CN111594340B - Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet - Google Patents
Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet Download PDFInfo
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- CN111594340B CN111594340B CN202010365949.7A CN202010365949A CN111594340B CN 111594340 B CN111594340 B CN 111594340B CN 202010365949 A CN202010365949 A CN 202010365949A CN 111594340 B CN111594340 B CN 111594340B
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- wedge surface
- detonation
- oblique
- nozzle
- jet flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
- F02K1/30—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for varying effective area of jet pipe or nozzle
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention belongs to the field of oblique detonation engines, and particularly relates to a wedge surface structure for controlling oblique detonation wave detonation by utilizing thermal jet. A nozzle in the same direction as the jet flow is arranged at one end, close to an engine air inlet, of the flat wedge surface, detonation products of the engine are introduced and are ejected from the nozzle to generate hot jet flow, the ejected hot jet flow forms an air wedge surface, the air wedge surface induces a new oblique shock wave, and the oblique detonation wave is stabilized at the jet flow position. According to the invention, the equidirectional nozzle is arranged on the basis of the straight wedge surface, the detonation product of the engine is introduced and is sprayed out from the nozzle, the sprayed hot jet forms a gas wedge surface, the gas wedge surface induces a new oblique shock wave, and the detonation of the oblique shock wave is realized through the temperature rise of the oblique shock wave; the wedge surface structure stabilizes the oblique detonation waves at the optimal position through the hot jet flow under a small wedge surface angle, and simultaneously ensures that the resistance is minimum and the total pressure loss is minimum, so that the thrust performance is optimized.
Description
Technical Field
The invention belongs to the field of oblique detonation engines, and particularly relates to a wedge surface structure for controlling oblique detonation wave detonation by utilizing thermal jet.
Background
The inclined detonation engine is the most ideal engine for hypersonic aircrafts. The working principle of the oblique detonation engine is as follows: supersonic incoming flow is impacted and compressed on the wedge surface to form oblique shock waves, the temperature and the pressure are increased and the speed is reduced after the oblique shock waves, and the oblique detonation waves are detonated after the oblique shock waves pass through a section of induction section.
According to the working characteristics of the oblique detonation engine, the wedge face angle cannot be too large, the mixture can be prematurely dissociated due to the too large wedge face angle, the thrust performance is influenced, and meanwhile, the resistance can be increased due to the too large wedge face angle; the wedge angle cannot be too small because the smaller the wedge angle, the lower the post-oblique shock static temperature, and the longer the induction length, which increases the size and thus the weight of the engine. And if a straight wedge surface is adopted, the detonation wave is difficult to control by changing the angle of the wedge surface.
Disclosure of Invention
The invention aims to provide a wedge surface structure for controlling detonation of an oblique detonation wave by utilizing hot jet.
The technical solution for realizing the purpose of the invention is as follows: a wedge surface structure for controlling the detonation of oblique detonation waves by using thermal jet is characterized in that a nozzle parallel to a flat wedge surface is arranged at one end, close to an engine air inlet, of the flat wedge surface, detonation products of an engine are introduced and are ejected from the nozzle to generate thermal jet, the ejected thermal jet forms a gas wedge surface, and the gas wedge surface induces a new oblique shock wave to stabilize the oblique detonation waves at a jet position.
Further, the spout and the flat wedge surface remain parallel.
Further, the position of the nozzle on the wedge surface is adjusted, so that the position of the jet flow is changed.
Further, the shape of the nozzle is adjusted to vary the intensity of the hot jet.
Compared with the prior art, the invention has the remarkable advantages that:
(1) according to the invention, the equidirectional nozzle is arranged on the basis of the straight wedge surface, the detonation product of the engine is introduced and is sprayed out from the nozzle, the sprayed hot jet forms a gas wedge surface, the gas wedge surface induces a new oblique shock wave, and the detonation of the oblique shock wave is realized through the temperature rise of the oblique shock wave;
(2) the position of the equidirectional nozzles can be changed on the wedge surface, and the shapes of the equidirectional nozzles can be adjusted, so that the oblique detonation waves are always stabilized at the optimal position, and the maximum thrust is realized; the strength and the position of the thermal jet are changed according to actual requirements, so that the accurate control of the detonation position of the oblique detonation wave is realized.
(3) The wedge surface structure stabilizes the oblique detonation waves at the optimal position through the hot jet flow under a small wedge surface angle, and simultaneously ensures that the resistance is minimum and the total pressure loss is minimum, so that the thrust performance is optimized.
Drawings
Fig. 1 is a schematic view of a conventional flat wedge surface.
FIG. 2 is a schematic diagram of a wedge surface containing co-rotating thermal jets.
Fig. 3 is a thermal jet wedge equipped on an engine, wherein (a) is a general schematic diagram of the engine, and (b) is a schematic diagram of wedge installation.
