CN115143489A - Combustion chamber suitable for full-ring large-scale cyclone air intake - Google Patents
Combustion chamber suitable for full-ring large-scale cyclone air intake Download PDFInfo
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- CN115143489A CN115143489A CN202210677376.0A CN202210677376A CN115143489A CN 115143489 A CN115143489 A CN 115143489A CN 202210677376 A CN202210677376 A CN 202210677376A CN 115143489 A CN115143489 A CN 115143489A
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- swirl
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cyclones (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a combustion chamber suitable for full-ring large-scale cyclone air intake, which comprises a shell, a flame tube and M cyclone blades, wherein the flame tube is arranged in the shell; the flame tube comprises a rotational flow part and a combustion part which are coaxially and fixedly connected; the center of the end surface of the swirling part far away from the combustion part is provided with a blind hole which penetrates through the swirling part and extends into the combustion part to be used as a main flow air inlet channel; n main flow jet holes communicated with the main flow air inlet channel are uniformly arranged on the outer wall of the combustion part in the circumferential direction; the flame tube is arranged in the shell and is coaxial with the shell; m swirl blades are circumferentially and uniformly arranged between the outer shell and the swirl part of the flame tube. The invention forms a backflow area through the interaction of the full-ring air inlet rotational flow and the main flow incident from the jet hole, and is used for oil-gas mixing and flame stabilization, the airflow in the combustion chamber is full-ring scale rotational flow, and the outlet airflow has rotational quantity and is matched with the rear-end impeller machinery, thereby being beneficial to improving the rotational speed of the impeller machinery and improving the output efficiency and power.
Description
Technical Field
The invention relates to the field of heat energy power, in particular to a combustion chamber suitable for full-ring large-scale cyclone air intake.
Background
With the continuous improvement of the overall performance requirements of the current aero-engine, the future aero-engine must have the characteristics of ultralow emission, high efficiency and low cost while maintaining the ignition performance and the lean blowout performance of the existing engine, and the development of the advanced combustion chamber design is promoted by the dual requirements of improving the performance and reducing the emission.
In order to obtain high efficiency and high power output of current aircraft turbine engines, rapid rotation of the turbine blades is required, which is achieved by impinging high temperature, high velocity gas jets between nozzle guide vanes against the turbine blades, where the gas undergoes accelerated expansion, and therefore, the mechanical and thermal stresses on the turbine blades are so high that the output efficiency of the engine is limited by the material properties of the turbine blades. Even if high temperature, high velocity gas jets are readily available, these jets cannot be effectively utilized due to the shortened life of the turbine blades. By diluting the exhaust gas to produce a gas jet of moderate temperature and velocity and limiting the rotational speed of the turbine, a longer service life can be achieved, but this also results in inefficiency and limited power output. Another weakness of currently available aero turbine engines is the thermodynamic cycle, the ideal aero engine cycle is the brayton cycle, but in actual operation, the gas is retarded as it exits the compressor through the non-rotating stator vanes before entering the combustion chamber, and the gas expands through the nozzle vanes to drive the turbine wheel, the various stationary components of the combustion chamber, and the pressure drop due to friction with the swirling environment, resulting in an actual thermodynamic cycle far from the ideal brayton cycle.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art and provides a combustion chamber suitable for full-ring large-scale cyclone air intake, entrainment is generated through full-ring-scale cyclone air intake and interacts with main flow jet hole jet flow, a backflow area is formed behind the front wall surface of a flame tube, and the effects of oil-gas mixing and flame stabilization are achieved.
The invention adopts the following technical scheme for solving the technical problems:
a combustion chamber suitable for full-ring large-scale cyclone air intake comprises a shell, a flame tube and M cyclone blades, wherein M is a natural number more than 2;
the shell is a hollow cylinder with openings at two ends;
the flame tube comprises a rotational flow part and a combustion part; the swirl part and the combustion part are both cylinders, the radius of the end surface of the swirl part is larger than that of the end surface of the combustion part, the swirl part and the combustion part are coaxially and fixedly connected, and the swirl part is positioned at the upstream of the combustion part; the center of the end surface of the swirl part, which is far away from the combustion part, is provided with a blind hole which penetrates through the swirl part and extends into the combustion part to be used as a main flow air inlet channel; n main flow jet holes communicated with a main flow air inlet channel are uniformly arranged on the outer wall of the combustion part in the circumferential direction, and N is a natural number greater than 2;
the flame tube is arranged in the shell and is coaxial with the shell; the M swirl blades are circumferentially and uniformly arranged between the flame tube swirl portion and the shell, the uniform end is fixedly connected with the inner wall of the shell, the other end is fixedly connected with the outer wall of the flame tube swirl portion, and the mounting angles are equal.
