CN114151200A

CN114151200A - Igniter

Info

Publication number: CN114151200A
Application number: CN202111222258.2A
Authority: CN
Inventors: 魏豪; 时远; 何鹏; 赵弦; 袁昌波; 黄阿勇; 曾宇晖; 郭凯; 李九龙; 张伟; 钟世林
Original assignee: AECC Sichuan Gas Turbine Research Institute
Current assignee: AECC Sichuan Gas Turbine Research Institute
Priority date: 2021-10-20
Filing date: 2021-10-20
Publication date: 2022-03-08

Abstract

The invention discloses an igniter structure, belongs to the technical field of ignition devices in a main combustion area in an engine, and solves the technical problem of low ignition efficiency of the main combustion area of a product in the prior art. The ignition device is suitable for indirect ignition of an aircraft engine combustion chamber, the combustion chamber comprises a casing and a flame tube, the combustion chamber is mounted on the casing and comprises an ignition assembly, and the ignition assembly is used for conveying open fire or flame into the flame tube when the engine is started so as to ignite oil-gas mixture in a main combustion area of the flame tube. The ignition efficiency of the main combustion area is improved.

Description

Igniter

Technical Field

The invention belongs to the technical field of ignition devices in a main combustion area of an engine, and particularly relates to an igniter.

Background

The medium and small-sized aero-engine generally refers to a turbojet engine and a turbofan engine with the thrust below 5000daN, a turboshaft engine and a turboprop engine with the power below 5000kW and the like, and can be used as the power of military and civil helicopters, coaches, light attack planes, military and light transport planes, civil branch airliners, general airplanes, unmanned planes and cruise missiles. The output of the small and medium-sized aero-engines accounts for more than 80% of the world aero-engine market, and is an important component in the field of aero-engines.

The small and medium-sized aeroengines can use the research results and test conditions of large engines, but are not the shrinkage of large indoor engines, so that the small and medium-sized aeroengines have unique design and manufacturing technology, and the design to be considered comprises small size effect, influence of low Reynolds number on a gas compressor, low cost requirement, stability of a high-speed rotor and the like.

The igniter is used for forming an ignition source during starting or after high-altitude flameout. Conventional aircraft engines typically require the igniter to operate under three conditions: when the airplane is started on the ground, is stopped in the air and is in a storm or in maneuvering flight, the combustion chamber is prevented from flameout. Ignition performance directly affects the safety and reliability of the operation of the engine. When the engine is shut down at high altitude, the compressor is in a windmill state, the pressure and the temperature of the inlet of the combustion chamber are low, but the airflow speed is still high. Under such conditions, it is not easy to ensure reliable reignition. The ignition system must therefore have the following advantages: firstly, the ignition system should have sufficient energy and ensure reliable ignition within a specified ignition range; secondly, the igniter has enough pressure resistance, heat resistance and corrosion resistance, and a certain service life is ensured; thirdly, the ignition system should be simple in structure, light in weight, small in size, convenient to use and maintain.

The ignition device of the engine is generally direct ignition, the direct ignition is usually spark ignition, the direct ignition device has the advantages of simple structure, light weight, low cost and convenient replacement, but during ignition, an ignition electric nozzle with higher energy is needed, a fuel nozzle is required to have a very good fuel atomization effect under the condition of lower oil supply pressure and flow, and the requirement on the working range of the fuel nozzle and a main pipe is further severer. Meanwhile, in the ignition stage, the air flow in the combustion chamber is unstable, the oil-gas ratio and the flow field at the ignition electric nozzle are not easy to be accurately controlled, and the ignition reliability is relatively limited.

In view of the above, the present invention is particularly proposed.

Disclosure of Invention

The invention aims to provide an igniter, which solves the technical problem that the ignition efficiency of a main combustion area of a product in the prior art is low. The technical scheme of the scheme has a plurality of technical beneficial effects, which are described as follows:

an igniter is provided, which is suitable for indirect ignition of a combustion chamber of an aircraft engine, wherein the combustion chamber comprises a machine box and a flame tube and comprises an ignition assembly, and the ignition assembly is used for delivering open fire or flame into the flame tube when the engine is started so as to ignite oil-gas mixture in a main combustion area of the flame tube.

Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:

the device of present case forms solitary indirect ignition through setting up the ignition subassembly, and it forms the naked light earlier and then carries the naked light to combustion-supporting district, its advantage:

1) the air flow rate in the single pre-combustion chamber is low, and the flow field is stable;

2) the starting nozzle with the independent oil way can ensure the atomization effect of the ignition nozzle under small fuel flow, can reduce the debugging working pressure point of the fuel main pipe with the nozzle, and has lower manufacturing difficulty and cost;

3) the special air-entraining and oxygen-supplementing channel is provided, and the high-altitude ignition capacity of the combustion chamber is effectively improved.

