CN108800205A - A kind of eddy flow reinforcing/stamping combustion chamber - Google Patents
A kind of eddy flow reinforcing/stamping combustion chamber Download PDFInfo
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- CN108800205A CN108800205A CN201810371749.5A CN201810371749A CN108800205A CN 108800205 A CN108800205 A CN 108800205A CN 201810371749 A CN201810371749 A CN 201810371749A CN 108800205 A CN108800205 A CN 108800205A
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- duty
- stabilizer
- combustion chamber
- fuel injector
- fuel
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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
Abstract
A kind of eddy flow reinforcing/stamping combustion chamber belongs to new concept aero-engine swirl flow combustion technical field.In the chamber structure, flow slowing down is pressurized by diffuser；Diffuser pipe incoming is divided into primary air and cooling by-pass air duct air-flow by heat screen, and several cooling holes are provided on heat screen；Flameholder transmits and stablizes flame；Swirl vane is placed in flameholder and with primary air in setting angle, and downstream airflow is made to generate rotation；Oil supply system is divided into grade fuel feeding, radial stabilizer outer shroud fuel feeding and main combustion stage fuel feeding on duty, using the fuel system of direct-injection type atomizer and fuel ring pipe, main oil pipe point radial oil pipe.Compared to conventional burners, as a result of swirl flow combustion mode, flame propagation velocity is not by pressure influence, in addition subregion fuel system, oil gas are more fully mixed, more efficient stabilization of burning pollutes also smaller.Further, since reducing flameholder passes flame device, chamber structure is simplified, length shortens, weight saving.
Description
Technical field
The present invention relates to a kind of eddy flow reinforcing/stamping combustion chamber, the after-burner mainly as aero-engine or punching
Hydraulic motor combustion chamber belongs to new concept aero-engine swirl flow combustion technical field.
Background technology
After-burner plays a very important role always in military aircraft field, it can be such that fanjet improves
60%~70% lift makes turbojet engine improve 40%~50% lift.Currently, after-burner air-fuel mixture burns
Mode is divided into two kinds substantially：" 1. first mixing after-combustion ", 2. " burning in mixing ".
Flameholder is located at diffuser exit, and under normal circumstances, in flameholder upstream fuel injection, stabilizer downstream is returned
Stream district's groups knit burning.Air-flow slows down rapidly after entering diffuser, then forms recirculating zone in stabilizer tail portion, stabilizer setting exists
At diffuser exit, by control flameholder in be provided with mode adapt to chamber performance requirement.Due to needing to use
Radial and axial flameholder realizes that flame stabilization and propagation, flame stabilizer can create a stable region
Flame is maintained, then flame travels to unburned gas mixture by turbulent flow vortex, and general flame is in unburned gas mixture
In angle of flare be 3~4 °, therefore combustion chamber need a certain number of flameholders and need consider flame propagation length, because
The size of this traditional after-burner is generally all bigger.
Certainly, flameholder is more, and the pitot loss of after-burner is bigger, for balance combustion efficiency and total crushing
It loses, flameholder quantity should take a reasonable value with length.But such flame stabilization and transmission structure have certain lack
Point：1. the installation difficulty of flame stabilization structure requires height, and is easy failure；2. in an environment of high temperature, the cooling structure is difficult
Degree is very big；3. efficiency of combustion and pitot loss are easily influenced by flameholder quantity, need considering higher efficiency of combustion
Under the conditions of keep lower pitot loss；4. efficiency of combustion depends on inflow Mach number.
Invention content
In view of the above existing problems in the prior art, the present invention provides a kind of eddy flow reinforcing/stamping combustion chambers, use
Swirl vane generates Swirling Flow, and in equal length, flame propagation velocity and air-fuel mixture degree can be improved, and improves burning effect
Rate and stability, and stabilizer can be simplified, keep structure compacter, mitigates weight.
