CN110617160B - Step type combustion chamber and inner wall of engine without spray pipe - Google Patents
Step type combustion chamber and inner wall of engine without spray pipe Download PDFInfo
- Publication number
- CN110617160B CN110617160B CN201910811696.9A CN201910811696A CN110617160B CN 110617160 B CN110617160 B CN 110617160B CN 201910811696 A CN201910811696 A CN 201910811696A CN 110617160 B CN110617160 B CN 110617160B
- Authority
- CN
- China
- Prior art keywords
- wall surface
- combustion chamber
- engine
- combustion
- axial
- 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.)
- Active
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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention provides a step-type combustion chamber and an inner wall of a non-nozzle engine, wherein the inner wall of the combustion chamber comprises a head radial wall surface and an axial wall surface; the radial wall surface of the head part consists of an initial step wall surface, a transition wall surface and a pressure stabilizing step wall surface, the initial step wall surface and the pressure stabilizing step wall surface are the same plane and are vertical to the axis of the engine, the transition wall surface has a certain gradient, and the initial step wall surface and the pressure stabilizing step wall surface are connected into a whole; the axial wall surface is connected with the outer edge of the initial stepped wall surface and extends along the axial direction of the combustion chamber; the axial wall and the radial wall of the head together form a combustion chamber.
Description
Technical Field
The invention relates to an engine combustion chamber technology, in particular to a step-type combustion chamber and an inner wall of a non-nozzle engine.
Background
The engine without nozzle is often used as an initial boosting stage of a solid rocket ramjet engine, and is a unique solid rocket engine. The mechanical jet pipe in the traditional propeller is replaced by utilizing the gas choking effect, and the mechanical jet pipe has the advantages of simple structure, high reliability, lower cost and the like.
In order to ensure the necessary condition of maintaining the gas choking effect in the working process of the engine, the length-diameter ratio of the design of the engine without the nozzle has to be larger, so that the phenomenon of nonuniform transition of a combustion surface in the working process is very obvious. In addition, the change of the internal flow field of the engine without the nozzle is complex because the combustion surface is shifted to cause the change of the combustion gas channel along with the working process. Taking a single propellant non-nozzle engine as an example, it can be observed that at the same time the pressure of the gas channel of the non-nozzle engine decreases progressively from the inside towards the outside. And along with the time, under the condition of reasonable length-diameter ratio, the pressure at each part of the combustion chamber is reduced by monotone, the pressure gradient in the channel is reduced, and the gas acceleration effect is gradually weakened.
The main drawback of the existing engine without nozzle is that the specific impulse is small. Relevant research shows that the specific impulse of the engine without the nozzle under the same condition is 80-90% of that of the traditional engine. In principle, the loss of specific impulse is due to the pressure loss generated during the gas choking process, which is related to the pore size of the gas channel. Therefore, the pressure loss at the end of the engine operation is more serious than at the beginning.
Disclosure of Invention
The invention aims to provide a stepped combustion chamber of a non-nozzle engine.
The first technical scheme for realizing the invention is as follows: a step-type combustion chamber of a non-nozzle engine comprises a head radial wall surface and an axial wall surface; the radial wall surface of the head part consists of an initial step wall surface, a transition wall surface and a pressure stabilizing step wall surface, the initial step wall surface and the pressure stabilizing step wall surface are the same plane and are vertical to the axis of the engine, the transition wall surface has a certain gradient, and the initial step wall surface and the pressure stabilizing step wall surface are connected into a whole; the axial wall surface is connected with the outer edge of the initial stepped wall surface and extends axially along the combustion chamber; the axial wall and the radial wall of the head together form a combustion chamber.
Further, the axial distance between the initial step wall surface and the tail part of the engine is smaller than the axial distance between the pressure stabilizing step wall surface and the tail part of the engine.
Furthermore, a boosting agent is arranged in the combustion chamber, a combustion channel is arranged in the middle of the boosting agent along the axial direction, and one end, far away from the radial wall surface of the head, of the boosting agent is funnel-shaped.
