CN116816541A - Rocket engine thrust chamber using Hartmann whistle nozzle - Google Patents
Rocket engine thrust chamber using Hartmann whistle nozzle Download PDFInfo
- Publication number
- CN116816541A CN116816541A CN202310897935.3A CN202310897935A CN116816541A CN 116816541 A CN116816541 A CN 116816541A CN 202310897935 A CN202310897935 A CN 202310897935A CN 116816541 A CN116816541 A CN 116816541A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- liquid
- gas
- hartmann
- hartmann whistle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000007788 liquid Substances 0.000 claims abstract description 123
- 239000000446 fuel Substances 0.000 claims abstract description 18
- 239000007800 oxidant agent Substances 0.000 claims abstract description 15
- 238000002485 combustion reaction Methods 0.000 claims abstract description 14
- 230000001590 oxidative effect Effects 0.000 claims abstract description 13
- 239000007921 spray Substances 0.000 claims abstract description 11
- 239000003380 propellant Substances 0.000 abstract description 27
- 238000000889 atomisation Methods 0.000 abstract description 20
- 230000000694 effects Effects 0.000 abstract description 9
- 230000009286 beneficial effect Effects 0.000 abstract description 5
- 238000001816 cooling Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000001879 gelation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000002002 slurry Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Landscapes
- Nozzles (AREA)
Abstract
The invention relates to the technical field of rocket engines, and discloses a rocket engine thrust chamber using a Hartmann whistle nozzle, which comprises a thrust chamber body part and a spray pipe part, wherein the thrust chamber body part comprises an outer shell, and the top end of the outer shell is connected with a gaseous oxidant inlet and a liquid fuel inlet; the upper part in the inner cavity of the outer shell is provided with a Hartmann whistle nozzle, and the lower part of the inner cavity is provided with a combustion chamber; the spray pipe part is a Laval spray pipe; the Hartmann whistle nozzle consists of a gas-liquid coaxial nozzle and a resonant cavity positioned below the gas-liquid coaxial nozzle, wherein the gas-liquid coaxial nozzle consists of a gas direct-current nozzle at the center and a liquid circumferential seam nozzle with a coaxial outer ring. The application of the Hartmann whistle nozzle in the invention effectively improves the atomization effect of the gel propellant or the Newtonian liquid propellant, improves the combustion efficiency in the thrust chamber, and improves the specific impact performance of the whole rocket engine; meanwhile, the application of the Hartmann whistle nozzle increases the spray cone angle, which is beneficial to the wall surface cooling of the thrust chamber.
Description
Technical Field
The invention relates to the technical field of rocket engines, in particular to a rocket engine thrust chamber using a Hartmann whistle nozzle.
Background
The gel propellant combines the advantages of high specific impulse, high controllability, stable and easy storage of the solid propellant and strong rapid maneuverability of the solid propellant, so that the gelation of the liquid propellant is one of the important development directions at present and is a new trend of the development of the liquid propellant.
The gel propellant exhibits a viscoelastic solid during storage, undergoes a viscosity drop under shear stress during supply to the rocket engine thrust chamber, and eventually atomizes into a liquid for combustion. Due to the high zero shear viscosity and special rheological property, the gel propellant tends to have poor atomization quality when a conventional atomization nozzle is used, so that the combustion efficiency of a rocket engine thrust chamber is affected, such as a direct-current injector applicable to the gel propellant, a gel propellant injector and an engine thrust chamber, as well as an injector and an injection method as disclosed in CN201963418U, as well as an injector and an injection method as disclosed in CN 212359969U.
There are some nozzle improvements and applications for gel propellants, such as: CN113882967B announces a ramjet system using solid particle gel fuel, but with a smaller nozzle flow, which is only applicable to ramjet engines; CN114017204 discloses a ramjet system using energetic slurry fuel, but with a single-phase nozzle, which is not suitable for rocket engines having two components, fuel and oxidant; CN112177802a discloses a rocket engine preheating self-striking injector suitable for gel fuel, but its nozzle structure is complicated and is only suitable for the type of propellant with reduced temperature rise viscosity.