The technical scheme is that：
A kind of eddy flow reinforcing/stamping combustion chamber is loopful shape structure, including：Diffuser, heat screen, outer casing, flame are steady
Determine device, oil supply system, swirl vane and high-energy spark plug；
Incoming gas is entered by the diffuser in the eddy flow reinforcing/stamping combustion chamber；
The heat screen is arranged in the outer casing, and the Incoming gas is divided into primary air and by-pass air duct air-flow；
The flameholder is arranged in the diffuser air flow outlet；
The flameholder includes：Stabilizer and v-stabilizer on duty, the v-stabilizer are located at described on duty steady
Determine in device；
The oil supply system is arranged in the stabilizer on duty；
The swirl vane, the swirl vane and the master are set between the stabilizer on duty and the v-stabilizer
Air-flow makes downstream airflow generate rotation in setting angle.
Further, the swirl vane and the primary air set angle as 30 °~80 °.
Further, the flameholder further includes：Radial stabilizer and biography flame slot, the radial direction stabilizer are placed in institute
State stabilizer outer shroud on duty；The biography flame slot is placed in the stabilizer inner ring on duty, and the v-stabilizer is placed in the biography flame slot
Inside.
Further, the radial stabilizer sweepback setting and angle of sweep are not more than 35 °, the biographys flame slot sweepback be arranged and
Angle of sweep is not more than 30 °.
Further, the oil supply system is mainly made of grade fueller on duty and mainstream fueller, described on duty
Grade fueller is located at mainstream fueller upstream, and the swirl vane is located at mainstream fueller downstream.
Further, described value class fueller includes：It is grade outer shroud fuel feeding manifold on duty, overhanging Fuel Injector Bar one, on duty
Grade fuel nozzle and evaporator tank Fuel Injector Bar, described value class outer shroud fuel feeding manifold and the evaporator tank Fuel Injector Bar are loop configuration
And it is respectively positioned in the stabilizer on duty；
The radial setting of the overhanging Fuel Injector Bar one drawn from described value class outer shroud fuel feeding manifold, is distributed several institutes thereon
State grade fuel nozzle on duty；
The evaporator tank Fuel Injector Bar is uniformly distributed circumferentially several evaporator tank Fuel Injector Bar outlets；
The mainstream fueller is placed in the v-stabilizer upstream, mainly by mainstream fuel manifold, overhanging Fuel Injector Bar
Two, interior to stretch Fuel Injector Bar and direct-injection type atomizer composition, it is responsible for combustion chamber main flow area fuel feeding, wherein the mainstream fuel manifold is
Annular, the overhanging Fuel Injector Bar two and the interior Fuel Injector Bar of stretching radially are arranged, and are arranged on the overhanging Fuel Injector Bar two several described
Direct-injection type atomizer.
Further, the heat screen, which is arranged, several carries out heat screen wall surface cooling cooling hole.
The present invention has the advantages that：
1, quickly, about 3~4 times of turbulent-flame, under certain condition, flame propagation velocity is or not swirl flame spread speed
With pressure change；The centrifugal force that strong eddy flow generates makes the high-temperature gas of burning float inwards, and unburned cryogenic gas is made to sink,
Be conducive to improve chamber performance, increase flame propagation velocity, improve mixing capacity, improves efficiency of combustion；
2, flame device is passed due to reducing flameholder, chamber structure is simplified, length shortens, weight saving；
3, experiments have shown that the flame that the lower high-temperature gas of Swirling Flow (centripetal acceleration is 2000~4000g) control floats passes
Broadcasting speed makes 5 times of common turbulent flame spread speed, and when inflow Mach number increases, flame propagation velocity also will increase, also
It is to say, inflow Mach number does not influence efficiency of combustion substantially；
4, pitot loss is small, and swirler blades angle can carry out Rational choice by calculating between 30 ° to 80 °, can make to add
Power combustion chamber energy loss reduces；
5, because swirl flow combustion is more more stable than traditional combustion system, thus it is less to discharge fume, noise smaller；Experiment proves, arranges
Nitrogen oxide NOx reduces by 30 one 50% in gas；
6, the cold air that centrifugal action keeps density big forms stable cooling layer, and the shortening of chamber length makes cooling air demand
Amount is further reduced, thus annular firing chamber outer wall cooling effect is more preferable.
