CN115075983A - Gas generator and liquid rocket engine - Google Patents
Gas generator and liquid rocket engine Download PDFInfo
- Publication number
- CN115075983A CN115075983A CN202210989904.6A CN202210989904A CN115075983A CN 115075983 A CN115075983 A CN 115075983A CN 202210989904 A CN202210989904 A CN 202210989904A CN 115075983 A CN115075983 A CN 115075983A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- fuel
- oxidant
- gas generator
- main body
- 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
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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention relates to a fuel gas generator and a liquid rocket engine, wherein the fuel gas generator comprises a main body, an igniter and at least one nozzle combination structure, wherein the main body is provided with an oxidant inlet and a fuel inlet, an ignition channel and a combustion chamber are arranged in the main body, and one end of the combustion chamber, which is far away from the ignition channel, is provided with a fuel gas outlet; the igniter is arranged on the main body and communicated with the ignition channel; the nozzle combination structure is arranged in the main body and communicated with the combustion chamber, the nozzle combination structure comprises an oxidant nozzle and a fuel nozzle, the oxidant nozzle is communicated with the oxidant inlet, the fuel nozzle is communicated with the fuel inlet, one of the oxidant nozzle and the fuel nozzle is a centrifugal nozzle, and the other of the oxidant nozzle and the fuel nozzle is a straight-flow nozzle. The liquid in the centrifugal nozzle in the fuel gas generator provided by the invention is accelerated through centrifugal rotation and is collided and mixed with the liquid sprayed by the direct current nozzle, so that the mixing degree and the mixing uniformity are improved, and the problem of low combustion efficiency of the conventional fuel gas generator is solved.
Description
Technical Field
The invention belongs to the technical field of rocket engines, and particularly relates to a fuel gas generator and a liquid rocket engine.
Background
In recent years, commercial aerospace is developed vigorously at home and abroad, liquid rocket engines are more and more emphasized by domestic and foreign aviation universities, and the gas generator is an important combustion device in the liquid rocket engine and is used for atomizing, mixing and combusting a propellant to generate high-temperature and high-pressure gas to work to drive a turbine to rotate at a high speed so as to drive a turbopump to enable the liquid rocket engine to work and provide power for the whole rocket.
However, there are many short plates in existing gasifiers: the gas generator has lower reliability due to complex processing technology; the outlet gas temperature uniformity of the gas generator is poor, and partial ablation and the like are easily caused to the turbine pump assembly; the existing fuel gas generator mostly adopts a direct current injection mode, so that the atomization effect is poor, the combustion efficiency is low, and the performance of the rocket engine is further influenced.
Disclosure of Invention
The object of the present invention is to at least solve the problem of low combustion efficiency of existing gas generators. The purpose is realized by the following technical scheme:
in a first aspect, the present invention provides a gasifier comprising:
the fuel gas burner comprises a main body, wherein an oxidant inlet and a fuel inlet are formed in the main body, an ignition channel and a combustion chamber communicated with the ignition channel are formed in the main body, and a fuel gas outlet is formed in one end, far away from the ignition channel, of the combustion chamber;
an igniter mounted on the body and in communication with the ignition channel;
at least one nozzle assembly mounted within the body and in communication with the combustion chamber, the nozzle assembly including an oxidant nozzle in communication with the oxidant inlet and a fuel nozzle in communication with the fuel inlet, one of the oxidant nozzle and the fuel nozzle being configured as a centrifugal nozzle and the other being configured as a straight flow nozzle.
According to the gas generator provided by the embodiment of the invention, the igniter is arranged on the main body, flame is sprayed into the combustion chamber through the ignition channel, meanwhile, the oxidant enters the main body through the oxidant inlet and is sprayed into the combustion chamber through the oxidant nozzle, meanwhile, the fuel enters the main body through the fuel inlet and is sprayed into the combustion chamber through the fuel nozzle.
Additionally, in some embodiments of the invention, the oxidant nozzle is disposed coaxially with the fuel nozzle, the oxidant nozzle is disposed as a centrifugal nozzle, and the fuel nozzle is disposed as a straight nozzle.