As a further optimization scheme of the combustion chamber suitable for full-ring large-scale cyclone air intake, the axial lines of the main flow jet holes are perpendicularly intersected with the axial line of the combustion part.
As a further optimization scheme of the combustion chamber suitable for full-ring large-scale cyclone air intake, the total area of the cross sections of the N main flow jet holes is smaller than the area of the cross section of the main flow air intake channel.
As a further optimization scheme of the combustion chamber suitable for full-ring large-scale cyclone air intake, the distance between the cyclone part of the flame tube and the shell is 5-10mm, and the installation angles of the cyclone blades are 45 degrees.
As a further optimization scheme of the combustion chamber suitable for full-ring large-scale swirl air intake, the distance between the axis of the main flow jet hole and the end face of the downstream of the swirl part of the flame tube is Q, the distance between the outer wall of the swirl part and the outer wall of the combustion part is P, and the ratio of Q to P is 1.25.
As a further optimization scheme of the combustion chamber suitable for full-ring large-scale cyclone air intake, the height of the main flow jet hole is 35mm, the height of the main flow jet hole meets the rectification requirement, and the main flow air intake direct injection is guaranteed not to be deflected.
As a further optimization scheme of the combustion chamber suitable for full-ring large-scale cyclone air intake, the range of N is 12 to 18, and a good intercepting effect is formed on the cyclone air intake.
Compared with the prior art, the invention adopting the technical scheme has the following technical effects:
1. the full-ring-scale rotational flow is realized in a smaller structure, so that the matching with an impeller is facilitated, and higher power is output;
2. the establishment of a reflux area is realized in a smaller space by adopting the combined action of the structural parameters and the pneumatic parameters;
3. when the full-ring rotational flow is generated, the cooling effect of the wall surface is considered, and the pressure of the cooling structure design is reduced.
Drawings
FIG. 1 is a schematic perspective cut-away view of the present invention;
FIG. 2 is a partial schematic structural view of the present invention;
fig. 3 is a cross-sectional view of the present invention.
In the figure, 1-shell, 2-flame tube, 3-cyclone air inlet channel, 4-cyclone blade, 5-main flow air inlet channel, 6-main flow jet hole, 7-end surface of downstream cyclone part of flame tube, 8-reflux zone.
Detailed Description
The technical scheme of the invention is further explained in detail by combining the attached drawings:
the present invention may be embodied in many different forms and should not be construed as 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 invention to those skilled in the art. In the drawings, components are exaggerated for clarity.
In order to reduce the pressure drop generated by impeller machinery and improve the thermodynamic performance potential of an engine, the invention provides a combustion chamber suitable for full-ring large-scale cyclone air intake. The device has the advantages that the full-circle scale cyclone air inflow is adopted, the outlet airflow of the device is also influenced by the cyclone, the outlet airflow has rotation quantity, the outlet airflow can directly act on the movable blade with high reaction degree of the gas turbine, large torque can be generated, and high power can be output.
As shown in fig. 1, 2 and 3, the invention discloses a combustion chamber suitable for full-ring large-scale swirl intake, which comprises a shell, a flame tube and M swirl blades, wherein M is a natural number greater than 2;
the shell is a hollow cylinder with openings at two ends;
the flame tube comprises a rotational flow part and a combustion part; the swirl part and the combustion part are both cylinders, the radius of the end surface of the swirl part is larger than that of the end surface of the combustion part, the swirl part and the combustion part are coaxially and fixedly connected, and the swirl part is positioned at the upstream of the combustion part; the center of the end surface of the swirl part, which is far away from the combustion part, is provided with a blind hole which penetrates through the swirl part and extends into the combustion part to be used as a main flow air inlet channel; n main flow jet holes communicated with a main flow air inlet channel are uniformly arranged on the outer wall of the combustion part in the circumferential direction, and N is a natural number greater than 2;
the flame tube is arranged in the shell, and the flame tube is arranged in the shell, coaxial with the housing; the M swirl blades are circumferentially and uniformly arranged between the flame tube swirl portion and the shell, the uniform end is fixedly connected with the inner wall of the shell, the other end is fixedly connected with the outer wall of the flame tube swirl portion, and the mounting angles are equal.