Description of the drawings：
Fig. 1 is eddy flow reinforcing/stamping combustion chamber structural schematic diagram of the present invention；
Fig. 2 is that the flameholder of eddy flow reinforcing/stamping combustion chamber of the present invention and swirl vane structural schematic diagram (contain office
Portion's cutaway view Amplified image)；
Fig. 3 is the grade fueller structural schematic diagram on duty of eddy flow reinforcing/stamping combustion chamber of the present invention；
Fig. 4 is the mainstream fueller structural schematic diagram of eddy flow reinforcing/stamping combustion chamber of the present invention；
Fig. 5 is the operation principle schematic diagram of grade fueller on duty shown in Fig. 3；
Fig. 6 is eddy flow reinforcing/stamping combustion chamber eddy flow schematic cross-section of the present invention；
Fig. 7 is the stabilizer on duty circulation interface combustion process schematic diagram of eddy flow reinforcing/stamping combustion chamber of the present invention；
Fig. 8 is the mainstream circulation interface combustion zone schematic diagram of eddy flow reinforcing/stamping combustion chamber of the present invention；
It is identified in figure：1- eddy flows reinforcing/stamping combustion chamber, 2- diffusers, 3- heat screens, the outer casings of 4-, 5- grades on duty supply
Oily device, 6- mainstream fuellers, 7- stabilizers on duty, 8- swirl vanes, 9- biography flame slots, 10-V type stabilizers, 11- are radially steady
Determine device, 12- high-energy spark plugs, 13- cooling holes, the 14- overhanging Fuel Injector Bars one of grade outer shroud fuel feeding manifold, 151- on duty, the overhanging sprays of 152-
Beam hanger two, 16- grade fuel nozzles on duty, 17- evaporator tank Fuel Injector Bars, the outlet of 18- evaporator tank Fuel Injector Bars, 19- mainstream fuel manifolds,
Stretch Fuel Injector Bar in 20-, 21- direct-injection type atomizers, 22- interlayer rings, 23- is into compression ring, the outer stabilizers of 24-, 25- inner balancers, 26-
Mixed zone, the areas Shuan Wo on duty 27-, the primary zones 28- (stabilizer section), 29- flame fronts, 30- eddy flows.
Specific implementation mode：
Technical scheme of the present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in Figure 1, eddy flow reinforcing/stamping combustion chamber 1 of the present invention is loopful shape combustion chamber,
It is mainly by diffuser 2, heat screen 3, outer casing 4, grade fueller 5 on duty, mainstream fueller 6, on duty steady
Determine device 7, swirl vane 8, pass flame slot 9, v-stabilizer 10, radial stabilizer 11 and the composition of high-energy spark plug 12.Air-flow is through diffuser
Enter combustion chamber after 2 deceleration superchargings, in favor of the tissue of burning.Heat screen 3 is arranged in outer casing 4, is flowed out from diffuser 2
Air-flow divides through heat screen 3 for primary air and for cooling by-pass air duct air-flow, heat screen 3 arrange it is several to 3 wall surface of heat screen into
The cooling cooling hole 13 of row.
As shown in Figure 1, Figure 2 and shown in Fig. 5, the setting of stabilizer 7 on duty is in the outlet of diffuser 2, heat screen 3, mainly by interlayer
Ring 22 is formed into compression ring 23, outer stabilizer 24 and inner balancer 25.Radial stabilizer 11 is placed in 7 outer shroud of stabilizer on duty, sweepback
It is arranged and angle of sweep is not more than 35 °；Biography flame slot 9 is placed in 7 inner ring of stabilizer, sweepback setting and angle of sweep on duty and is not more than 30 °, V
Type stabilizer 10, which is placed in, passes 9 inside of flame slot.