The indirect igniter has high ignition reliability and wide application range, and the reliability and timeliness of engine ignition are life lines of missiles.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a perspective view of the device of the present invention;

FIG. 2 is a schematic view of the installation position of the present invention;

FIG. 3 is a cross-sectional view of the present invention with baffles;

FIG. 4 is a cross-sectional view of the present invention with an air supplement tube;

wherein, 1, atomizing and spraying; 2. a housing; 3. an ignition electric nozzle; 4. a breather pipe; 5. a communicating pipe; 6. a baffle plate; 8. air hole supplement; 9. a gas supplementing pipe; 10. a casing.

Detailed Description

The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.

It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention, and the drawings only show the components related to the present invention rather than the number, shape and size of the components in practical implementation, and the type, quantity and proportion of the components in practical implementation can be changed freely, and the layout of the components can be more complicated.

In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details. In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

The igniter shown in fig. 1 is suitable for indirect ignition of an aircraft engine combustion chamber, which comprises a casing 10 and a flame tube, and comprises an ignition assembly, wherein the ignition assembly is used for delivering open fire or flame into the flame tube when the engine is started so as to ignite oil-gas mixture in a main combustion area of the flame tube.

The indirect ignition device of the scheme avoids the situation that an igniter in a main combustion area cannot normally ignite due to high atomization concentration in a high-altitude high-pressure environment or during direct ignition, and generally can ignite for multiple times to burn, so that the service performance of an engine is reduced. By forming an independent fire source and delivering it to the combustion zone, the inefficient direct ignition is avoided. The starting nozzle with the independent oil way can ensure the atomization effect of the ignition nozzle under small fuel flow, and can reduce the debugging working pressure point of the fuel main pipe with the nozzle.

It should be pointed out that, at the stage of ignition, the air flow in the combustion chamber is unstable, the oil-gas ratio and the flow field at the ignition electric nozzle 3 are not easy to be accurately controlled, and the reliability of ignition is relatively limited. At present, direct ignition is adopted more, but with the increasing concern of people on pollution, the design of the head of the flame tube is developed towards the lean oil direction; in addition, the use of new alternative fuels reduces the evaporation performance, which deteriorates the high-altitude ignition performance, and the adoption of direct ignition is increasingly difficult. Therefore, one of the approaches to solving the above difficulties is to design the indirect ignition device chamber with compact structure and reliable performance.

This point firearm can provide stable high-energy torch to the flame tube under various operating modes, synthesizes and sees that the device can satisfy small-size aeroengine point firearm ignition wide range, simple structure, reliability height, repeatedly usable's demand. The indirect igniter has the advantages of simple and novel structure, low manufacturing cost and high working reliability, and can meet the requirements of wide ignition range, simple structure, high reliability and repeated use of the small aero-engine igniter.

As a specific implementation manner provided by the scheme, the ignition assembly comprises a shell 2 and a communicating pipe 5 integrally arranged on the shell 2, wherein one end of the communicating pipe 5 is connected into a main combustion area in the flame tube; 2 intervals of casing set up atomizing spraying 1, ignition electric nozzle 3 and are used for combustion-supporting gas to introduce the muffler 9 in the

casing

2, and 9 both sides of muffler set up the muffler, and the air is got into by 2 bottom surfaces of casing, also can set up alone and deposit the oxygen jar, through

muffler

9 and 2 intercommunications of casing, also other modes, wherein:

one end of the atomizing nozzle is connected into the shell 2, and the other end of the atomizing nozzle is connected with the oil supply pipe; ignition electric torch 3 sets up with atomizing nozzle in opposite directions in casing 2, avoids high concentration oil-gas mixture to submerge ignition electric torch 3, wherein:

when the atomizing nozzle atomizes the oil supplied by the oil supply pipe, the air supply pipe 9 supplies combustion-supporting gas into the shell 2, the combustion-supporting gas is ignited by the ignition electric nozzle 3 to generate flame, and the flame is conveyed to a main combustion area in the flame tube through the communicating pipe 5.

Further, as shown in fig. 1 and fig. 2, the communicating tube 5 and the casing 2 are matched in a spherical manner, so that the thermal expansion difference between the outer wall casing 10 and the flame tube during operation can be eliminated. The shell and the casing are also in spherical surface matching connection.

The advantage of burning in casing 2 is that receive the factor of environment less, and casing 2 is installed at the quick-witted casket 10 default position, and the default position is the position that corresponds with the main combustion zone in the flame tube, and its area in the region of casing 2 for the combustion zone is less, does benefit to and forms the naked light.

As a specific implementation mode provided by the present disclosure, the device further includes a baffle 6 disposed in the vertical direction, and the positions of the baffle are as follows: set up baffle 6 in casing 2 and near atomizing nozzle position department for avoid the oil gas mixture after atomizing nozzle atomizing to cover ignition electric nozzle 3, make ignition electric nozzle 3 unable normal work. The fuel oil atomizer can prevent excessive atomized oil and gas mixtures in the shell 2 from causing the ignition electric nozzle 3 not to ignite the mixtures in the shell 2, and simultaneously, the fuel oil atomization performance and the ignition stability are improved.