And the axes of the main flow jet holes are vertically intersected with the axis of the combustion part.
The total area of the cross sections of the N main flow jet holes is smaller than the area of the cross section of the main flow air inlet channel.
The distance between the swirl part of the flame tube and the shell is 5-10mm, and the mounting angles of swirl blades are all 45 degrees.
The distance between the axis of the main flow jet hole and the end face of the downstream of the swirl part of the flame tube is Q, the distance between the outer wall of the swirl part and the outer wall of the combustion part is P, and the ratio of Q to P is 1.25.
The height of mainstream jet hole is 35mm, and the high rectification demand that satisfies of mainstream jet hole guarantees that mainstream admits air and penetrates directly and do not deflect.
The range of N is 12 to 18, and a good intercepting effect is formed on the cyclone air inflow.
A rotational flow air inlet channel is formed between the flame tube rotational flow part and the shell, and a combustion cavity is formed between the flame tube combustion part and the shell. After the gas enters the rotational flow gas inlet channel, generating rotational flow, enabling the rotational flow to enter the combustion chamber along with the shell, and enabling the mainstream gas to enter the flame tube after being rectified by the mainstream jet hole through the mainstream gas inlet channel; the swirl inlet and the main stream inlet act in the flame tube, the flow field structure has entrainment effect, a backflow vortex is formed between the downstream end surface of the swirl part of the flame tube and the N main stream jet holes, and the generation of the backflow vortex can be used for oil-gas mixing and flame stabilization; the vortex structure in the backflow area can change along with the change of the pneumatic parameters and the structural parameters, and has certain regularity.
Part of the swirl intake air and the main flow intake air participate in the formation of the backflow zone, and part of the swirl intake air and the main flow intake air are used for cooling the physical wall surface in a combustion state.
The outlet airflow of the invention has a swirl angle, can be matched with the impeller machinery at the outlet, and is beneficial to improving the rotating speed of the impeller machinery and improving the output efficiency and power. The invention adopts a new structure to control the interaction of the rotational flow air intake and the main flow air intake, has good effects of oil-gas mixing and full-circle scale flame stabilization, improves the problems of the combustion chamber in the prior art, and has the characteristics of simple and compact structure and light weight.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A combustion chamber suitable for full-ring large-scale cyclone air intake is characterized by comprising a shell, a flame tube and M cyclone blades, wherein M is a natural number more than 2;
the shell is a hollow cylinder with openings at two ends;
the flame tube comprises a rotational flow part and a combustion part; the swirl part and the combustion part are both cylinders, the radius of the end surface of the swirl part is larger than that of the end surface of the combustion part, the swirl part and the combustion part are coaxially and fixedly connected, and the swirl part is positioned at the upstream of the combustion part; the center of the end surface of the swirl part, which is far away from the combustion part, is provided with a blind hole which penetrates through the swirl part and extends into the combustion part to be used as a main flow air inlet channel; n main flow jet holes communicated with a main flow air inlet channel are uniformly arranged on the outer wall of the combustion part in the circumferential direction, and N is a natural number larger than 2;
the flame tube is arranged in the shell and is coaxial with the shell; the M swirl blades are circumferentially and uniformly arranged between the flame tube swirl portion and the shell, the uniform end is fixedly connected with the inner wall of the shell, the other end is fixedly connected with the outer wall of the flame tube swirl portion, and the mounting angles are equal.
2. The combustion chamber accommodating full-ring large-scale swirl intake according to claim 1, wherein the axes of the main flow jet holes are perpendicular to the axis of the combustion part.
3. The combustion chamber accommodating full-ring large-scale swirl intake according to claim 1, wherein the total area of the cross sections of the N mainstream jet holes is smaller than the cross sectional area of the mainstream intake passage.
4. The combustor adapting to full-ring large-scale swirl intake air of claim 1, wherein the distance between the swirl part of the flame tube and the outer shell is 5-10mm, and the installation angles of swirl blades are all 45 degrees.