As shown in figures 1 and 3, grade fueller 5 on duty by grade outer shroud fuel manifold 14 on duty, overhanging Fuel Injector Bar 1,
Grade fuel nozzle 16 and evaporator tank Fuel Injector Bar 17 on duty are constituted, and provide fuel for the areas Shuan Wo 27 on duty, wherein grade outer shroud on duty supplies
Oily manifold 14 and evaporator tank Fuel Injector Bar 17 are loop configuration and are placed in 7 device of stabilizer on duty, evaporator tank Fuel Injector Bar 17
It is uniformly distributed circumferentially several evaporator tank Fuel Injector Bar outlets 18, the radial setting of overhanging Fuel Injector Bar 1, overhanging Fuel Injector Bar 1
Upper several grade fuel nozzles 16 on duty of setting；
As shown in Fig. 1, Fig. 5, Fig. 7 and Fig. 8, air is split into 7 outer sidewind of stabilizer on duty when passing through stabilizer 7 on duty
And interior air-flow；Outside air is flowed through from 24 outside wall surface of outer stabilizer, enters primary zone with flame slot 9 is passed by radial stabilizer 11
28；Interior air-flow is flowed into from into compression ring 23 between outer stabilizer 24 and inner balancer 25, interior air-flow by evaporator tank Fuel Injector Bar 17 with
Fuel oil mixes, and enters the areas Shuan Wo 27 on duty along 25 wall surface of inner balancer.
As Figure 1 and Figure 4, mainstream fueller 6 is placed in 10 upstream of v-stabilizer, mainly by mainstream fuel manifold 19,
Overhanging Fuel Injector Bar 2 152, interior Fuel Injector Bar 20 and the direct-injection type atomizer 21 stretched form, and are responsible for combustion chamber main flow area fuel feeding.Wherein, main
It is annular to flow fuel manifold 19, and overhanging Fuel Injector Bar 2 152 and interior 20 radial direction of Fuel Injector Bar of stretching are arranged, are set on overhanging Fuel Injector Bar 2 152
Set several direct-injection type atomizers 21.
Referring to Fig.1, Fig. 2, swirl vane 8 are placed between stabilizer 7 and v-stabilizer 10 on duty, under mainstream fueller 6
Trip, and angle is formed with primary air, so that downstream airflow is generated rotation.
High-energy spark plug 12 is arranged in stabilizer 7 on duty.
The operation principle of the present invention is：
Referring to Fig.1 and combine Fig. 7, Fig. 8, eddy flow reinforcing/stamping combustion chamber 1 during the work time, using subregion fuel feeding side
Formula, partial air and fuel enter stabilizer 7 on duty, control 27 equivalent proportion of the areas Shuan Wo on duty 1.0 or so, fuel is on duty double
Stability and high efficiency burning, the grade on duty as entire combustion chamber are carried out in whirlpool area 27.Radial stabilizer outer shroud fuel oil is outside grade on duty
The grade fuel nozzle 16 on duty of ring fuel feeding manifold 14 sprays, and form is sprayed in direction perpendicular to incoming, using bilateral, and fuel oil is mixed with incoming
It burns into mixed zone 26 after mixed；Mainstream fuel oil is sprayed from the direct-injection type atomizer 21 of mainstream fueller 6, and direction is vertical
In incoming, form is sprayed using bilateral, fuel oil burns with after mainstream interaction blending into primary zone 28.
As shown in fig. 6, in mainstream flow area, air-flow forms eddy flow 30 by swirl vane 8.Eddy flow 30 be it is a kind of simultaneously
With axial, radially and tangentially speed spiral fluid, eddy flow 30 helps to being sufficiently mixed for mainstream and fuel oil, spiral shell
The fluid form that rotation is advanced increases fuel oil in the residence time in primary zone 28, and the presence of tangential velocity and radial velocity adds
Strong substance between mainstream and primary zone 28, energy exchange, are conducive to flame transmission.