The second technical scheme for realizing the aim of the invention is as follows: the inner wall of the stepped combustion chamber of the engine without the spray pipe comprises a head radial wall surface and an axial wall surface; the radial wall surface of the head part consists of an initial step wall surface, a transition wall surface and a pressure stabilizing step wall surface, the initial step wall surface and the pressure stabilizing step wall surface are the same plane and are vertical to the axis of the engine, the transition wall surface has a certain gradient, and the initial step wall surface and the pressure stabilizing step wall surface are connected into a whole; the axial wall surface is connected with the outer edge of the initial step wall surface and extends along the axial direction of the combustion chamber.
Further, the axial distance between the initial step wall surface and the tail part of the engine is smaller than the axial distance between the pressure stabilizing step wall surface and the tail part of the engine.
Compared with the prior art, the invention has the following advantages: (1) the invention utilizes the combustion surface to push, increases the combustion area of the propellant at the later working stage of the engine through the shape of the inner wall of the combustion chamber, compensates partial pressure loss, improves the gas acceleration effect and improves the specific impulse performance of the engine without a spray pipe; (2) the invention only compensates the pressure loss in the middle and later periods with lower internal pressure of the engine, hardly influences the maximum pressure peak value appearing in the initial period of the working process, and does not put higher requirements on the shell while improving the specific impulse.
The present invention is described in further detail below with reference to the attached drawing figures.
Drawings
FIG. 1 is a schematic view of the inner wall structure of a stepped combustion chamber of a flameless engine according to the present invention.
FIG. 2 is a schematic illustration of a combustion surface transition of the engine during operation of the present invention.
Detailed Description
Referring to fig. 1, the inner wall of the stepped combustion chamber of the engine without the nozzle pipe comprises a head radial wall surface 1 and an axial wall surface 2.
The head radial wall surface 1 consists of an initial step wall surface 3, a transition wall surface 4 and a pressure stabilizing step wall surface 5, and the initial step wall surface 3 and the pressure stabilizing step wall surface 5 are the same plane and are vertical to the axis of the engine; the transition wall surface 4 has a certain gradient and connects the initial step wall surface 3 and the pressure stabilizing step wall surface 5 into a whole.
The axial wall surface 2 is tightly combined with the head radial wall surface 1 to form the inner wall of the combustion chamber together.
The axial distance between the initial step wall surface 3 and the tail part of the engine is shorter, and the axial distance between the pressure stabilizing step wall surface 5 and the tail part of the engine is longer.
The present invention is further illustrated by the following specific examples.
Example 1
Referring to fig. 1, the inner wall of the stepped combustion chamber of the engine without the nozzle pipe comprises a head radial wall surface 1 and an axial wall surface 2;
the head radial wall surface 1 consists of an initial step wall surface 3, a transition wall surface 4 and a pressure stabilizing step wall surface 5, and the initial step wall surface 3 and the pressure stabilizing step wall surface 5 are the same plane and are vertical to the axis of the engine; the transition wall surface 4 has a certain gradient and connects the initial step wall surface 3 and the pressure stabilizing step wall surface 5 into a whole.
The axial wall surface 2 and the head radial wall surface 1 are tightly combined to form the inner wall of the combustion chamber together.
The axial distance between the initial step wall surface 3 and the tail part of the engine is short, and the axial distance between the pressure stabilizing step wall surface 5 and the tail part of the engine is long.
