CN112166669B - Blunt type injection turbulent ring ignition and flame stabilization device - Google Patents
Blunt type injection turbulent ring ignition and flame stabilization device Download PDFInfo
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- CN112166669B CN112166669B CN201218005979.3A CN201218005979A CN112166669B CN 112166669 B CN112166669 B CN 112166669B CN 201218005979 A CN201218005979 A CN 201218005979A CN 112166669 B CN112166669 B CN 112166669B
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Abstract
A bluff body type injection turbulator ring ignition and flame stabilization device, comprising: injector (1), combustion chamber (2), electric igniter (3) and turbulent ring (4), its characterized in that: the injector is provided with a gas component channel and a liquid component nozzle, wherein the liquid component nozzle is a centrifugal nozzle (12) and is arranged at the central part of the inner wall of the injector (1), the gas component channel is a straight-flow hole (11) and is uniformly distributed at the periphery of the centrifugal nozzle (12) along the circumferential direction, the central line of the straight-flow hole (11) and the injection surface form an included angle alpha, and the nozzle of the straight-flow hole (11) points to the inner side wall surface of the combustion chamber; a turbulent ring (4) is arranged at an injection surface outlet of the injector, one end of the turbulent ring (4) is abutted against the inner wall of the injection surface of the injector, the side surface of the turbulent ring is tightly attached to the inner surface of the combustion chamber, and an electric igniter is arranged on the side wall of the combustion chamber close to the downstream of the turbulent ring.
Description
Technical Field
The invention relates to an ignition and flame stabilization device, in particular to a blunt body type injection turbulent ring ignition and flame stabilization device.
Background
The injector is a key component of the engine and determines the combustion efficiency and thermal state of the injector face plate and chamber walls of the combustion chamber, and for a two-component non-pyrophoric propellant engine, the ignition performance, response characteristics, and pulse capability of the generator. At present, most of the two-component engines adopt liquid/liquid self-ignition (non-self-ignition) propellants, the technology of injectors of the engines is mature, a set of complete design test screening criteria is established, but the liquid/liquid injectors are not suitable for gas/liquid non-self-ignition propellants (such as air/kerosene); the gas/liquid non-autoignition propellant nozzles are only applied to some high-thrust engines, the nozzles only relate to mixing problems, do not relate to engine ignition, pulse operation, thermal protection of a thrust chamber and the like, and the gas/liquid non-autoignition propellant nozzles are a key problem which needs to be solved by injectors of low-thrust engines. In general, a low-thrust gas/liquid bipropellant non-spontaneous-combustion propellant engine injector is still blank in China.
At present, no description or report of similar technologies to the technology of the invention is found at home, and similar data at home and abroad is not collected.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, the blunt body type injection turbulent ring ignition and flame stabilization device for the gas/liquid bipropellant non-spontaneous combustion propellant engine is provided, the problems of ignition, flame stabilization and the like of the gas/liquid bipropellant non-spontaneous combustion propellant are solved, and the advantages of a stable state/pulse double working mode of the gas/liquid bipropellant non-spontaneous combustion propellant engine and the like are achieved.
The technical solution of the invention is as follows:
a bluff body type injection turbulator ring ignition and flame stabilization device, comprising: the combustor comprises an injector 1, a combustion chamber 2, an electric igniter 3 and a turbulent flow ring 4, and is characterized in that: the injector is provided with a gas component channel and a liquid component nozzle, wherein the liquid component nozzle is a centrifugal nozzle 12 and is arranged at the central part of the inner wall of the injector 1, the gas component channel is a straight flow hole 11 and is uniformly distributed at the periphery of the centrifugal nozzle 12 along the circumferential direction, the central line of the straight flow hole 11 and an injection surface form an included angle alpha, and a nozzle of the straight flow hole 11 points to the inner side wall surface of the combustion chamber; a turbulent ring 4 is arranged at an outlet of an injection surface of the injector, one end of the turbulent ring 4 abuts against the inner wall of the injection surface of the injector, the side surface of the turbulent ring is tightly attached to the inner surface of a combustion chamber, and an electric igniter is arranged on the side wall of the combustion chamber close to the downstream of the turbulent ring.
Further, the adopted liquid component can be hydrocarbon fuel, and the adopted gaseous component is air.
Furthermore, the gaseous component channel can also be a circular seam type direct current channel.
Furthermore, the included angle alpha between the central line of the circular seam type direct current channel and the injection surface is about 15-30 degrees.
Further, the outer end of the turbulent ring has a radial protrusion part, and the height H of the radial protrusion part is not more than 5 mm.