5. The combustion chamber of claim 2 adapted to full-ring large-scale swirl intake, wherein the distance between the axis of the main flow jet hole and the end face of the flame tube downstream of the swirl portion is Q, the distance between the outer wall of the swirl portion and the outer wall of the combustion portion is P, and the ratio of Q to P is 1.25.
6. The combustion chamber suitable for full-ring large-scale cyclone air intake according to claim 2, wherein the height of the main flow jet hole is 35mm, and the height of the main flow jet hole meets the rectification requirement, so that the main flow air intake direct injection is ensured not to be deflected.
7. The combustion chamber suitable for the full-ring large-scale swirl intake according to claim 1, wherein the range of N is 12 to 18, and a good intercepting effect is formed on the swirl intake.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210677376.0A CN115143489B (en) | 2022-06-15 | 2022-06-15 | Combustion chamber suitable for full-ring large-scale rotational flow air intake |
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| CN202210677376.0A CN115143489B (en) | 2022-06-15 | 2022-06-15 | Combustion chamber suitable for full-ring large-scale rotational flow air intake |
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| CN115143489A true CN115143489A (en) | 2022-10-04 |
| CN115143489B CN115143489B (en) | 2023-08-11 |
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Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB670968A (en) * | 1949-02-24 | 1952-04-30 | Ronald Guerjn Meschino | Vapourizing system for a gas turbine engine |
| GB2078364A (en) * | 1980-06-17 | 1982-01-06 | Bs & B Eng Co | Fuel inlet assemblies for fuel reactors |
| JPH0658543A (en) * | 1992-05-15 | 1994-03-01 | Toyota Motor Corp | Swirl type ring-shaped burner |
| DE69407565D1 (en) * | 1993-10-19 | 1998-02-05 | Europ Gas Turbines Ltd | FUEL INJECTION NOZZLE |
| JP2004162959A (en) * | 2002-11-11 | 2004-06-10 | Ishikawajima Harima Heavy Ind Co Ltd | Annular type spiral diffusion flame combustor |
| US20090199563A1 (en) * | 2008-02-07 | 2009-08-13 | Hamilton Sundstrand Corporation | Scalable pyrospin combustor |
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN103277811A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Single-cavity trapped vortex combustor |
| US20150176842A1 (en) * | 2013-12-24 | 2015-06-25 | Alstom Technology Ltd | Method for operating a combustor for a gas turbine and combustor for a gas turbine |
| CN104863751A (en) * | 2015-03-27 | 2015-08-26 | 冯志新 | Circular jet-propelled double-rotor turbofan aero-engine |
| CN105020744A (en) * | 2015-07-06 | 2015-11-04 | 南京航空航天大学 | Inclined-flow trapped-vortex combustor |
| CN107091486A (en) * | 2017-04-10 | 2017-08-25 | 西北工业大学 | A kind of after-burner annular flame barrel structure with cyclone |
| CN107726364A (en) * | 2017-09-26 | 2018-02-23 | 中国科学院工程热物理研究所 | A kind of vaporizer tube combustor |
| CN108131687A (en) * | 2017-12-14 | 2018-06-08 | 西北工业大学 | Liquidate the tiny engine burner inner liner of guide vane inside and outside a kind of band |
| CN108561896A (en) * | 2018-03-15 | 2018-09-21 | 西北工业大学 | A kind of tiny engine burner inner liner with twin-stage guide vane |
| US20200041131A1 (en) * | 2018-07-31 | 2020-02-06 | Hotstart, Inc. | Rotary Atomizer |
| CN110779042A (en) * | 2018-07-31 | 2020-02-11 | 中国人民解放军国防科技大学 | Rotary detonation combustion chamber and engine with same |
| CN110925799A (en) * | 2019-11-21 | 2020-03-27 | 北京航空航天大学 | Combustion chamber structure for suppressing combustion instability |
| CN210345531U (en) * | 2019-03-20 | 2020-04-17 | 北京驰宇空天技术发展有限公司 | Annular combustion chamber |
| CN111520754A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Novel miniature aeroengine combustion chamber |