In some embodiments of the present invention, the main body includes a housing, a top cover, a first supporting plate, and a second supporting plate, the top cover, the first supporting plate, and the second supporting plate are sequentially arranged along an axial direction of the housing, and the nozzle assembly is disposed along the axial direction of the main body and is respectively connected to the first supporting plate and the second supporting plate.
In some embodiments of the present invention, the outer end surface of the top cover is provided with an igniter butting portion, the igniter butting portion is matched with the igniter, and the igniter butting portion is provided with a sealing ring.
In some embodiments of the invention, the cavity between the top cover and the first support plate is provided as an oxidant chamber, the oxidant chamber being in communication with the oxidant inlet and the oxidant nozzle, respectively; the cavity between the first support plate and the second support plate is set as a fuel cavity which is communicated with the fuel inlet and the fuel nozzle respectively.
In some embodiments of the invention, the nozzle assembly is provided in a plurality, and the plurality of nozzle assemblies are arranged uniformly around the axis of the main body.
In some embodiments of the invention, an ignition nose is arranged at one end of the ignition channel communicated with the combustion chamber.
In some embodiments of the invention, the firing nose includes a plurality of apertures that are evenly arranged about the axis of the body.
In some embodiments of the present invention, a bent pipe is disposed at an end of the combustion chamber, a bent angle of the bent pipe ranges from 60 ° to 120 °, and a nozzle of the bent pipe is disposed as the gas outlet.
A second aspect of the invention provides a liquid rocket engine comprising a gas generator according to any of the embodiments described above.
The liquid rocket engine provided by the embodiment of the invention has the same advantages as the gas generator provided by any embodiment, and because the gas generator sets one of the oxidant nozzle and the fuel nozzle as the centrifugal nozzle, the liquid (oxidant or fuel) in the centrifugal nozzle is accelerated through centrifugal rotation and collides and mixes with the liquid (fuel or oxidant) sprayed by the straight-flow nozzle, the mixing degree and mixing uniformity of the oxidant and the fuel are improved, the atomization effect and the combustion efficiency are improved, and the working efficiency of the liquid rocket engine is further improved.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like parts are designated by like reference numerals throughout the drawings.
In the drawings:
FIG. 1 is a schematic view of a gasifier;
FIG. 2 is a partial cross-sectional view of the gasifier of FIG. 1;
FIG. 3 is a top plan view of the gasifier of FIG. 1;
FIG. 4 is a schematic view of the interior of the gasifier from below;
FIG. 5 is a schematic cross-sectional view of a nozzle assembly in the gasifier;
FIG. 6 is a cross-sectional view taken along line A-A of FIG. 5;
fig. 7 is a sectional view taken in the direction B-B in fig. 5.
The reference symbols in the drawings denote the following:
1000. a gas generator; 10. a main body; 100. a top cover; 110. an igniter butt joint part; 200. a first support plate; 210. an oxidant inlet; 220. a fuel inlet; 230. an ignition channel; 240. an ignition nose; 300. a second support plate; 400. a nozzle assembly structure; 410. an oxidant nozzle; 420. a fuel nozzle; 510. a combustion chamber; 520. and a gas outlet.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only, and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," "including," and "having" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof.
Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.
For convenience of description, spatially relative terms, such as "inner", "outer", "lower", "below", "upper", "above", and the like, may be used herein to describe one element or feature's relationship to another element or feature as illustrated in the figures. Such spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" or "over" the other elements or features. Thus, the example term "below … …" can include both an orientation of above and below.