In connection with fig. 2, the light grey parts indicate the initial propellant residues during operation, the dark grey parts indicate the final propellant residues during operation, 8 indicates the initial propellant burning surface and 9 indicates the final propellant burning surface. It can be seen that, as the combustion surface progresses, the combustion surface speed increases and combustion quality increases in the combustion chamber having a particular shape as the propellant combustion surface begins to contact the transition wall surface, and the internal pressure drop begins to be suppressed. When the combustion surface is intersected with the transition wall surface, the length-diameter ratio is increased while the combustion surface is increased, if the combustion surface is continuously increased in the axial direction, the internal pressure intensity may start to rise for the second time, and the risk of influencing the maximum pressure intensity of the head is influenced, so that the increasing speed of the combustion surface needs to be controlled by the pressure-stabilizing stepped wall surface at a proper position, and the effect of stabilizing the internal pressure intensity is achieved. This shows that the stepped combustion chamber inner wall design of the present invention has unique advantages in a linerless engine.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
The invention utilizes the step-type change of the inner wall structure of the combustion chamber to artificially control the combustion area of the engine propellant in the working process, and improves the average working pressure of the engine under the condition of controlling the maximum pressure in the combustion chamber to be basically unchanged, so that the engine without a spray pipe obtains better specific impulse performance. The method can be applied to the fields of design and optimization of rocket engines and the like, and has good engineering application prospect.
Claims (3)
1. A step-type combustion chamber of a non-nozzle engine is characterized in that the inner wall of the combustion chamber comprises a head radial wall surface (1) and an axial wall surface (2); the head radial wall surface (1) consists of an initial step wall surface (3), a transition wall surface (4) and a pressure stabilizing step wall surface (5), the initial step wall surface (3) and the pressure stabilizing step wall surface (5) are the same plane and are perpendicular to the axis of the engine, the transition wall surface (4) has a certain gradient, and the initial step wall surface (3) and the pressure stabilizing step wall surface (5) are connected into a whole; the axial wall surface (2) is connected with the outer edge of the pressure stabilizing stepped wall surface (5) and extends along the axial direction of the combustion chamber; the axial wall surface (2) and the head radial wall surface (1) jointly form a combustion chamber; the axial distance between the initial step wall surface (3) and the tail part of the engine is smaller than the axial distance between the pressure stabilizing step wall surface (5) and the tail part of the engine; a boosting agent (6) is arranged in the combustion chamber, and a combustion channel (7) is arranged in the middle of the boosting agent (6) along the axial direction; the shape of the boosting agent (6) is consistent with that of the inner wall of the combustion chamber, when the combustion surface of the propellant begins to contact with the transition wall surface along with the transition of the combustion surface, the combustion chamber with a special shape enables the combustion surface to be accelerated and enlarged, the combustion quality to be increased, the internal pressure drop to be restrained, the increasing speed of the combustion surface is controlled by the pressure-stabilizing stepped wall surface, and the effect of stabilizing the internal pressure is achieved.
2. A combustion chamber according to claim 1, characterized in that the end of the booster remote from the head radial wall (1) is funnel-shaped.
3. The inner wall of the stepped combustion chamber of the engine without the nozzle is characterized by comprising a head radial wall surface (1) and an axial wall surface (2); the head radial wall surface (1) consists of an initial step wall surface (3), a transition wall surface (4) and a pressure stabilizing step wall surface (5), the initial step wall surface (3) and the pressure stabilizing step wall surface (5) are the same plane and are perpendicular to the axis of the engine, the transition wall surface (4) has a certain gradient, and the initial step wall surface (3) and the pressure stabilizing step wall surface (5) are connected into a whole; the axial wall surface (2) is connected with the outer edge of the pressure stabilizing stepped wall surface (5) and extends along the axial direction of the combustion chamber; the