As a specific embodiment provided by the present disclosure, a plurality of vent pipes 4 are arranged on the casing 2 at intervals in a direction toward the flame tube, and the vent pipes 4 are used for introducing two streams of air between the flame tube and the casing 10 into the casing 2, so as to push the flame to a main combustion area in the flame tube by thrust force formed by pressure difference. The gas conveyed between the flame tube and the casing 10 is effectively utilized to form a pressure difference to push open fire into a combustion-supporting area.

It should be noted that the casing 2 is mounted on the inner surface of the casing 10 or embedded in the casing 10, and there are two air flows between the flame tube and the casing 10.

As a specific embodiment provided in the present application, a communication pipe 5 for conveying flame is rotatably connected to the housing 2 to reduce assembly deviation, and the flame tube expands in a hot state, thereby avoiding the influence of expansion with heat and contraction with cold, and canceling the deformation between the flame tube and the casing 10.

As a specific embodiment provided in the present application, the air supply pipe 9 is disposed at a position between the baffle 6 and the ignition electric nozzle 3, so as to maximize the oxygen combustion supporting effect, and the air supply pipe 9 supplies oxygen and extends the duration of the open fire.

Further, an air supply hole 8 is arranged on the shell and between the baffle plate and the ignition nozzle, and oxygen is supplied.

As a specific embodiment provided by the present disclosure, the top end of the baffle 6 is fixed to the housing 2, and the bottom surface of the baffle has a gap with a predetermined distance from the housing 2, the middle region is provided with a plurality of holes through which oil mist passes, the bottom of the housing 2 forms an oil concentration region, and the rest of the space is air, so as to form an open fire.

During operation, fuel is atomized and sprayed out through the atomizing nozzle, and the fuel is decelerated at the baffle plate to enhance atomization.

Oxygen enters the air supplementing hole 8 and the air supplementing pipe 9, the oil atomized by the atomizing nozzle is ignited through the ignition nozzle 3, open fire is generated in the shell 2, pressure difference is formed by air entering through the vent pipe 4, the open fire is sent into the combustion assisting area through the communicating pipe 5, and in the conveying process, the air continuously enters the air through the air supplementing hole 8 and the air supplementing pipe 9 to maintain the combustion of the open fire.

It should be noted that the vent tube 4 is disposed on the housing and faces the direction of the two remaining air flows, and the air supply hole 8 and the air supply tube 9 are disposed oppositely. The igniter can provide a stable high-energy torch for the flame tube under various working conditions and has reliable ignition performance.

The products provided by the present invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the core concepts of the present invention. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the invention without departing from the inventive concept, and those improvements and modifications also fall within the scope of the claims of the invention.

Claims

1. An igniter suitable for the indirect ignition of a combustion chamber of an aircraft engine, the combustion chamber comprising a casing and a flame tube, characterized in that the igniter is mounted on the casing and comprises an ignition assembly for delivering a generated open flame or flame into the flame tube when the engine is started so as to ignite an oil-gas mixture in a main combustion zone of the flame tube.

2. The igniter of claim 1, wherein the ignition assembly comprises a housing and a communicating tube integrally arranged on the housing, and one end of the communicating tube is connected to a main combustion area in the flame tube;

the casing interval sets up atomizing spraying, ignition electric nozzle and is used for combustion-supporting gas to introduce the air supplement pipe in the casing, wherein:

one end of the atomizing nozzle is connected into the shell, and the other end of the atomizing nozzle is connected with an oil supply pipe; the ignition electric nozzle is arranged in the shell in a way of facing to the atomizing nozzle, wherein:

when the atomizing nozzle atomizes the oil supplied by the oil supply pipe, the gas supply pipe supplies combustion-supporting gas into the shell, the combustion-supporting gas is ignited by the ignition electric nozzle to generate flame, and the flame is conveyed to a main combustion area in the flame tube through the communicating pipe.

3. The igniter of claim 2, wherein said housing is mounted in a predetermined position in said casing, said predetermined position corresponding to a main combustion zone in said flame tube.

4. The igniter of claim 3, further comprising a baffle plate disposed in the housing and adjacent to the atomizing nozzle for preventing the oil-gas mixture atomized by the atomizing nozzle from covering the ignition nozzle, so that the ignition nozzle cannot work normally.

5. The igniter as in claim 4, wherein a plurality of vent pipes are provided on the housing at intervals in a direction toward the flame tube, the vent pipes are used for introducing two streams of air between the flame tube and the casing into the housing, and pushing the flame to the main combustion area in the flame tube by thrust force generated by pressure difference.

6. The igniter of claim 5, wherein the communicating tube for transmitting the flame is rotatably connected to the housing to reduce assembly deviation, and the flame tube expands in a hot state to prevent thermal expansion and contraction and to offset deformation between the flame tube and the casing.

7. The igniter of claim 6, wherein said air supplement tube is disposed at a location between said baffle plate and said ignition tip.

8. The igniter of claim 7, wherein the baffle has a top end fixed to the housing and a bottom surface spaced a predetermined distance from the housing, and a central region having a plurality of oil mist passing holes.