As shown in fig. 1 to 3, an embodiment of the present invention provides a gas generator 1000, wherein the gas generator 1000 includes a main body 10, an igniter (not shown), and at least one nozzle assembly 400, as shown in fig. 2, the main body 10 is provided with an oxidant inlet 210 and a fuel inlet 220, the main body 10 is provided with an ignition channel 230 and a combustion chamber 510 communicated with the ignition channel 230, and one end of the combustion chamber 510, which is far away from the ignition channel 230, is provided with a gas outlet 520; the igniter is installed on the main body 10 and communicates with the ignition path 230; the nozzle assembly 400 is installed in the body 10 and communicates with the combustion chamber 510, the nozzle assembly 400 includes an oxidizer nozzle 410 and a fuel nozzle 420, the oxidizer nozzle 410 communicates with the oxidizer inlet 210, the fuel nozzle 420 communicates with the fuel inlet 220, one of the oxidizer nozzle 410 and the fuel nozzle 420 is provided as a centrifugal nozzle, and the other is provided as a straight flow nozzle.
According to the gas generator 1000 of the embodiment of the present invention, the igniter is mounted on the body 10, the flame is injected into the combustion chamber 510 through the ignition passage 230, and the oxidant enters the body 10 through the oxidant inlet 210 and is injected into the combustion chamber 510 through the oxidant nozzle 410, and the fuel enters the body 10 through the fuel inlet 220 and is injected into the combustion chamber 510 through the fuel nozzle 420, in this embodiment, one of the oxidant nozzle 410 and the fuel nozzle 420 is a centrifugal nozzle, so that the liquid (oxidant or fuel) in the centrifugal nozzle is accelerated by centrifugal rotation and collides with the liquid (fuel or oxidant) injected from the straight nozzle to be mixed, thereby improving the mixing degree and mixing uniformity of the oxidant and the fuel, further improving the atomization effect and the combustion efficiency, and solving the problem of low combustion efficiency of the existing gas generator 1000.
The body 10 of the gas generator 1000 in this embodiment may be provided as an integrally formed structure, the oxidant inlet 210 and the fuel inlet 220 may be provided at opposite sides of the body 10 by integral forming and disposed near the top of the body 10, and accordingly, an igniter may be installed at the top of the body 10, whereby an oxidant entering the body 10 through the oxidant inlet 210 and a fuel entering the body 10 through the fuel inlet 220 may be mixed in the body 10 and mixed and combusted after the ignition of the igniter, wherein the igniter may be provided as a torch igniter or a powder igniter, the oxidant may be provided as liquid oxygen, and the fuel may be provided as liquid methane or liquid kerosene, which is not particularly limited in this embodiment and may be selected according to actual circumstances.
Further, please refer to fig. 2, in this embodiment, the main body 10 includes a housing, a top cover 100, a first supporting plate 200, and a second supporting plate 300, the top cover 100, the first supporting plate 200, and the second supporting plate 300 are sequentially arranged from top to bottom along an axial direction of the housing, and the top cover 100, the first supporting plate 200, and the second supporting plate 300 may be connected to the housing by welding, or by integral molding, or by fastening members such as bolts and screws, which is not limited in this embodiment. On this basis, the top cover 100 is connected to the top of the housing, the first support plate 200 and the second support plate 300 are both connected to the inside of the housing, and cavities are formed between the top cover 100 and the first support plate 200 and between the first support plate 200 and the second support plate 300.
As shown in fig. 2 and 3, the outer end surface of the top cap 100 is provided with an igniter receipt 110, and the igniter receipt 110 is engaged with an igniter, that is, the igniter is mounted on the main body 10 through the igniter receipt 110 and communicates with the ignition passage 230 in the main body 10, whereby a flame generated from the igniter can be introduced into the main body 10 through the ignition passage 230. In this embodiment, the igniter is connected to the main body 10, and the connection manner may be through a fastener such as a screw, and the connection manner is not specifically limited in this embodiment and may be selected according to actual situations; on this basis, the igniter butting portion 110 is further provided with a sealing ring for improving the sealing property between the igniter and the main body 10, the sealing ring may be a graphite sealing ring, and the type of the sealing ring is not specifically limited in this embodiment, and may be selected according to actual situations.