axial distance between the initial step wall surface (3) and the tail part of the engine is smaller than the axial distance between the pressure stabilizing step wall surface (5) and the tail part of the engine; a boosting agent (6) is arranged in the combustion chamber, and a combustion channel (7) is arranged in the middle of the boosting agent (6) along the axial direction; the shape of the boosting agent (6) is consistent with that of the inner wall of the combustion chamber, when the combustion surface of the propellant begins to contact with the transition wall surface along with the transition of the combustion surface, the combustion chamber with a special shape enables the combustion surface to be accelerated and enlarged, the combustion quality to be increased, the internal pressure drop to be restrained, the increasing speed of the combustion surface is controlled by the pressure-stabilizing stepped wall surface, and the effect of stabilizing the internal pressure is achieved.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910811696.9A CN110617160B (en) | 2019-08-30 | 2019-08-30 | Step type combustion chamber and inner wall of engine without spray pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910811696.9A CN110617160B (en) | 2019-08-30 | 2019-08-30 | Step type combustion chamber and inner wall of engine without spray pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110617160A CN110617160A (en) | 2019-12-27 |
| CN110617160B true CN110617160B (en) | 2022-06-28 |
Family
ID=68922792
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910811696.9A Active CN110617160B (en) | 2019-08-30 | 2019-08-30 | Step type combustion chamber and inner wall of engine without spray pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110617160B (en) |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2326260C2 (en) * | 2006-07-26 | 2008-06-10 | Федеральное государственное унитарное предприятие "Федеральный центр двойных технологий "Союз" (ФГУП "ФЦДТ "Союз") | Charge molded within solid-fuel rocket engine case |
| CN102080607B (en) * | 2009-11-30 | 2014-06-18 | 贵州航天风华精密设备有限公司 | Motor for forest fire extinguishing bomb |
| CN205980958U (en) * | 2016-08-09 | 2017-02-22 | 山西北方兴安化学工业有限公司 | Civilian combination powder charge of single chamber dualthrust for rocket |
| CN106481457B (en) * | 2016-10-28 | 2017-11-24 | 西安近代化学研究所 | A kind of solid gas starter |
| CN207278380U (en) * | 2017-09-15 | 2018-04-27 | 江西洪都航空工业集团有限责任公司 | A kind of nozzleless rocket motor powder charge Grain structure |
| US20190120174A1 (en) * | 2017-10-25 | 2019-04-25 | Northrop Grumman Innovation Systems, Inc. | Precursor compositions for an insulation, insulated rocket motors, and related methods |
| CN109578148A (en) * | 2018-11-07 | 2019-04-05 | 北方特种能源集团有限公司西安庆华公司 | A kind of fanjet pyrotechnic initiator abnormity powder charge |
-
2019
- 2019-08-30 CN CN201910811696.9A patent/CN110617160B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110617160A (en) | 2019-12-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4095021B2 (en) | Rocket vehicle thrust booster in the nozzle's widest part | |
| JP4949154B2 (en) | Gas exhaust nozzle of bypass turbomachine with exhaust cross section or throat cross section that can be changed by moving secondary cowl | |
| CN110107915B (en) | Main combustion chamber three-channel short sudden-expansion diffuser | |
| JP2009008087A (en) | Spray hole profile | |
| EP3036422B1 (en) | High performance convergent divergent nozzle | |
| US7509796B2 (en) | Pintle-controlled propulsion system with external dynamic seal | |
| EP2137395B1 (en) | Rocket engine laval nozzle | |
| EP2594741A2 (en) | Diffuser, in particular for an axial flow machine | |
| CN110617160B (en) | Step type combustion chamber and inner wall of engine without spray pipe | |
| CN110821708A (en) | Three-combustion-speed variable-thickness combined explosive column structure of jet pipe-free engine | |
| US3608312A (en) | Self-actuated dual area annular nozzle | |
| CN110439708B (en) | Partially-coated spray-pipe-free propeller explosive column | |
| SE8503554D0 (en) | SPACIAL ROCKET DRIVER | |
| JPH0828207A (en) | Balanced steam control valve assembly and plug type valve element therefor | |
| GB1468726A (en) | Gas turbine engines | |
| US3138921A (en) | Variable area nozzle | |
| EP2993405A1 (en) | Variable orifice jet for a turbine engine | |
| WO2003081163A3 (en) | Ammunition projectile having enhanced aerodynamic profile | |
| EP3009639A1 (en) | Gas turbine engine nacelle | |
| US3937238A (en) | Variable area engine inlet | |
| KR101608588B1 (en) | A Gas flow adjuster | |
| CN110168230A (en) | Subregion surface roughness | |
| CN105756806A (en) | Axial symmetry spray pipe having afterburning function | |
| GB2194616A (en) | Propulsion nozzles thereby reducing lateral forces | |
| US20130091849A1 (en) | Augmentor spray bar with tip support bushing |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |