CN109737457B - Rotary detonation combustion chamber enabling detonation waves to be transmitted in one direction - Google Patents
Rotary detonation combustion chamber enabling detonation waves to be transmitted in one direction Download PDFInfo
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- CN109737457B CN109737457B CN201811533081.6A CN201811533081A CN109737457B CN 109737457 B CN109737457 B CN 109737457B CN 201811533081 A CN201811533081 A CN 201811533081A CN 109737457 B CN109737457 B CN 109737457B
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Abstract
The invention discloses a rotary detonation combustor capable of realizing unidirectional propagation of detonation waves, which comprises a combustor outer ring, a combustor inner ring, a mounting seat and an igniter, wherein the combustor inner ring is fixedly connected with the combustor outer ring; the combustion chamber inner ring is coaxial with the combustion chamber outer ring; the outer wall surface of the combustion chamber inner ring is a cylindrical surface; the inner wall surface of the outer ring of the combustion chamber is a periodic gradually-reduced and suddenly-expanded molded surface, the curvature radius of the inner wall surface of the gradually-reduced section is gradually reduced, and a step surface is formed between the suddenly-expanded section and the next periodic molded surface; the mounting seat is arranged at the beginning of the tapered section along the outer ring of the combustion chamber; the igniter is arranged on the mounting seat; according to the combustion chamber, the inner wall surface of the outer ring of the combustion chamber can inhibit the generation of reverse detonation waves in the initiation stage of the rotary detonation waves, and the propagation of the reverse detonation waves is effectively prevented in the propagation stage of the rotary detonation waves.
Description
Technical Field
The invention belongs to the technical field of aerospace power, and particularly relates to a rotary detonation combustion chamber capable of realizing unidirectional propagation of detonation waves.
Background
The traditional aerospace engines mostly generate power based on deflagration combustion, and through decades of development, the engines are close to maturity, the performance is difficult to greatly improve, and a novel engine technology with higher development efficiency becomes a necessary trend in the field of propulsion. The detonation wave is a supersonic combustion wave with a rapidly increased thermodynamic state after expanding a reaction surface, can be regarded as a strong shock wave with chemical reaction, and has the advantages of fast energy release, small entropy increase, high thermal cycle efficiency and the like compared with the detonation wave.
In an annular combustion chamber of the rotary detonation engine, the propagation direction of the rotary detonation wave after detonation has strong randomness, and the steering phenomenon of the rotary detonation wave after detonation can occur. The rotary detonation combustor which can enable detonation waves to be transmitted in a single direction and control the direction of the detonation waves has very important practical significance, for example, when a combined engine of the rotary detonation combustor and a turbine is researched, the problem of the transmission direction of the rotary detonation waves needs to be considered, and the transmission direction of the rotary detonation waves can be controlled, so that the design work of the turbine is facilitated.
Disclosure of Invention
The invention aims to provide a rotary detonation combustion chamber capable of enabling detonation waves to be transmitted in a single direction, and the rotary detonation combustion chamber is used for solving the problem that the propagation direction of the detonation waves in the conventional rotary detonation combustion chamber is uncontrollable.
The technical solution for realizing the purpose of the invention is as follows:
a rotary detonation combustion chamber enabling detonation waves to be transmitted in a single direction comprises a combustion chamber outer ring, a combustion chamber inner ring, a mounting seat and an igniter;
the combustion chamber inner ring is coaxial with the combustion chamber outer ring; the outer wall surface of the combustion chamber inner ring is a cylindrical surface; the inner wall surface of the outer ring of the combustion chamber is a periodic gradually-reducing and suddenly-expanding molded surface, the periodicity is n, (n is more than or equal to 2), the curvature radius of the inner wall surface of the gradually-reducing section is gradually reduced, and a step surface is formed between the suddenly-expanding section and the next periodic molded surface; the mounting seat is arranged at the beginning of the tapered section along the outer ring of the combustion chamber; the igniter is arranged on the mounting seat.
Compared with the prior art, the invention has the following remarkable advantages:
(1) the inner wall surface of the combustion chamber outer ring of the rotary detonation combustion chamber can inhibit the generation of reverse detonation waves in the detonation stage of the rotary detonation waves.
(2) The inner wall surface of the combustion chamber outer ring of the rotary detonation combustion chamber can effectively prevent the propagation of reverse detonation waves in the propagation stage of the rotary detonation waves.
(3) The rotary detonation combustion chamber is simple in structure, high in reliability and free of special structural requirements for igniters.
The present invention is described in further detail below with reference to the attached drawing figures.
Drawings
FIG. 1 is an axial cross-sectional view of the general structure of a rotary detonation combustor of the present invention.
FIG. 2 is a circumferential section A-A of the general structure of a rotary detonation combustor of the present invention.
Detailed Description
For the purpose of illustrating the technical solutions and technical objects of the present invention, the present invention will be further described with reference to the accompanying drawings and specific embodiments.
With reference to fig. 1-2, the rotary detonation combustor for unidirectionally propagating detonation waves of the invention comprises a combustor outer ring 1, a combustor inner ring 2, a mounting seat 3 and an igniter;
the combustion chamber inner ring 2 is coaxial with the combustion chamber outer ring 1; the outer wall surface of the combustion chamber inner ring 2 is a cylindrical surface; the inner wall surface of the combustion chamber outer ring 1 is a periodic gradually-reducing and suddenly-expanding molded surface, the periodicity is n, n is larger than or equal to 2, the curvature radius of the inner wall surface of the gradually-reducing section is gradually reduced, and a step surface 1-1 is formed between the suddenly-expanding section and the next periodic molded surface, so that the one-way transmission of the rotary detonation wave is realized, and the transmission direction of the rotary detonation wave is controlled. The mounting seat 3 is arranged at the beginning of the tapered section along the combustion chamber outer ring 1 so as to improve the capability of inhibiting the generation of reverse detonation waves in the initiation stage of the rotary detonation waves. The igniter is provided on the mount 3 to ignite a combustion cavity formed between the combustion chamber outer ring 1 and the combustion chamber inner ring 2.