Further, as shown in fig. 2, the oxidant inlet 210 and the fuel inlet 220 are respectively disposed at two opposite sides of the housing, and in some embodiments of the present invention, the axis of the oxidant inlet 210 and the axis of the fuel inlet 220 may be parallel, which not only facilitates the molding of the main body 10, but also facilitates the subsequent mixing of the oxidant and the fuel. On the basis of the above embodiment, the oxidant inlet 210 is located between the top cover 100 and the first supporting plate 200, the oxidant inlet 210 is communicated with the oxidant chamber, and accordingly, a cavity formed between the top cover 100 and the first supporting plate 200 is provided as the oxidant chamber, so that the oxidant can enter the oxidant chamber; the fuel inlet 220 is positioned between the first and second support plates 200 and 300, and the fuel inlet 220 communicates with the fuel chamber, and accordingly, a hollow space formed between the first and second support plates 200 and 300 is provided as the fuel chamber, so that fuel can enter the fuel chamber.
On the basis of the above embodiments, as shown in fig. 2, the nozzle assembly 400 is installed in the body 10, and in some embodiments of the present invention, the nozzle assembly 400 is disposed along the axial direction of the body 10, both ends of the nozzle assembly 400 are respectively connected to the first supporting plate 200 and the second supporting plate 300, and the nozzle assembly 400 includes an oxidizer nozzle 410 and a fuel nozzle 420, wherein the oxidizer nozzle 410 is communicated with the oxidizer chamber, and the fuel nozzle 420 is communicated with the fuel chamber, so that the oxidizer introduced into the body 10 through the oxidizer inlet 210 firstly enters the oxidizer chamber and then is sprayed out through the oxidizer nozzle 410; the fuel introduced into the main body 10 through the fuel inlet 220 first enters the fuel chamber and then is injected through the fuel nozzle 420.
In some embodiments of the present invention, as shown in fig. 2, 4 and 5, the nozzle assembly 400 is provided as a cylindrical structure, the oxidizer nozzle 410 and the fuel nozzle 420 are nested with their axes coincident, one of the oxidizer nozzle 410 and the fuel nozzle 420 is a centrifugal nozzle and the other is a straight nozzle, and optionally, when the oxidizer nozzle 410 is provided as a centrifugal nozzle, the fuel nozzle 420 is provided as a straight nozzle; when the fuel nozzle 420 is configured as a centrifugal nozzle, the oxidant nozzle 410 is configured as a straight flow nozzle.
According to the above embodiment, since the oxidant chamber is located upstream of the fuel chamber in the present embodiment, that is, the oxidant nozzle 410 is located upstream of the fuel nozzle 420 in the nozzle assembly 400, as shown in fig. 6, the oxidant nozzle 410 is configured as a centrifugal nozzle in the present embodiment, and as shown in fig. 7, the fuel nozzle 420 is configured as a straight-flow nozzle, specifically, as an annular straight-flow nozzle, so that the oxidant can be collided and mixed with the fuel after being accelerated by centrifugal rotation, and the mixing degree and mixing uniformity are improved, so as to further ensure the subsequent sufficient combustion.
Further, as shown in fig. 4, in some embodiments of the present invention, a plurality of nozzle combinations 400 are provided, for example, the shape of at least a part of the main body 10 is configured as a cylinder, the plurality of nozzle combinations 400 are uniformly arranged around the axis of the main body 10, in an alternative embodiment, the number of nozzle combinations 400 is nine, nine nozzle combinations 400 are uniformly arranged in the main body 10, and each nozzle combination 400 is connected to the first supporting plate 200 and the second supporting plate 300, so as to ensure the stability of each nozzle combination 400.
On the basis of the above embodiment, the main body 10 is further provided with the ignition passage 230 and the combustion chamber 510, and the nozzle assembly 400 in the above embodiment is communicated with the combustion chamber 510, so that the mixed oxidant and fuel can be injected into the combustion chamber 510; in the present embodiment, the ignition passage 230 is located near the top of the main body 10, as shown in fig. 2, the ignition passage 230 penetrates the top cover 100, the first supporting plate 200 and the second supporting plate 300, the top end of the ignition passage 230 communicates with the igniter, and the bottom end of the ignition passage 230 communicates with the combustion chamber 510, so that the flame generated by the igniter enters the combustion chamber 510 through the ignition passage 230 to ignite the mixed oxidant and fuel.
