquid rocket
- rocket engine
- inlet
- resonant
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- 239000007788 liquid Substances 0.000 title claims abstract description 37
- 239000007921 spray Substances 0.000 claims abstract description 18
- 230000000694 effects Effects 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 9
- 239000002737 fuel gas Substances 0.000 claims description 8
- 238000000576 coating method Methods 0.000 claims description 5
- 238000012937 correction Methods 0.000 claims description 4
- 230000003647 oxidation Effects 0.000 claims description 4
- 238000007254 oxidation reaction Methods 0.000 claims description 4
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 abstract description 21
- 210000001503 joint Anatomy 0.000 abstract description 5
- 238000013016 damping Methods 0.000 abstract description 3
- 238000002347 injection Methods 0.000 abstract description 2
- 239000007924 injection Substances 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 description 8
- 238000013461 design Methods 0.000 description 4
- 238000002679 ablation Methods 0.000 description 3
- 230000010355 oscillation Effects 0.000 description 3
- 239000003380 propellant Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000003870 refractory metal Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Images
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
- F02K9/60—Constructional parts; Details not otherwise provided for
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention provides an acoustic resonator suitable for a liquid rocket engine and the liquid rocket engine, wherein the acoustic resonator is arranged at the joint of an engine spray pipe and an injector, and comprises a plurality of inlet holes 1 and resonant cavities 2 which are arranged along the circumferential direction. The invention has simple structure and convenient operation, utilizes the butt joint of the engine spray pipe and the injector, does not need to occupy extra injector space like arranging the acoustic cavity, can reduce the diameter of the combustion chamber, improve the compactness of the engine structure, or can arrange more injection units on the injector to improve the performance under the same diameter of the combustion chamber, the resonant cavity is arranged in the butt joint surface of the spray pipe with adjustable size, and can maximize the volume of the resonant cavity, improve the damping effect and avoid the limitation of the opening area when the acoustic cavity is designed, besides the volume occupied by the ribs.
Description
Technical Field
The invention relates to the technical field of liquid rocket engines, in particular to an acoustic resonator suitable for a liquid rocket engine and the liquid rocket engine.
Background
The liquid rocket engine is a chemical rocket engine using liquid propellant as energy and working medium. The liquid propellant burns or decomposes in the combustion chamber of the engine to generate high-temperature and high-pressure fuel gas which is sprayed out through the supersonic jet pipe, so that thrust required by the rocket and the spacecraft is provided.
When the combustion process of the liquid propellant in the combustion chamber is coupled with the fluid dynamics in the engine system, combustion oscillations are induced, accompanied by periodic oscillations in gas pressure, temperature and velocity, a phenomenon known as combustion instability.
Since combustion instability, particularly high frequency combustion instability, can have catastrophic consequences such as engine burnout, damage, etc., corresponding measures must be taken to suppress combustion instability during the design of medium and large liquid rocket engines, and the primary measures to suppress high frequency combustion instability include baffles and acoustic resonators.
The acoustic cavity is a 1/4 wavelength acoustic resonator, which is an annular groove or discrete hole arranged at the joint corner of the injector and the spray pipe, and can be divided into an axial direction and a radial direction according to the direction of the groove or the hole. The acoustic resonator represented by the acoustic cavity is widely applied to the liquid rocket engine due to the simple structure, easy processing and no need of cooling. Although the acoustic cavity has the advantages, in the practical process, the problems of structural bulkiness, easy ablation, poor damping effect and the like are solved.
Patent publication CN101949541a discloses an injector with an integrated resonator. Additionally, the present disclosure relates to a system, which may include a turbine engine. The turbine engine may include a fuel nozzle. The fuel nozzle may include an air passage. The fuel nozzle may also include a fuel passage such that the fuel nozzle communicates with a combustion zone of the turbine engine. Further, the fuel nozzle may include a resonator. The resonator is disposed in the fuel nozzle proximate the combustion zone. However, the resonator is arranged in the fuel nozzle, occupies a large space, occupies additional nozzle space, and is not compact in structure.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an acoustic resonator suitable for a liquid rocket engine and the liquid rocket engine.
According to the acoustic resonator suitable for the liquid rocket engine, which is provided by the invention, the acoustic resonator is arranged at the joint of the engine spray pipe and the injector, the acoustic resonator comprises a plurality of inlet holes and a plurality of resonant cavities which are arranged along the circumferential direction, the adjacent resonant cavities are separated by ribs, and fuel gas in the engine spray pipe enters and exits the resonant cavities through the inlet holes.
Preferably, the structural parameters of the inlet hole and the resonant cavity satisfy the following conditions:
wherein A and L are the area and depth of the inlet aperture respectively; v is the volume of the resonator, λ is an empirical correction factor taking into account the inlet effect, f is the resonant frequency of the acoustic resonator, c is the local sound velocity in the acoustic resonator.