| CN112945566A (en) * | 2021-03-15 | 2021-06-11 | 南京赛恩通航科技有限公司 | Simulation structure, test platform and test method of gas-distributing type annular combustion chamber |
| CN113685843A (en) * | 2021-08-26 | 2021-11-23 | 华能国际电力股份有限公司 | Rotary detonation combustion chamber based on swirler injection |
-
2022
- 2022-06-15 CN CN202210677376.0A patent/CN115143489B/en active Active
Patent Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB670968A (en) * | 1949-02-24 | 1952-04-30 | Ronald Guerjn Meschino | Vapourizing system for a gas turbine engine |
| GB2078364A (en) * | 1980-06-17 | 1982-01-06 | Bs & B Eng Co | Fuel inlet assemblies for fuel reactors |
| JPH0658543A (en) * | 1992-05-15 | 1994-03-01 | Toyota Motor Corp | Swirl type ring-shaped burner |
| DE69407565D1 (en) * | 1993-10-19 | 1998-02-05 | Europ Gas Turbines Ltd | FUEL INJECTION NOZZLE |
| JP2004162959A (en) * | 2002-11-11 | 2004-06-10 | Ishikawajima Harima Heavy Ind Co Ltd | Annular type spiral diffusion flame combustor |
| US20090199563A1 (en) * | 2008-02-07 | 2009-08-13 | Hamilton Sundstrand Corporation | Scalable pyrospin combustor |
| CN103196159A (en) * | 2013-03-18 | 2013-07-10 | 哈尔滨工程大学 | Annular grading trapped vortex combustor |
| CN103277811A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Single-cavity trapped vortex combustor |
| US20150176842A1 (en) * | 2013-12-24 | 2015-06-25 | Alstom Technology Ltd | Method for operating a combustor for a gas turbine and combustor for a gas turbine |
| CN104863751A (en) * | 2015-03-27 | 2015-08-26 | 冯志新 | Circular jet-propelled double-rotor turbofan aero-engine |
| CN105020744A (en) * | 2015-07-06 | 2015-11-04 | 南京航空航天大学 | Inclined-flow trapped-vortex combustor |
| CN107091486A (en) * | 2017-04-10 | 2017-08-25 | 西北工业大学 | A kind of after-burner annular flame barrel structure with cyclone |
| CN107726364A (en) * | 2017-09-26 | 2018-02-23 | 中国科学院工程热物理研究所 | A kind of vaporizer tube combustor |
| CN108131687A (en) * | 2017-12-14 | 2018-06-08 | 西北工业大学 | Liquidate the tiny engine burner inner liner of guide vane inside and outside a kind of band |
| CN108561896A (en) * | 2018-03-15 | 2018-09-21 | 西北工业大学 | A kind of tiny engine burner inner liner with twin-stage guide vane |
| US20200041131A1 (en) * | 2018-07-31 | 2020-02-06 | Hotstart, Inc. | Rotary Atomizer |
| CN110779042A (en) * | 2018-07-31 | 2020-02-11 | 中国人民解放军国防科技大学 | Rotary detonation combustion chamber and engine with same |
| CN210345531U (en) * | 2019-03-20 | 2020-04-17 | 北京驰宇空天技术发展有限公司 | Annular combustion chamber |
| CN110925799A (en) * | 2019-11-21 | 2020-03-27 | 北京航空航天大学 | Combustion chamber structure for suppressing combustion instability |
| CN111520754A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Novel miniature aeroengine combustion chamber |
| CN112945566A (en) * | 2021-03-15 | 2021-06-11 | 南京赛恩通航科技有限公司 | Simulation structure, test platform and test method of gas-distributing type annular combustion chamber |
| CN113685843A (en) * | 2021-08-26 | 2021-11-23 | 华能国际电力股份有限公司 | Rotary detonation combustion chamber based on swirler injection |
Non-Patent Citations (2)
| Title |
|---|
| 丁国玉: "套筒角度对三级旋流燃烧室燃烧性能的影响", 《推进技术》, vol. 38, no. 2, pages 376 - 384 * |
| 王云飙: "结构参数和涵道比对新型漏斗...合扩压器性能影响的数值研究", 《推进技术》, vol. 43, no. 4, pages 200761 - 1 * |
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| CN115143489B (en) | 2023-08-11 |
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Inventor after: Jin Yi Inventor after: Jin Baodong Inventor after: Yao Kanghong Inventor after: Zhang Kai Inventor after: Wang Yunbiao Inventor after: Wang Donghao Inventor before: Jin Baodong Inventor before: Jin Yi Inventor before: Yao Kanghong Inventor before: Zhang Kai Inventor before: Wang Yunbiao Inventor before: Wang Donghao |