As shown in fig. 7,7 mainstream section of stabilizer on duty, 7 downstream of stabilizer on duty forms 27 structure of double whirlpool recirculating zones, diameter
Mixing recirculating zone 26 is formed to 11 downstream of stabilizer, the unburned gas mixture in mixed zone 26 is ignited by double whirlpool recirculating zones 27.
Flame is lighted in double whirlpool recirculating zones 27, is propagated to annular V type groove downstream to V-shaped groove by 2 circumferentially distributed root diameters, is lighted whole
A combustion chamber, flame propagation process refer to flame front 29；Mainstream fuel oil equivalent proportion controls between 0.4~0.9.
With reference to Fig. 5, Fig. 7 and Fig. 8, the igniting of eddy flow reinforcing/stamping combustion chamber of the present invention and flame stabilization：In stabilization on duty
The interlayer ring 22 of device 7, into compression ring 23, outer stabilizer 24 and 25 Sizes of inner balancer it is matched in the case of, stabilizer 7 on duty
Downstream forms double whirlpool recirculating zones 27.Fuel oil is sprayed from evaporator tank Fuel Injector Bar outlet 18, and Incoming gas is outer steady from entering into compression ring 23
Determine the channel between device 24 and inner balancer 25, fully to blend with air-flow while fuel oil evaporates in evaporator tank, be formed flammable
Mixed gas；At a certain characteristic moment, ignition system connects the high-temperature plasma area to form a similar diffusion flame shape, lights height
Flammable mixed gas near energy sparking plug 12, forms the core fire group with sufficient size and temperature.Core fire group is passing around
It while broadcasting flame, is moved with air-flow, under this double effect, flame circumferentially travels to entire 7 downstream of stabilizer on duty
Double whirlpool recirculating zones 27 in, formed stable point burning things which may cause a fire disaster；After incoming mixture enters evaporator tank, under the action of the stable point burning things which may cause a fire disaster
It is heated and is ignited；The circumferential of flame is propagated, and will be lighted entire annular stabilizer 7 on duty, is thus indicated an igneous
Work(.Section where passing flame slot in radial V-arrangement, air-flow pass flame slot under the driving of differential pressure action by passing flame slot 9 in radial V-arrangement
Downstream forms mixed zone 26, and flame propagates to v-stabilizer 10 by mixed on low speed area 26 and ignites under the correspondence of v-stabilizer 10
Low regime is swum, primary zone 28 is formed, final entire combustion chamber is ignited and stablizes burning.
With reference to Fig. 2 and Fig. 6, the cyclonic effect of eddy flow reinforcing/stamping combustion chamber of the present invention：Swirl vane shown in Fig. 2
In the case of rational deployment and size design, mainstream fuel oil is sprayed from overhanging Fuel Injector Bar 15 and interior Fuel Injector Bar 20 of stretching perpendicular to incoming
Go out, air-flow generates radially and tangentially component velocity by swirl vane, and flow spiral, which advances, enhances the exchange of quality and momentum, makes
Air-fuel mixture is more uniform, and increase fuel oil in the stroke of main flow area, increase fuel oil residence time indirectly, improve combustion
Burn efficiency；Eddy flow as shown in Figure 6 flows to schematic diagram, and rotating fluid generates centrifugal effect, due to the presence of the cold and hot temperature difference, burning production
Object generates convection current because of density difference, and then, the displacement of cold and hot product just produces buoyancy, for the buoyancy effect of some strength
Be conducive to improve flame propagation velocity, entire combustion chambers burn is more abundant.
3 wall surface of heat screen is cooled down using effusion wall mode in eddy flow reinforcing/stamping combustion chamber 1 of the present invention, can also be made
With other types of cooling, meet different requirements, such as impinging cooling, impact air film etc..