Since the beginning of the 90 s of the last century, a new type of ultrasonic atomization technology has been receiving attention, such as the hydrodynamic ultrasonic atomizer disclosed in CN200977496Y and the hydrodynamic ultrasonic generator disclosed in CN204060592U for reducing the viscosity of extra heavy oil. The Hartmann whistle is a typical and effective hydrodynamic ultrasonic atomizing nozzle, has the characteristics of simple structure, small volume and impact resistance, and is suitable for working under the condition that the combustion chamber of a rocket engine is relatively bad. The ultrasonic wave generated by the device has high frequency and high intensity, and can effectively atomize the liquid with larger viscosity, so the gel propellant has a certain application prospect in the aspect of atomization.
Disclosure of Invention
The invention aims to provide a rocket engine thrust chamber using a Hartmann whistle nozzle, which can improve the atomization effect of gel propellant and Newton liquid propellant, further improve the combustion efficiency and specific impulse of the engine, and has the following specific technical scheme:
a rocket engine thrust chamber using a Hartmann whistle nozzle, comprising a thrust chamber body part and a jet pipe part, wherein the thrust chamber body part comprises an outer shell coaxially connected with the upper part of the jet pipe part, and the top end of the outer shell is connected with a gaseous oxidant inlet and a liquid fuel inlet; the upper part in the inner cavity of the outer shell is provided with a Hartmann whistle nozzle, and the lower part of the inner cavity is a combustion chamber; the spray pipe part is a Laval spray pipe, and the combustion chamber is communicated with the Laval spray pipe; the Hartmann whistle nozzle consists of a gas-liquid coaxial nozzle and a resonant cavity positioned below the gas-liquid coaxial nozzle, wherein the gas-liquid coaxial nozzle consists of a gas direct-current nozzle at the center and a liquid circular seam nozzle with a coaxial outer ring;
the gas direct-current nozzle comprises a gas path shell, wherein an opening at the upper part of a gas direct-current channel in the gas path shell is a Hartmann whistle nozzle gas inlet communicated with the gaseous oxidant inlet, a flow director is arranged in the gas direct-current channel, a circle of through holes communicated up and down are uniformly distributed on the flow director, the center of the flow director is fixedly connected with the upper end of a whistle rod, and the lower end of the whistle rod penetrates out of the opening at the lower part of the gas direct-current channel and is fixedly connected with the bottom of an inner cavity of the resonant cavity below; the lower opening of the gas direct-current channel is a Hartmann whistle nozzle gas nozzle, and a circular seam gas passage is formed between the Hartmann whistle nozzle gas nozzle and the whistle rod;
the liquid circumferential-joint nozzle comprises a liquid path shell coaxially fixed outside the gas path shell, a Hartmann whistle nozzle liquid inlet communicated with the liquid fuel inlet is formed in the liquid path shell, a Hartmann whistle nozzle liquid nozzle spout is formed in the lower portion of the liquid path shell, a circumferential-joint liquid passage is formed between the Hartmann whistle nozzle liquid spout and the outer wall of the gas path shell, and the Hartmann whistle nozzle liquid spout is gradually inclined from top to bottom in a direction close to the central axis of the gas path shell.
In the invention, oxidant gas firstly enters the gas inlet of the Hartmann whistle nozzle, is sprayed out from the gas nozzle of the Hartmann whistle nozzle through the flow director, and is crashed into the resonant cavity to generate a strong sound field. The liquid propellant enters the outer annular channel of the nozzle from the liquid inlet of the Hartmann whistle nozzle from the fuel cavity, and is sprayed out from the liquid outlet of the Hartmann whistle nozzle to form a circle of liquid film surrounding the resonant cavity. The strong sound wave excites capillary wave on the surface of the liquid film, and the capillary wave is unstably broken into tiny liquid drops, so that the atomization process is completed.
Preferably, a ring-shaped supporting seat for supporting the lower surface of the liquid path shell is arranged on the inner cavity wall of the outer shell, and the resonant cavity is positioned below the ring-shaped supporting seat.
Preferably, 8 circles of through holes with the diameter of 2.5mm are uniformly distributed on the flow director.
Preferably, the diameter of the gas nozzle of the Hartmann whistle nozzle is 7mm, the outer diameter of the whistle rod is 5-6 mm, and the circumferential width of the circumferential gas passage is 0.5-1 mm.
Preferably, the Hartmann whistle nozzle liquid inlet is 6 through holes with the diameter of 30mm which are formed in the liquid path shell at equal intervals along the circumferential direction.
Preferably, the included angle between the liquid nozzle of the Hartmann whistle nozzle and the bottom plane of the liquid circumferential-seam nozzle is 45-75 degrees.
Preferably, the diameter of the liquid nozzle of the Hartmann whistle nozzle is 11mm, the diameter of the outer ring at the bottom of the air path shell is 11.6-12.2 mm, and the width of the circular seam liquid passage is 0.3-0.6 mm.
Preferably, the deflector is positioned within the air path housing by a shoulder.
Preferably, the inner diameter range of the resonant cavity is 7-9 mm, and the depth range of the resonant cavity is 3-8 mm; the distance between the resonant cavity and the bottom surface of the gas nozzle of the Hartmann whistle nozzle ranges from 1mm to 16mm.
Preferably, the gas flow range of the Hartmann whistle nozzle is 6-60 g/s, and the liquid flow range is 30-60 g/s; the frequency range of the strong sound wave generated by the Hartmann whistle nozzle is 7000-9000 Hz.
The invention has the beneficial effects that:
by adopting the technical scheme, the rocket engine thrust chamber consists of an oxidant inlet, a fuel inlet, a nozzle and a Laval nozzle, wherein the nozzle adopts a Hartmann whistle nozzle. The Hartmann whistle nozzle consists of a gas-liquid coaxial nozzle and a resonant cavity, and the gas direct-current nozzle ejects high-speed airflow to collide with the resonant cavity to generate strong sound waves. The liquid nozzle is a circular seam nozzle, gel propellant or Newton liquid propellant is sprayed out through the circular seam nozzle to form a liquid film surrounding the resonant cavity, and strong sound waves act on the liquid film to promote the liquid film to break into tiny liquid drops so as to complete the atomization process.
Compared with a rocket engine thrust chamber adopting a common ventilation liquid coaxial nozzle, the application of the Hartmann whistle nozzle in the invention effectively improves the atomization effect of gel propellant or Newton liquid propellant, improves the combustion efficiency in the thrust chamber and improves the specific impact performance of the whole rocket engine; on the other hand, the application of the Hartmann whistle nozzle increases the spray cone angle, which is beneficial to the wall cooling of the thrust chamber.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are only embodiments of the present invention, and other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic overall cross-sectional view of a rocket engine thrust chamber according to the present invention;
FIG. 2 is a schematic diagram of a Hartmann whistle nozzle according to the present invention;
FIG. 3 is a partial cross-sectional view taken along the direction A-A in FIG. 2;
FIG. 4 is a schematic diagram of the generation of intense sound waves by the Hartmann whistle nozzle of the present invention;
FIG. 5 is a schlieren measurement of the intense sound wave of a Hartmann whistle nozzle according to the present invention;
FIG. 6 is a graph comparing the atomization effect of a Hartmann whistle nozzle and a gas-liquid coaxial nozzle according to the present invention on a conventional propellant (the left graph shows the atomization effect of a Hartmann whistle nozzle on a conventional propellant, and the right graph shows the atomization effect of a gas-liquid coaxial nozzle on a conventional propellant);
fig. 7: the invention relates to a Hartmann whistle nozzle and a gas-liquid coaxial nozzle, which are used for comparing the atomization effect of the Hartmann whistle nozzle on a gel propellant (the left side of the figure is the atomization effect of the Hartmann whistle nozzle on the gel propellant, and the right side of the figure is the atomization effect of the gas-liquid coaxial nozzle on the gel propellant).
In the figure:
a 10-hartmann whistle nozzle,
the device comprises a gas inlet of a 11-Hartmann whistle nozzle, a 12-deflector, a 13-whistle rod, a 14-Hartmann whistle nozzle gas nozzle, a 15-resonant cavity, a 16-Hartmann whistle nozzle liquid inlet, a 17-Hartmann whistle nozzle liquid nozzle, a 18-gas path shell and a 19-liquid path shell;
20-gaseous oxidant inlet;
30-liquid fuel inlet;
40-combustion chamber;
a 50-Laval nozzle;
a 60-degree outer shell body, wherein the outer shell body is provided with a plurality of grooves,
61-annular support.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
Examples:
as shown in fig. 1, the present invention provides a rocket engine thrust chamber using a hartmann whistle nozzle, comprising a thrust chamber body part and a nozzle part, wherein the thrust chamber body part comprises an outer shell 60 coaxially connected to the upper part of the nozzle part, the top center of the outer shell 60 is connected with a gaseous oxidant inlet 20, and the top edge is connected with a liquid fuel inlet 30; the Hartmann whistle nozzle 10 is arranged at the upper part in the inner cavity of the outer shell, and the combustion chamber 40 is arranged at the lower part in the inner cavity; the nozzle portion is a Laval nozzle 50, and the combustion chamber 40 communicates with the Laval nozzle 50.
As shown in fig. 2 and 3, the hartmann whistle nozzle 10 consists of a gas-liquid coaxial nozzle and a resonant cavity 15 positioned below the gas-liquid coaxial nozzle, wherein the gas-liquid coaxial nozzle consists of a gas direct-current nozzle in the center and a liquid circumferential seam nozzle with a coaxial outer ring;
the gas direct-current nozzle comprises a gas path shell 18, a Hartmann whistle nozzle gas inlet 11 communicated with a gaseous oxidant inlet 20 is arranged at the upper opening of a gas direct-current channel in the gas path shell 18, a flow director 12 is arranged in the gas direct-current channel, and the flow director 12 is positioned in the gas path shell 18 through a shaft shoulder; the flow director 12 is uniformly provided with a circle of through holes which are communicated up and down, the center of the flow director 12 is fixedly connected with the upper end of a whistle rod 13, the lower end of the whistle rod 13 penetrates through the lower opening of the gas direct current channel and is fixedly connected with the bottom of the inner cavity of the lower resonant cavity 15; the lower opening of the gas direct-current channel is a Hartmann whistle nozzle gas nozzle 14, and a circular seam gas passage is formed between the Hartmann whistle nozzle gas nozzle 14 and the whistle rod 13;
the liquid circumferential-joint nozzle comprises a liquid path shell 19 coaxially fixed outside the gas path shell 18, a Hartmann whistle nozzle liquid inlet 16 communicated with a liquid fuel inlet 30 is formed in the liquid path shell 19, a Hartmann whistle nozzle liquid nozzle 17 communicated with the Hartmann whistle nozzle liquid inlet 16 is formed in the lower portion of the liquid path shell 19, a circumferential-joint liquid passage is formed between the Hartmann whistle nozzle liquid nozzle 17 and the outer wall of the gas path shell 18, and the Hartmann whistle nozzle liquid nozzle 17 is gradually inclined from top to bottom in a direction close to the central axis of the gas path shell.
Further, a ring-shaped supporting seat 61 for supporting the lower surface of the liquid path housing is installed on the inner cavity wall of the outer housing 60, and the resonant cavity 15 is located below the ring-shaped supporting seat 61.
As shown in fig. 2, the gaseous oxidizer enters the hartmann whistle nozzle gas inlet 11 from the gaseous oxidizer inlet 20, then passes through the deflector 12, and finally is ejected from the annular gas passage between the hartmann whistle nozzle gas nozzle orifice 14 and the whistle pin 13. As shown in fig. 3, 8 circles of through holes with the diameter of 2.5mm are uniformly distributed on the flow director 12 so as to allow the gas to pass through.