Further, as shown in fig. 2 to 4, in some embodiments of the present invention, an ignition nose 240 is disposed at an end of the ignition channel 230 communicating with the combustion chamber 510, and the ignition nose 240 in this embodiment is used to make the flame entering the combustion chamber 510 more uniform, thereby making the oxidant and fuel combustion more uniform. In some embodiments of the present invention, the ignition nose 240 includes a plurality of apertures that are evenly arranged about the axis of the body 10. In an alternative embodiment, as shown in fig. 3 and 4, the number of the small holes is three, three small holes are uniformly arranged at the bottom end of the ignition passage 230, and the included angle between two adjacent small holes is 120 °.
In some embodiments of the present invention, as shown in fig. 1 and fig. 2, a bent tube is disposed at a bottom end of the combustion chamber 510, it should be noted that in this embodiment, the bent tube and the housing of the main body 10 may be configured as an integrally formed structure, the bent tube may also be connected to the bottom of the housing by welding, a bending angle of the bent tube ranges from 60 ° to 120 °, for example, may be set as 90 °, a nozzle of the bent tube is configured as a gas outlet 520, due to the configuration of the bent tube, the oxidant and the fuel can be sufficiently combusted in the combustion chamber 510, and high-temperature and high-pressure gas generated after combustion is discharged after being bent, so that a temperature of the gas is more uniform, a possibility of occurrence of a local excessive temperature is avoided or reduced, and a possibility of local ablation on the turbine pump assembly is avoided or reduced.
Illustratively, when the oxidant is liquid oxygen and the fuel is liquid methane, the liquid oxygen enters the nozzle assembly 400 through the oxidant chamber, and is ejected from the centrifugal nozzle after being accelerated by rotation, the liquid methane enters the nozzle assembly 400 through the fuel chamber and is ejected from the direct current nozzle after being accelerated by rotation, the liquid methane and the fuel chamber collide to form micro droplets, the droplets are crushed and mixed, the mixing degree and the mixing uniformity are improved, and then the micro droplets enter the combustion chamber 510 in the main body 10 to be combusted, so that high-temperature and high-pressure fuel gas is generated, and the fuel gas is bent through the bent pipe and then is discharged through the fuel gas outlet 520, so that the temperature uniformity of the fuel gas is improved.
The embodiment of the second aspect of the invention provides a liquid rocket engine, which comprises the gas generator 1000 according to any one of the above embodiments, and it is understood that the liquid rocket engine generally further comprises a turbopump, the turbopump is communicated with the gas generator 1000, and the high-temperature and high-pressure gas generated by the gas generator 1000 enters the turbopump and can drive the turbopump to operate at high speed to do work to provide power for the rocket.
The liquid rocket engine according to the embodiment of the present invention has the same advantages as the gas generator 1000 according to any of the embodiments, and since the gas generator 1000 sets one of the oxidant nozzle 410 and the fuel nozzle 420 as a centrifugal nozzle, the liquid (oxidant or fuel) in the centrifugal nozzle is accelerated by centrifugal rotation and collides and mixes with the liquid (fuel or oxidant) ejected from the straight-flow nozzle, so as to improve the mixing degree and mixing uniformity of the oxidant and the fuel, improve the atomization effect and the combustion efficiency, and further improve the working efficiency of the liquid rocket engine.