Preferably, the lambda is in the range of 1.05 to 1.90.
Preferably, the plurality of inlet holes are evenly distributed in the circumferential direction.
Preferably, the plurality of resonant cavities are uniformly distributed in the circumferential direction.
Preferably, the resonant cavity is disposed outside the inlet aperture.
Preferably, the number of the inlet holes and the number of the resonant cavities are 12 and are arranged in a one-to-one correspondence.
Preferably, the inlet hole and the inner surface of the resonant cavity are coated with high-temperature oxidation resistant coatings.
Preferably, the cross-sectional shapes of the inlet aperture and the resonant cavity include rectangular, fan-shaped and annular.
According to the liquid rocket engine provided by the invention, the acoustic resonator suitable for the liquid rocket engine is adopted, and the opening direction of the inlet hole is perpendicular to the gas backflow direction.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention has simple structure and convenient operation, utilizes the butt joint of the engine spray pipe and the injector, and does not need to occupy extra injector space like arranging an acoustic cavity, thereby reducing the diameter of a combustion chamber and improving the compactness of the engine structure, or arranging more injection units on the injector under the same diameter of the combustion chamber so as to improve the performance.
2. The invention adopts the technical means that the opening direction of the inlet hole is perpendicular to the gas backflow direction, so that the acoustic resonator has excellent high temperature resistance, and the problem of ablation of the acoustic cavity caused by gas backflow is avoided.
3. The invention adopts the technical means that the resonant cavity is arranged in the butt joint surface of the spray pipe with adjustable size, and can maximize the volume of the resonant cavity, improve the damping effect and avoid the limitation of the opening area during the design of the acoustic cavity besides the volume occupied by the ribs.
4. The invention adopts the technical means of coating the inner surface of the acoustic resonator with the high-temperature oxidation resistant coating, improves the high-temperature resistant capability, and reduces the heat transfer from the spray pipe and the fuel gas to the injector.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic side view of the present invention;
fig. 2 is a schematic structural view of the present invention when used in a liquid rocket engine.
The figure shows:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
The invention discloses an acoustic resonator suitable for a liquid rocket engine and the liquid rocket engine, wherein the acoustic resonator consists of a plurality of inlet Kong Hexie vibrating cavities arranged on an engine spray pipe, and pressure waves with specific frequency or close to the specific frequency are dissipated in the resonator through an optimal design to maintain stable combustion of the engine.
According to the acoustic resonator suitable for the liquid rocket engine, as shown in fig. 1-2, the acoustic resonator is arranged at the joint of an engine spray pipe and an injector, the acoustic resonator comprises a plurality of inlet holes 1 and a plurality of resonant cavities 2 which are arranged along the circumferential direction, adjacent resonant cavities 2 are separated by ribs, and fuel gas in the engine spray pipe enters and exits the resonant cavities 2 through the inlet holes 1.
The structural parameters of the inlet hole 1 and the resonant cavity 2 are as follows:
wherein A and L are the area and depth of the inlet aperture 1 respectively; v is the volume of the resonator 2, λ is an empirical correction factor taking account of the inlet effect, f is the resonance frequency of the acoustic resonator, c is the local sound velocity in the acoustic resonator. The lambda reference range is 1.05-1.90, and because of the high-frequency combustion instability, various array types and frequencies exist, various parameter combinations (parameters such as the area, the depth and the volume of the resonant cavity 2 of the inlet hole are adjusted) can be adopted, or a plurality of groups of acoustic resonators are designed, so that the inhibition effect is improved.
The plurality of inlet holes 1 are uniformly distributed in the circumferential direction. The plurality of resonant cavities 2 are uniformly distributed in the circumferential direction. The resonant cavity 2 is arranged outside the inlet aperture 1. The number of the inlet holes 1 and the number of the resonant cavities 2 are 12 and are arranged in one-to-one correspondence. The inner surfaces of the inlet hole 1 and the resonant cavity 2 are coated with high-temperature oxidation resistant coatings, so that the high-temperature resistance is improved, and the heat transfer from the spray pipe and the fuel gas to the injector is reduced. The cross-sectional shapes of the inlet hole 1 and the resonant cavity 2 comprise rectangular, fan-shaped and annular shapes, the design is flexible, and the shape combination is not limited.
According to the liquid rocket engine provided by the invention, the acoustic resonator suitable for the liquid rocket engine is adopted, and the opening direction of the inlet hole 1 is perpendicular to the gas backflow direction. Because the spray pipe uses refractory metal as a raw material, and the opening direction of the inlet hole 1 is perpendicular to the gas backflow direction, the acoustic resonator has excellent high-temperature resistance, and the problem of ablation of the acoustic cavity caused by gas backflow does not exist.