Diameter d of Hartmann whistle nozzle gas jet 14 g 7mm. The Hartmann whistle nozzle gas nozzle 14 and the whistle bar 13 together form a circular slit gas passage, wherein the whistle bar 13 has a diameter d s The outer diameter of (2) is 5-6 mm, so the width of the circular seam gas passage is in the range of: 0.5-1 mm.
The upper end of the whistle rod 13 is fixedly connected with the deflector 12, and the lower end is fixedly connected with the resonant cavity 15. Inner diameter d of resonant cavity 15 r The range of (2) is: 7-9 mm, the depth h ranges from: 3-8 mm. The distance L between the resonant cavity 15 and the bottom surface of the gas nozzle 14 of the Hartmann whistle nozzle is determined by the length of the whistle rod 13, and the range of L is 1-16 mm。
As shown in fig. 2, liquid fuel enters from the liquid fuel inlet 30, passes through the hartmann whistle nozzle liquid inlet 16, and is ejected from the hartmann whistle nozzle liquid outlet 17. As shown in fig. 3, the hartmann whistle nozzle liquid inlet 16 is 6 through holes with the diameter of 30mm which are formed in the liquid path shell 19 at equal intervals along the circumferential direction, namely the hartmann whistle nozzle liquid inlet 16 consists of a circle of 6 through holes with the diameter of 30 mm. The included angle a between the liquid nozzle 17 of the Hartmann whistle nozzle and the bottom plane of the liquid circumferential seam nozzle is 45-75 degrees. Diameter d of Hartmann whistle nozzle liquid spout 17 i Fixed to 11mm, diameter d of bottom outer ring of air path housing 18 o The range is 11.6-12.2 mm, so the circumferential width of the circumferential liquid passage is 0.3-0.6 mm.
In the invention, the gas flow range of the Hartmann whistle nozzle 10 is 6-60 g/s, and the liquid flow range is 30-60 g/s; the hartmann whistle nozzle 10 produces strong sound waves in the frequency range 7000 to 9000Hz.
Working principle:
when the nozzle works, the gaseous oxidant enters from the gaseous oxidant inlet 20, passes through the Hartmann whistle nozzle gas inlet 11 and the flow director 12 and is sprayed out from the Hartmann whistle nozzle gas nozzle 14. As shown in fig. 4, the high-velocity gas flow from the hartmann whistle nozzle gas jet 14 impinges on the gas inside the resonance chamber, and intense shock waves are generated inside the resonance chamber 15. The shock wave is reflected by the inner wall surface of the resonant cavity and then is transmitted out of the cavity to form strong sound wave, and the frequency range of the strong sound wave is as follows: 7000 to 9000Hz. In fig. 4, the sound wave is indicated at a, and the gas is indicated at b.
Liquid fuel enters the outer annular channel of the nozzle from the fuel cavity through the liquid inlet 16 of the Hartmann whistle nozzle, and forms a circle of liquid surrounding the resonant cavity 15 after being sprayed out from the liquid outlet 17 of the Hartmann whistle nozzle. When strong sound waves propagate to the gas-liquid interface, capillary waves are excited on the surface of the liquid, and the capillary waves grow and break to finally form tiny liquid drops, so that the atomization process is completed.
As shown in fig. 5, the strong sound wave generated by the hartmann whistle nozzle 10 is photographed by a schlieren method capable of displaying the change of the gas density, and the region with obvious black-white intervals is the strong sound wave.
As shown in fig. 6, when the liquid is a conventional newtonian liquid propellant, the hartmann whistle nozzle 10 has better atomization quality and a larger atomization cone angle than a gas-liquid coaxial nozzle with the same gas-liquid flow rate, which is beneficial for the wall surface cooling of the rocket engine thruster chamber.