Illustratively, when the oxidant is liquid oxygen and the fuel is liquid methane, the liquid oxygen enters the nozzle composite structure 400 through the oxidant cavity, the liquid oxygen is ejected after being accelerated by rotation from the centrifugal nozzle, the liquid methane enters the nozzle composite structure 400 through the fuel cavity and is ejected by acceleration from the direct current nozzle, the liquid methane and the fuel form micro droplets after colliding, the droplets are crushed and mixed, the mixing degree and the mixing uniformity are improved, the liquid methane enters the combustion chamber 510 in the main body 10 to be combusted, high-temperature and high-pressure fuel gas is generated, the fuel gas is bent through the bent pipe and then is discharged through the fuel gas outlet 520, the temperature uniformity of the fuel gas is improved, the fuel gas enters the turbine pump of the liquid rocket engine to drive the turbine pump to operate, and the working efficiency of the liquid rocket engine is improved.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A gas generator, characterized in that the gas generator comprises:
the fuel gas burner comprises a main body, wherein an oxidant inlet and a fuel inlet are formed in the main body, an ignition channel and a combustion chamber communicated with the ignition channel are formed in the main body, and a fuel gas outlet is formed in one end, far away from the ignition channel, of the combustion chamber;
an igniter mounted on the body and in communication with the ignition channel;
at least one nozzle assembly mounted within the body and in communication with the combustion chamber, the nozzle assembly including an oxidant nozzle in communication with the oxidant inlet and a fuel nozzle in communication with the fuel inlet, one of the oxidant nozzle and the fuel nozzle being configured as a centrifugal nozzle and the other being configured as a straight flow nozzle.
2. The gas generator as claimed in claim 1, wherein the oxidant nozzle is arranged coaxially with the fuel nozzle, the oxidant nozzle being arranged as a centrifugal nozzle and the fuel nozzle being arranged as a straight nozzle.
3. The gas generator as claimed in claim 1, wherein the main body includes a housing, a head cover, a first support plate and a second support plate, the head cover, the first support plate and the second support plate are sequentially arranged along an axial direction of the housing, and the nozzle assembly is disposed along the axial direction of the main body and is connected to the first support plate and the second support plate, respectively.
4. The gas generator as claimed in claim 3, wherein the outer end surface of the top cap is provided with an igniter docking portion, the igniter docking portion is engaged with the igniter, and the igniter docking portion is provided with a sealing ring.
5. The gas generator as claimed in claim 3, wherein the cavity between the head cover and the first support plate is provided as an oxidant chamber communicating with the oxidant inlet and the oxidant nozzle, respectively; the cavity between the first support plate and the second support plate is set as a fuel cavity which is communicated with the fuel inlet and the fuel nozzle respectively.
6. The gas generator as claimed in claim 1, wherein the nozzle assembly is provided in a plurality, the plurality of nozzle assemblies being evenly arranged about the axis of the body.
7. The gas generator as claimed in claim 1, wherein an ignition nose is provided at an end of the ignition passage communicating with the combustion chamber.
8. The gasifier of claim 7, wherein the ignition nose includes a plurality of apertures that are evenly arranged about an axis of the body.
9. The gas generator as claimed in claim 1, wherein the end of the combustion chamber is provided with a bent pipe, the bent pipe has a bent angle ranging from 60 ° to 120 °, and a nozzle of the bent pipe is provided as the gas outlet.
10. A liquid rocket engine, characterized in that it comprises a gas generator according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210989904.6A CN115075983A (en) | 2022-08-18 | 2022-08-18 | Gas generator and liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210989904.6A CN115075983A (en) | 2022-08-18 | 2022-08-18 | Gas generator and liquid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115075983A true CN115075983A (en) | 2022-09-20 |
Family
ID=83244486
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210989904.6A Pending CN115075983A (en) | 2022-08-18 | 2022-08-18 | Gas generator and liquid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115075983A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115405440A (en) * | 2022-11-01 | 2022-11-29 | 北京宇航推进科技有限公司 | Gas generator of liquid rocket engine and head thereof |
| CN118066037A (en) * | 2024-04-25 | 2024-05-24 | 北京中科宇航技术有限公司 | 110 Ton pintle type liquid oxygen kerosene engine gas generator |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2345238C1 (en) * | 2007-11-15 | 2009-01-27 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Mixing head of liquid propellant rocket engine chamber |
| CN109469559A (en) * | 2019-01-24 | 2019-03-15 | 北京宇航推进科技有限公司 | The integrated ejector filler of liquid-propellant rocket engine |
| CN109798202A (en) * | 2019-04-04 | 2019-05-24 | 北京宇航推进科技有限公司 | A kind of liquid-propellant rocket engine ejector filler integrating electric igniter |
| CN212130635U (en) * | 2020-04-13 | 2020-12-11 | 星河动力(北京)空间科技有限公司 | Gas generator |
| CN114412664A (en) * | 2021-12-23 | 2022-04-29 | 北京航天动力研究所 | Thrust chamber head structure for reducing ignition impact |
-
2022
- 2022-08-18 CN CN202210989904.6A patent/CN115075983A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2345238C1 (en) * | 2007-11-15 | 2009-01-27 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Mixing head of liquid propellant rocket engine chamber |
| CN109469559A (en) * | 2019-01-24 | 2019-03-15 | 北京宇航推进科技有限公司 | The integrated ejector filler of liquid-propellant rocket engine |
| CN109798202A (en) * | 2019-04-04 | 2019-05-24 | 北京宇航推进科技有限公司 | A kind of liquid-propellant rocket engine ejector filler integrating electric igniter |
| CN212130635U (en) * | 2020-04-13 | 2020-12-11 | 星河动力(北京)空间科技有限公司 | Gas generator |
| CN114412664A (en) * | 2021-12-23 | 2022-04-29 | 北京航天动力研究所 | Thrust chamber head structure for reducing ignition impact |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115405440A (en) * | 2022-11-01 | 2022-11-29 | 北京宇航推进科技有限公司 | Gas generator of liquid rocket engine and head thereof |
| CN118066037A (en) * | 2024-04-25 | 2024-05-24 | 北京中科宇航技术有限公司 | 110 Ton pintle type liquid oxygen kerosene engine gas generator |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115075983A (en) | Gas generator and liquid rocket engine | |
| US10731862B2 (en) | Systems and methods for a multi-fuel premixing nozzle with integral liquid injectors/evaporators | |
| CN203570457U (en) | Two-stage mixing type nozzle device | |
| CN114001374A (en) | Gas-liquid two-phase dual-fuel rotary detonation combustion chamber | |
| EP3102877B1 (en) | Combustor | |
| KR20190025497A (en) | Premixing fuel injectors and methods of use in gas turbine combustor | |
| EP3376109B1 (en) | Dual-fuel fuel nozzle with liquid fuel tip | |
| CN109140506B (en) | Nozzle assembly for dual fuel nozzle | |
| CN102175041B (en) | Dividing wall type regenerative cooling air oxygen alcohol torch type igniter | |
| CN115789699A (en) | Combined nozzle combustion chamber | |
| US11215365B2 (en) | Nozzle for combustors, combustor, and gas turbine including the same | |
| US9677766B2 (en) | Fuel nozzle for use in a turbine engine and method of assembly | |
| CN113551265B (en) | Fuel nozzle and gas turbine | |
| CN103917826A (en) | Turbomachine combustor assembly and method of operating a turbomachine | |
| CN109140505B (en) | Dual fuel nozzle and combustor | |
| CN114165359B (en) | Injector structure for preventing body from overheating | |
| CN212406906U (en) | Three-stroke injector | |
| EP3988846B1 (en) | Integrated combustion nozzle having a unified head end | |
| CN112344373B (en) | Stirling engine dual-mode combustion chamber and implementation method thereof | |
| EP3026249B1 (en) | Gas generator | |
| CN114483380A (en) | Small-sized gas generating device capable of being started for multiple times | |
| CN115307177A (en) | Bifurcated pilot premixer for main micro-mixer array in gas turbine engine | |
| CN112166669B (en) | Blunt type injection turbulent ring ignition and flame stabilization device | |
| US11015810B2 (en) | Combustor nozzle assembly and gas turbine having the same | |
| CN115325569B (en) | Combustion chamber, gas turbine and combustion control method |
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 |