The working principle of the invention is as follows:
on a spray pipe made of refractory metal, an inlet hole 1 and a resonant cavity 2 are processed near the butt joint position with an injector, and the inlet hole 1 adopts a discrete form to form a gas inlet and outlet channel; each resonant cavity 2 is separated by ribs to prevent fuel gas from rotating in the cavity, after the injector is effectively connected with the spray pipe, a semi-closed cavity space is formed at the joint, namely an acoustic resonator, the fuel gas enters and exits the resonant cavity 2 through the inlet hole 1 to dissipate energy in back and forth oscillation, and when the resonant frequency of the acoustic resonator is similar to a certain vibration mode frequency of unstable high-frequency combustion of an engine, the mode can be restrained, so that the combustion tends to be stable.
Example 1
As shown in fig. 1, in this embodiment, on the interface of the nozzle pipe with the injector, there are machined inlet holes 1 and cavities 2, and the inlet holes 1 and cavities 2 are uniformly arranged in the circumferential direction, each of which has 12.
The first-order tangential vibration mode of the engine used in this embodiment has a frequency of 1.49×10 4 Hz, the average sound velocity in the combustion chamber is 1140.3m/s. For this purpose, an acoustic resonator structure is designed with the following parameters:
taking the empirical correction factor of the inlet effect into account to 1.25, taking the local sound velocity in the resonator to be 65% of the average sound velocity in the combustion chamber, i.e. 741.2m/s, the inlet orifice 1 adopts a rectangular shapeThe length and width of the hole are 2mm multiplied by 2mm, the depth of the hole is 2mm, the inlet and outlet of the hole keeps sharp edges, the cross section of the resonant cavity 2 is a fan ring, the inner diameter and the outer diameter are phi 42 and phi 51 respectively, the groove depth is 2.1mm, the width of the rib separating each resonant cavity is 1.6mm, and therefore the volume of a single resonant cavity is 99.9mm 3 Through the combination of the parameters, the acoustic resonator can restrain the first-order tangential vibration mode of the engine.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. The acoustic resonator is suitable for a liquid rocket engine, and is characterized in that the acoustic resonator is arranged at the joint of an engine spray pipe and an injector, the acoustic resonator comprises a plurality of inlet holes (1) and a plurality of resonant cavities (2) which are arranged along the circumferential direction, the adjacent resonant cavities (2) are separated by ribs, and fuel gas in the engine spray pipe enters and exits the resonant cavities (2) through the inlet holes (1).
2. Acoustic resonator suitable for a liquid rocket engine according to claim 1, characterized in that the structural parameters of the inlet aperture (1) and the resonant cavity (2) are such that:
wherein A and L are the area and depth of the inlet hole (1) respectively; v is the volume of the resonant cavity (2), lambda is an empirical correction factor taking into account the inlet effect, f is the resonant frequency of the acoustic resonator, and c is the local sound velocity in the acoustic resonator.
3. An acoustic resonator suitable for use in a liquid rocket engine according to claim 2, wherein the λ is in the range of 1.05-1.90.
4. Acoustic resonator suitable for a liquid rocket engine according to claim 1, characterized in that the plurality of inlet holes (1) are uniformly distributed in the circumferential direction.
5. Acoustic resonator adapted for use in a liquid rocket engine according to claim 1, characterized in that the plurality of resonant cavities (2) are uniformly distributed in the circumferential direction.
6. Acoustic resonator adapted for use in a liquid rocket engine according to claim 1, characterized in that the resonant cavity (2) is arranged outside the inlet opening (1).
7. Acoustic resonator suitable for liquid rocket engines according to claim 1, characterized in that the number of inlet holes (1) and resonant cavities (2) is 12 and arranged in a one-to-one correspondence.
8. Acoustic resonator suitable for liquid rocket engines according to claim 1, characterized in that both the inlet aperture (1) and the inner surface of the resonant cavity (2) are coated with a high temperature oxidation resistant coating.
9. Acoustic resonator adapted for use in a liquid rocket engine according to claim 1, characterized in that the cross-sectional shape of the inlet aperture (1) and the resonant cavity (2) comprises rectangular, fan-shaped and ring-shaped.
10. A liquid rocket engine, characterized in that an acoustic resonator according to any one of claims 1-9 is used, which is suitable for a liquid rocket engine, the opening direction of the inlet opening (1) being perpendicular to the gas return direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211632667.4A CN116398324A (en) | 2022-12-19 | 2022-12-19 | Acoustic resonator suitable for liquid rocket engine and liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211632667.4A CN116398324A (en) | 2022-12-19 | 2022-12-19 | Acoustic resonator suitable for liquid rocket engine and liquid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116398324A true CN116398324A (en) | 2023-07-07 |
Family
ID=87011128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211632667.4A Pending CN116398324A (en) | 2022-12-19 | 2022-12-19 | Acoustic resonator suitable for liquid rocket engine and liquid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116398324A (en) |
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2022
- 2022-12-19 CN CN202211632667.4A patent/CN116398324A/en active Pending
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