In addition, swirler blades are also designed to angle adjustable structure, such pitot loss becomes adjustable, can be with
Adjusting swirler blades makes efficiency of combustion stablize 100%, and when not opening reinforcing, pitot loss is very low, adds
Power combustion chamber energy loss is small.Specifically, in the state of not opening reinforcing, swirl vane is opened completely, caused by the acylic motion of downstream
Pitot loss；If applied in existing efficient after-burner, under cruising condition, pitot loss can reduce by 1~2%.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, several improvement can also be made without departing from the principle of the present invention, these improvement also should be regarded as the present invention's
Protection domain.
Claims (7)
1. a kind of eddy flow reinforcing/stamping combustion chamber is loopful shape structure, including：Diffuser (2), heat screen (3), outer casing
(4), flameholder, oil supply system and high-energy spark plug (12), Incoming gas enter eddy flow reinforcing/punching press by diffuser (2)
In combustion chamber (1), the heat screen (3) that the Incoming gas is divided into primary air and by-pass air duct air-flow is arranged in outer casing (4),
The flameholder is arranged in diffuser (2) exit, which is characterized in that
The flameholder includes：Stabilizer (7) on duty and v-stabilizer (10), v-stabilizer (10) are located at stabilization on duty
In device (7)；
The oil supply system is arranged in stabilizer on duty (7)；
Swirl vane (8) is set between stabilizer (7) on duty and v-stabilizer (10), and swirl vane (8) is in the primary air
Angle is set, downstream airflow is made to generate rotation.
2. a kind of eddy flow reinforcing/stamping combustion chamber according to claim 1, which is characterized in that swirl vane (8) with it is described
Primary air sets angle as 30 °~80 °.
3. a kind of eddy flow reinforcing/stamping combustion chamber according to claim 1, which is characterized in that the flameholder is also
Including：Radial stabilizer (11) and biography flame slot (9), radial stabilizer (11) are placed in stabilizer on duty (7) outer shroud, pass flame slot (9)
It is placed in stabilizer on duty (7) inner ring, v-stabilizer (10), which is placed in, to be passed on the inside of flame slot (9).
4. a kind of eddy flow reinforcing/stamping combustion chamber according to claim 3, which is characterized in that after radial stabilizer (11)
It plunders setting and angle of sweep is not more than 35 °, pass flame slot (9) sweepback setting and angle of sweep is not more than 30 °.
5. a kind of eddy flow reinforcing/stamping combustion chamber according to claim 1 or 2, which is characterized in that the oil supply system master
It to be made of grade fueller (5) on duty and mainstream fueller (6), grade fueller (5) on duty is located at mainstream fueller
(6) upstream, swirl vane (8) are located at mainstream fueller (6) downstream.
6. a kind of eddy flow reinforcing/stamping combustion chamber according to claim 5, which is characterized in that
Grade fueller (5) on duty includes：Grade outer shroud fuel feeding manifold (14) on duty, overhanging Fuel Injector Bar one (151), grade fuel feeding on duty
Nozzle (16) and evaporator tank Fuel Injector Bar (17), wherein grade outer shroud fuel feeding manifold (14) on duty and evaporator tank Fuel Injector Bar (17) are
It loop configuration and is respectively positioned in stabilizer on duty (7)；
The overhanging Fuel Injector Bar one (151) drawn from grade outer shroud fuel feeding manifold (14) on duty is radially arranged, and is distributed thereon several on duty
Grade fuel nozzle (16)；
Evaporator tank Fuel Injector Bar (17) is uniformly distributed circumferentially several evaporator tank Fuel Injector Bar outlets (18)；
Mainstream fueller (6) is placed in v-stabilizer (10) upstream, mainly by mainstream fuel manifold (19), overhanging Fuel Injector Bar two
(152), interior to stretch Fuel Injector Bar (20) and direct-injection type atomizer (21) composition, mainstream fuel manifold (19) is annular；Overhanging Fuel Injector Bar
Two (152) and interior Fuel Injector Bar (20) of stretching radially are arranged, and several direct-injection type atomizers (21) are arranged on overhanging Fuel Injector Bar two (152).