Preferably, the mounting seat 3 is installed near the entrance of the combustion chamber to improve the success rate of detonation.
Preferably, the mounting seat 3 is in threaded connection with the outer ring 1 of the combustion chamber, so that different mounting seats 3 can be conveniently dismounted and replaced, and the igniter can be conveniently replaced.
In the combustion chamber, in the initiation stage of the rotary detonation wave, an igniter arranged on the mounting seat 3 generates flame jet flow and enters the combustion chamber, and the flame jet flow is obstructed by a sudden expansion step surface 1-1 on the inner wall surface of an outer ring 1 of the combustion chamber and cannot be transmitted when the flame jet flow is reversely transmitted in the combustion chamber; the flame is not limited when propagating in the positive direction of the combustion chamber, and the flame propagates in the positive direction and develops into detonation waves. Therefore, the generation of reverse detonation waves is restrained in the detonation stage of the rotary detonation waves. In the stage of propagation of the rotary detonation wave, if the detonation wave which is reversely propagated is generated in the combustion chamber, when the reverse detonation wave is propagated to the sudden-expansion step surface 1-1 on the inner wall surface of the combustion chamber outer ring 1, the intensity of the detonation wave is mainly concentrated near the inner wall surface of the combustion chamber outer ring 1, and the reverse detonation wave is decoupled after colliding with the sudden-expansion step surface 1-1. Thereby, the propagation of the reverse detonation wave is prevented in the propagation stage of the rotation detonation wave. Compared with the existing rotary detonation combustor, the rotary detonation combustor provided by the invention can ensure detonation and stable propagation of detonation waves, can enable the rotary detonation waves to be propagated in a single direction, and is controllable in propagation direction.
Claims (3)
1. A rotary detonation combustion chamber enabling detonation waves to be transmitted in a single direction is characterized by comprising a combustion chamber outer ring (1), a combustion chamber inner ring (2), a mounting seat (3) and an igniter;
the combustion chamber inner ring (2) is coaxial with the combustion chamber outer ring (1); the outer wall surface of the combustion chamber inner ring (2) is a cylindrical surface; the inner wall surface of the combustion chamber outer ring (1) is a periodic gradually-reducing and suddenly-expanding molded surface, the period number is n (n is more than or equal to 2), the curvature radius of the inner wall surface of the gradually-reducing section is gradually reduced, and a step surface (1-1) is formed between the suddenly-expanding section and the next periodic molded surface; the mounting seat (3) is arranged at the beginning of the reducing section along the outer ring (1) of the combustion chamber; the igniter is arranged on the mounting seat (3).
2. A combustion chamber according to claim 1, characterized in that the mounting seat (3) is mounted close to the combustion chamber inlet.
3. A combustion chamber according to claim 1, characterized in that the mounting seat (3) is screwed to the outer combustion chamber ring (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811533081.6A CN109737457B (en) | 2018-12-14 | 2018-12-14 | Rotary detonation combustion chamber enabling detonation waves to be transmitted in one direction |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811533081.6A CN109737457B (en) | 2018-12-14 | 2018-12-14 | Rotary detonation combustion chamber enabling detonation waves to be transmitted in one direction |
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| CN109737457A CN109737457A (en) | 2019-05-10 |
| CN109737457B true CN109737457B (en) | 2020-06-19 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110469871B (en) * | 2019-09-09 | 2020-08-21 | 西北工业大学 | Stirling cycle-based compound cooling rotary detonation combustion chamber |
| US11572840B2 (en) * | 2019-12-03 | 2023-02-07 | General Electric Company | Multi-mode combustion control for a rotating detonation combustion system |
| CN111197765B (en) * | 2019-12-18 | 2021-08-03 | 南京理工大学 | Rotary detonation combustion chamber |
| CN111594341B (en) * | 2020-05-07 | 2022-07-22 | 西北工业大学 | One-way priming device of rotary detonation engine |
| CN112066417B (en) * | 2020-08-20 | 2021-12-10 | 西北工业大学 | Rotary detonation combustion method for eliminating gyro moment in flight process |
| CN113154458B (en) * | 2021-04-23 | 2022-08-02 | 中国人民解放军国防科技大学 | Continuous rotation detonation combustion chamber and ramjet |
| CN113757725B (en) * | 2021-06-26 | 2022-08-02 | 中国人民解放军空军工程大学 | Rotary detonation combustion chamber modal control flow channel configuration |
| CN114060854A (en) * | 2021-11-08 | 2022-02-18 | 北京化工大学 | Rotary detonation engine for concentrating detonation waves at inner side of combustion chamber |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103675194A (en) * | 2013-12-18 | 2014-03-26 | 西安近代化学研究所 | Testing device and method for deflagration to detonation transition |
| CN103899436A (en) * | 2014-04-01 | 2014-07-02 | 西北工业大学 | Spiral multi-channel pulse detonation engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10436110B2 (en) * | 2017-03-27 | 2019-10-08 | United Technologies Corporation | Rotating detonation engine upstream wave arrestor |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103675194A (en) * | 2013-12-18 | 2014-03-26 | 西安近代化学研究所 | Testing device and method for deflagration to detonation transition |
| CN103899436A (en) * | 2014-04-01 | 2014-07-02 | 西北工业大学 | Spiral multi-channel pulse detonation engine |
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