Further, the distance L between the turbulent ring and the injection surface is between 1/3 and 2/3 of the diameter D of the combustion chamber.
Furthermore, the electric igniter is parallel to or retracted from or extended out of the inner wall surface of the combustion chamber by about 2mm, and the distance S between the electric igniter and the outer end of the turbulence ring is about 5-10 mm.
The blunt body type injection turbulent ring ignition and flame stabilization device is applied to an air/kerosene fuel gas generator, so that the reliable ignition and pulse work of the engine are realized; the blunt body type injection turbulent ring ignition and flame stabilization device has strong design expansibility, can be suitable for generators with power of ten kilowatts to hundreds of kilowatts, and covers the power type spectrum of a low-power generator.
The blunt body type injection turbulent ring ignition and flame stabilization device adopts the blunt body type injection turbulent ring structure, realizes the difficult problems of ignition and flame stabilization of the gas/liquid bipropellant non-spontaneous combustion propellant, obtains the advantages of steady state/pulse double working mode of the gas/liquid bipropellant non-spontaneous combustion propellant engine and the like, and fills the domestic blank.
Drawings
FIG. 1 is a schematic longitudinal cross-sectional view of a bluff body injection turbulator ring ignition and flame stabilization device in accordance with the present invention.
The notations in the figure are:
l: axial length of the spoiler ring; h: the height of the turbulent flow ring;
s: the distance between the electric igniter and the spoiler ring; d: the diameter of the combustion chamber.
α: the central line of the gas component injection hole forms an included angle with the injection surface.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Fig. 1 is a schematic longitudinal sectional view of a blunt body type injection turbulent ring ignition and flame stabilization device according to the present invention, which is an embodiment of an air/kerosene gas generator comprising an injector 1, a combustion chamber 2, an electric igniter 3, and a turbulent ring 4.
The injector is provided with 6 air channels and kerosene nozzles, wherein the kerosene nozzles are centrifugal nozzles 12 and are arranged in the center of the injector, the number of the air channels is 6, the air channels are uniformly distributed on the periphery of the kerosene nozzles along the circumferential direction, the included angle between the central line of each straight flow hole and an injection surface is 30 degrees, and the nozzles point to the inner wall surface of the combustion chamber; a turbulent ring is arranged at an outlet of an injection surface of the injector, the turbulent ring has a blocking effect on mixed gas and generates a low-speed backflow area, and the length L and the height H of the low-speed backflow area influence the form of the backflow area; an electric igniter is arranged on the side wall of the combustion chamber close to the downstream of the turbulence ring, is in threaded connection with the combustion chamber and is sealed by an aluminum gasket end face. The blunt body type injection turbulent ring ignition and flame stabilization device comprises: the combustor comprises an injector 1, a combustion chamber 2, an electric igniter 3 and a turbulent flow ring 4, and is characterized in that: the injector is provided with a gas component channel and a liquid component nozzle, wherein the liquid component nozzle is a centrifugal nozzle 12 and is arranged at the central part of the inner wall of the injector 1, the gas component channel is a straight flow hole 11 and is uniformly distributed at the periphery of the centrifugal nozzle 12 along the circumferential direction, the central line of the straight flow hole 11 and an injection surface form an included angle alpha, and a nozzle of the straight flow hole 11 points to the inner side wall surface of the combustion chamber; a turbulent ring 4 is arranged at an outlet of an injection surface of the injector, one end of the turbulent ring 4 abuts against the inner wall of the injection surface of the injector, the side surface of the turbulent ring is tightly attached to the inner surface of a combustion chamber, and an electric igniter is arranged on the side wall of the combustion chamber close to the downstream of the turbulent ring. The liquid component can be hydrocarbon fuel, and the gaseous component is air. The gaseous component channel can also be a circular seam type direct current channel. The included angle alpha between the central line of the circular seam type direct current channel and the injection surface is about 15-30 degrees. The outer end of the turbulent ring has a radial projection with a height H not exceeding 5 mm. The distance L between the turbulent ring and the injection surface is 1/3-2/3 of the diameter D of the combustion chamber. The electric igniter is parallel to or retracted from or extended out of the inner wall surface of the combustion chamber by about 2mm, and the interval S between the electric igniter and the outer end of the turbulence ring is about 5-10 mm.