7. a kind of eddy flow reinforcing/stamping combustion chamber according to claim 1, which is characterized in that heat screen (3) arrangement is several
Cooling cooling hole (13) is carried out to heat screen (3) wall surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810371749.5A CN108800205B (en) | 2018-04-24 | 2018-04-24 | Swirl afterburning/stamping combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810371749.5A CN108800205B (en) | 2018-04-24 | 2018-04-24 | Swirl afterburning/stamping combustion chamber |
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| CN108800205B CN108800205B (en) | 2020-04-24 |
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| CN114046535A (en) * | 2021-11-09 | 2022-02-15 | 南京航空航天大学 | Adjustable blowing attached diffuser |
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| CN115653759A (en) * | 2022-10-13 | 2023-01-31 | 中国航发四川燃气涡轮研究院 | Afterburner oil supply system based on flow distribution and control flow design method |
| CN114645799B (en) * | 2022-02-24 | 2024-04-26 | 哈尔滨工业大学 | Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2674845A (en) * | 1951-05-02 | 1954-04-13 | Walter D Pouchot | Diffuser apparatus with boundary layer control |
| US4428191A (en) * | 1964-10-01 | 1984-01-31 | Rolls Royce Limited | Fuel combustion in ducted flow |
| CN1080044A (en) * | 1992-03-16 | 1993-12-29 | 通用电气公司 | The eddy current flameholder of isolating velocity field under the non-basic running operating mode |
| EP1391657A2 (en) * | 2002-08-22 | 2004-02-25 | Hitachi, Ltd. | Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor |
| CN1858498A (en) * | 2006-05-16 | 2006-11-08 | 北京航空航天大学 | Tangential standing vortex burning chamber |
| CN1875223A (en) * | 2003-09-05 | 2006-12-06 | 德拉文公司 | Pilot combustor for stabilizing combustion in gas turbine engines |
| CN103277814A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Low-emission trapped-vortex combustor with rich-burn/quick-quench/lean-burn combined with lean pre-mix pre-vaporization |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN105953265A (en) * | 2016-05-27 | 2016-09-21 | 南京航空航天大学 | Combination combustion chamber |
-
2018
- 2018-04-24 CN CN201810371749.5A patent/CN108800205B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2674845A (en) * | 1951-05-02 | 1954-04-13 | Walter D Pouchot | Diffuser apparatus with boundary layer control |
| US4428191A (en) * | 1964-10-01 | 1984-01-31 | Rolls Royce Limited | Fuel combustion in ducted flow |
| CN1080044A (en) * | 1992-03-16 | 1993-12-29 | 通用电气公司 | The eddy current flameholder of isolating velocity field under the non-basic running operating mode |
| EP1391657A2 (en) * | 2002-08-22 | 2004-02-25 | Hitachi, Ltd. | Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor |
| CN1875223A (en) * | 2003-09-05 | 2006-12-06 | 德拉文公司 | Pilot combustor for stabilizing combustion in gas turbine engines |
| CN1858498A (en) * | 2006-05-16 | 2006-11-08 | 北京航空航天大学 | Tangential standing vortex burning chamber |
| CN103277814A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Low-emission trapped-vortex combustor with rich-burn/quick-quench/lean-burn combined with lean pre-mix pre-vaporization |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN105953265A (en) * | 2016-05-27 | 2016-09-21 | 南京航空航天大学 | Combination combustion chamber |
Non-Patent Citations (2)
| Title |
|---|
| 朱志新等: "基于蒸发式值班稳焰的涡轮基组合燃烧室燃烧性能研究", 《推进技术》 * |
| 朱志新等: "涡轮基组合循环发动机超级燃烧室燃烧性能试验", 《航空动力学报》 * |
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