Detailed Description
The present invention is described in further detail below with reference to the attached drawing figures.
As shown in fig. 2 and 3, the present invention provides a wedge surface structure for controlling detonation of an oblique detonation wave by using a thermal jet, which aims to stabilize the oblique detonation wave at an optimal position by the thermal jet under a small wedge surface angle, and simultaneously minimize resistance and total pressure loss, thereby optimizing thrust performance.
According to the detonation jet nozzle, the nozzle is additionally arranged on the basis of the flat wedge surface, detonation products of an engine are introduced and are ejected from the nozzle, the ejected hot jet forms a gas wedge surface, the gas wedge surface induces a new oblique shock wave, and the detonation of the oblique shock wave is realized through the temperature rise of the oblique shock wave.
The intensity of the hot jet can be adjusted according to actual flight conditions, and then the detonation position of the oblique detonation wave is controlled.
The jet position can be changed according to actual requirements, so that the detonation position of the oblique detonation wave is controlled.
The nozzle and the wedge surface are kept parallel to prevent the jet flow from being too strong to cause huge total pressure loss, and the nozzle can slide on the wedge surface to change the position of the hot jet flow so as to control the initiation position of the oblique detonation wave. The shape of the nozzle can be adjusted to vary the jet intensity according to flight conditions to ensure optimum thrust performance.
Claims (3)
1. A wedge surface structure for controlling oblique detonation waves to detonate by utilizing hot jet flow is characterized in that a nozzle parallel to a straight wedge surface is arranged at one end, close to an engine air inlet channel, of the straight wedge surface, detonation products of an engine are introduced, the pressure of the detonation products is adjusted through the section of the nozzle to be larger than the environmental pressure of jet flow, under-expansion jet flow is generated by being sprayed out of the nozzle, the sprayed under-expansion hot jet flow forms a gas wedge surface with an angle larger than that of a basic solid wedge surface, the gas wedge surface induces a new oblique shock wave, and the oblique detonation waves are stabilized at the position of the jet flow; the spout and the flat wedge surface remain parallel.
2. The wedge surface structure of claim 1 wherein the hot jet pressure needs to be greater than the jet ambient pressure in order to form an under-expanded jet.
3. The wedge surface structure of claim 2, wherein the position of said nozzle orifice is adjusted to change the thermal jet position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010365949.7A CN111594340B (en) | 2020-04-30 | 2020-04-30 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010365949.7A CN111594340B (en) | 2020-04-30 | 2020-04-30 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111594340A CN111594340A (en) | 2020-08-28 |
| CN111594340B true CN111594340B (en) | 2022-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010365949.7A Active CN111594340B (en) | 2020-04-30 | 2020-04-30 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
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| Country | Link |
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| CN (1) | CN111594340B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112594737B (en) * | 2020-12-10 | 2022-04-29 | 北京理工大学 | Oblique detonation wave stationary control method and variable-geometry combustion chamber |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103899433A (en) * | 2014-03-31 | 2014-07-02 | 西北工业大学 | Novel thrust vectoring nozzle structure adopting shock vectoring controlling |
| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106014683A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Pressurization flow control device-containing SERN structure for TBCC |
| CN106930864A (en) * | 2017-03-29 | 2017-07-07 | 中国人民解放军国防科学技术大学 | A kind of supersonic speed detonation engine and its propulsion system |
| CN109026441A (en) * | 2018-09-27 | 2018-12-18 | 北京理工大学 | Shock wave lures burning ramjet and shock wave to lure combustion punching press starting method |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8359825B2 (en) * | 2008-05-21 | 2013-01-29 | Florida State University Research Foundation | Microjet creation and control of shock waves |
| PL420340A1 (en) * | 2017-01-30 | 2018-08-13 | General Electric Company | Reducing of the outlet nozzle shock wave |
| CN108915893B (en) * | 2018-06-27 | 2020-09-25 | 江苏大学 | Multi-tube spiral pulse detonation engine |
-
2020
- 2020-04-30 CN CN202010365949.7A patent/CN111594340B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103899433A (en) * | 2014-03-31 | 2014-07-02 | 西北工业大学 | Novel thrust vectoring nozzle structure adopting shock vectoring controlling |
| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106014683A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Pressurization flow control device-containing SERN structure for TBCC |
| CN106930864A (en) * | 2017-03-29 | 2017-07-07 | 中国人民解放军国防科学技术大学 | A kind of supersonic speed detonation engine and its propulsion system |
| CN109026441A (en) * | 2018-09-27 | 2018-12-18 | 北京理工大学 | Shock wave lures burning ramjet and shock wave to lure combustion punching press starting method |
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| CN111594340A (en) | 2020-08-28 |
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