As shown in fig. 7, when the liquid is a gel propellant, the hartmann whistle nozzle 10 has better atomization quality and a larger atomization cone angle than a gas-liquid coaxial nozzle with the same gas-liquid flow rate, which is beneficial for the wall surface cooling of the rocket engine thruster chamber.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A rocket engine thrust chamber using a Hartmann whistle nozzle, characterized by comprising a thrust chamber body part and a jet pipe part, wherein the thrust chamber body part comprises an outer shell coaxially connected to the upper part of the jet pipe part, and the top end of the outer shell is connected with a gaseous oxidant inlet and a liquid fuel inlet; the upper part in the inner cavity of the outer shell is provided with a Hartmann whistle nozzle, and the lower part of the inner cavity is a combustion chamber; the spray pipe part is a Laval spray pipe, and the combustion chamber is communicated with the Laval spray pipe; the Hartmann whistle nozzle consists of a gas-liquid coaxial nozzle and a resonant cavity positioned below the gas-liquid coaxial nozzle, wherein the gas-liquid coaxial nozzle consists of a gas direct-current nozzle at the center and a liquid circular seam nozzle with a coaxial outer ring;
the gas direct-current nozzle comprises a gas path shell, wherein an opening at the upper part of a gas direct-current channel in the gas path shell is a Hartmann whistle nozzle gas inlet communicated with the gaseous oxidant inlet, a flow director is arranged in the gas direct-current channel, a circle of through holes communicated up and down are uniformly distributed on the flow director, the center of the flow director is fixedly connected with the upper end of a whistle rod, and the lower end of the whistle rod penetrates out of the opening at the lower part of the gas direct-current channel and is fixedly connected with the bottom of an inner cavity of the resonant cavity below; the lower opening of the gas direct-current channel is a Hartmann whistle nozzle gas nozzle, and a circular seam gas passage is formed between the Hartmann whistle nozzle gas nozzle and the whistle rod;
the liquid circumferential-joint nozzle comprises a liquid path shell coaxially fixed outside the gas path shell, a Hartmann whistle nozzle liquid inlet communicated with the liquid fuel inlet is formed in the liquid path shell, a Hartmann whistle nozzle liquid nozzle spout is formed in the lower portion of the liquid path shell, a circumferential-joint liquid passage is formed between the Hartmann whistle nozzle liquid spout and the outer wall of the gas path shell, and the Hartmann whistle nozzle liquid spout is gradually inclined from top to bottom in a direction close to the central axis of the gas path shell.
2. A rocket engine thrust chamber employing a Hartmann whistle nozzle as recited in claim 1, wherein a ring of support seats for supporting the lower surface of the liquid path casing are mounted on the inner chamber wall of the outer casing.
3. A rocket engine thrust chamber employing a Hartmann whistle nozzle according to claim 1 wherein 8 circles of said through holes having a diameter of 2.5mm are uniformly distributed on said deflector.
4. A rocket engine thrust chamber employing a hartmann whistle nozzle according to claim 1 or 3, wherein the diameter of the hartmann whistle nozzle gas jet is 7mm, the outside diameter of the whistle rod is in the range of 5 to 6mm, and the circumferential width of the circumferential gas passage is in the range of 0.5 to 1mm.
5. A rocket engine thrust chamber employing a hartmann whistle nozzle according to claim 1 wherein said hartmann whistle nozzle liquid inlet is 6 through holes of 30mm diameter formed in said liquid path housing at equal intervals in the circumferential direction.
6. A rocket engine thrust chamber employing a Hartmann whistle nozzle according to claim 1 or 5 wherein the angle between the liquid jet of said Hartmann whistle nozzle and the bottom plane of said liquid circumferential seam nozzle is in the range of 45 ° to 75 °.
7. A rocket engine thrust chamber employing a hartmann whistle nozzle according to claim 1 or 5 wherein the diameter of the hartmann whistle nozzle liquid jet is 11mm, the diameter of the bottom outer ring of the air passage housing is in the range of 11.6 to 12.2mm, and the circumferential width of the circumferential liquid passage is in the range of 0.3 to 0.6 mm.