The air is jetted to the inner wall of the combustion chamber along a straight flow hole or an annular seam type straight flow channel and the face of the injector at a certain included angle, which is equivalent to that the airflow moving along the axis is disturbed by the bluff body in the incoming flow direction to change the streamline direction, and under the blocking action of the turbulent flow ring, a low-speed backflow area and a low-speed standing vortex are respectively generated in the middle of the front end of the combustion chamber and near the electric igniter, the electric spark generated by the electric igniter ignites the air/kerosene mixed gas at the low-speed standing vortex nearby the electric igniter to form an initial ignition source, the initial ignition source then ignites the low-speed backflow main flow in the middle of the front end of the combustion chamber, and the formed high-temperature and high-pressure fuel gas is finally jetted by the nozzle.
Claims (2)
1. A bluff body type injection turbulator ring ignition and flame stabilization device, comprising: injector (1), combustion chamber (2), electric igniter (3) and turbulent ring (4), its characterized in that: the injector is provided with a gas component channel and a liquid component nozzle, wherein the liquid component nozzle is a centrifugal nozzle (12) and is arranged at the central part of the inner wall of the injector (1), the gas component channel is a straight-flow hole (11) and is uniformly distributed at the periphery of the centrifugal nozzle (12) along the circumferential direction, the central line of the straight-flow hole (11) and the injection surface form an included angle alpha, and the nozzle of the straight-flow hole (11) points to the inner side wall surface of the combustion chamber; a turbulent ring (4) is arranged at an injection surface outlet of the injector, one end of the turbulent ring (4) is abutted against the inner wall of the injection surface of the injector, the side surface of the turbulent ring is tightly attached to the inner surface of a combustion chamber, and an electric igniter is arranged on the side wall of the combustion chamber close to the downstream of the turbulent ring;
air is sprayed to the inner wall of the combustion chamber along a certain included angle formed by the straight-flow hole and the injector surface, which is equivalent to that the airflow moving along the axis is disturbed by the blunt body in the incoming flow direction to change the streamline direction, and a low-speed backflow area and a low-speed standing vortex are respectively generated in the middle of the front end of the combustion chamber (2) and near the electric igniter (3) under the blocking action of the turbulence ring (4), the electric spark generated by the electric igniter ignites the air/kerosene mixed gas at the low-speed standing vortex nearby to form an initial ignition source, the initial ignition source ignites the low-speed backflow main flow in the middle of the front end of the combustion chamber (2), and the formed high-temperature and high-pressure fuel gas is finally sprayed out from the nozzle to form thrust through the combustion chamber (2);
the outer end of the turbulence ring is provided with a radial protruding part, and the height H of the radial protruding part is not more than 5 mm;
the distance L between the turbulent ring and the injection surface is between 1/3 and 2/3 of the diameter D of the combustion chamber;
the gaseous component adopted in the gaseous component channel is air;
the liquid component adopted in the liquid component nozzle is a hydrocarbon fuel;
the electric igniter is parallel to or retracted from or extended out of the inner wall surface of the combustion chamber by about 2mm, and the interval S between the electric igniter and the outer end of the turbulence ring is about 5-10 mm.
2. The bluff body injection turbulent ring ignition and flame stabilization device of claim 1, wherein said gaseous component channel is either an annular slot type direct current channel; the included angle between the central line of the circular seam type direct current channel and the injection surface is 15-30 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201218005979.3A CN112166669B (en) | 2012-11-22 | 2012-11-22 | Blunt type injection turbulent ring ignition and flame stabilization device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201218005979.3A CN112166669B (en) | 2012-11-22 | 2012-11-22 | Blunt type injection turbulent ring ignition and flame stabilization device |
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| CN112166669B true CN112166669B (en) | 2016-01-27 |
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| CN201218005979.3A Active CN112166669B (en) | 2012-11-22 | 2012-11-22 | Blunt type injection turbulent ring ignition and flame stabilization device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115127121A (en) * | 2022-06-15 | 2022-09-30 | 北京航空航天大学 | Flame-stabilizing premixed combustion device and aircraft engine simulation test equipment |
| CN115653788A (en) * | 2022-12-27 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | Hydrogen peroxide kerosene dual-component gas generator and working method thereof |
-
2012
- 2012-11-22 CN CN201218005979.3A patent/CN112166669B/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115127121A (en) * | 2022-06-15 | 2022-09-30 | 北京航空航天大学 | Flame-stabilizing premixed combustion device and aircraft engine simulation test equipment |
| CN115127121B (en) * | 2022-06-15 | 2024-01-12 | 北京航空航天大学 | Flame stabilizing premixing combustion device and aeroengine simulation test equipment |
| CN115653788A (en) * | 2022-12-27 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | Hydrogen peroxide kerosene dual-component gas generator and working method thereof |
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