8. A rocket engine thrust chamber employing a Hartmann whistle nozzle as recited in claim 1, wherein the deflector is positioned within the air path housing by a shoulder.
9. A rocket engine thrust chamber employing a hartmann whistle nozzle according to claim 1 wherein the inner diameter of said resonant cavity ranges from 7 to 9mm and the depth of said resonant cavity ranges from 3 to 8mm; the distance between the resonant cavity and the bottom surface of the gas nozzle of the Hartmann whistle nozzle ranges from 1mm to 16mm.
10. A rocket engine thrust chamber employing a hartmann whistle nozzle according to claim 1 wherein the hartmann whistle nozzle has a gas flow rate in the range of 6 to 60g/s and a liquid flow rate in the range of 30 to 60g/s; the frequency range of the strong sound wave generated by the Hartmann whistle nozzle is 7000-9000 Hz.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310897935.3A CN116816541A (en) | 2023-07-21 | 2023-07-21 | Rocket engine thrust chamber using Hartmann whistle nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310897935.3A CN116816541A (en) | 2023-07-21 | 2023-07-21 | Rocket engine thrust chamber using Hartmann whistle nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116816541A true CN116816541A (en) | 2023-09-29 |
Family
ID=88122129
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310897935.3A Pending CN116816541A (en) | 2023-07-21 | 2023-07-21 | Rocket engine thrust chamber using Hartmann whistle nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116816541A (en) |
-
2023
- 2023-07-21 CN CN202310897935.3A patent/CN116816541A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6688534B2 (en) | Air assist fuel nozzle | |
| CN111889292B (en) | Air-assisted electrostatic ultrasonic atomization nozzle and method | |
| CN114001374A (en) | Gas-liquid two-phase dual-fuel rotary detonation combustion chamber | |
| CN112431693B (en) | Pin injector, rocket engine and rocket | |
| WO2012092688A1 (en) | Self-excitation oscillation jet impact nozzle for complex fluid atomization | |
| CN110594041B (en) | Self-oscillation nozzle for atomizing granular gel-containing propellant of ramjet engine | |
| CN102175041B (en) | Dividing wall type regenerative cooling air oxygen alcohol torch type igniter | |
| CN116816541A (en) | Rocket engine thrust chamber using Hartmann whistle nozzle | |
| CN216244410U (en) | Gas-liquid two-phase dual-fuel rotary detonation combustion chamber | |
| US5269495A (en) | High-pressure atomizing nozzle | |
| CN105728219A (en) | Striking and self-exciting oscillation high-thickness fluid two-phase spraying nozzle | |
| JP3192864B2 (en) | Fine fuel injection nozzle | |
| CN117738815B (en) | Multi-acute angle blending structure-based gas-liquid-solid multiphase hollow cylinder type continuous detonation engine | |
| CN115218221B (en) | Rotary sliding arc plasma regulation and control combustion device | |
| JPS6057909B2 (en) | Internal mixing atomizer | |
| CN212359969U (en) | Gel propellant injector and engine thrust chamber | |
| CN114658565B (en) | Propelling device, engine and aircraft | |
| JP2777568B2 (en) | Fuel injection nozzle | |
| CN111734557A (en) | Gel propellant injector and engine thrust chamber | |
| CN118066036B (en) | Liquid-phase kerosene empty cylinder type continuous detonation engine | |
| RU205044U1 (en) | SPRAY UNIT OF ROTARY BURNER FOR OIL FUEL | |
| CN114877377B (en) | Outer ring detonation combustor | |
| RU2170884C1 (en) | Combustion chamber with circular ultrasonic self-excited oscillator for fuel atomizing | |
| CN113279881B (en) | Multi-pintle injector unit combustion chamber | |
| CN115217701B (en) | Porous fuel atomization mixing structure and method for air suction type pulse detonation engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |