CN108954387A - A kind of micro gas turbine engine and its chamber assembly that burns - Google Patents
A kind of micro gas turbine engine and its chamber assembly that burns Download PDFInfo
- Publication number
- CN108954387A CN108954387A CN201810895086.7A CN201810895086A CN108954387A CN 108954387 A CN108954387 A CN 108954387A CN 201810895086 A CN201810895086 A CN 201810895086A CN 108954387 A CN108954387 A CN 108954387A
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- China
- Prior art keywords
- casing
- combustion chamber
- inner liner
- wall
- burner inner
- Prior art date
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Classifications
-
- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
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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
- F23R3/58—Cyclone or vortex type combustion chambers
Abstract
The present invention relates to a kind of burning chamber assemblies of micro gas turbine engine, including burner inner liner and casing, with the combustion chamber of circular ring shape in the burner inner liner, multiple combustion chamber oil supplying holes that fuel oil is sprayed into the combustion chamber are offered on the burner inner liner, the combustion chamber oil supplying hole is along the circumferentially distributed of the combustion chamber, and the one-to-one evaporation tube of combustion chamber oil supplying hole is additionally provided in the combustion chamber, the first end of any one evaporation tube is each attached on the burner inner liner and is connected to the corresponding combustion chamber oil supplying hole, the same side of the equal direction of second end via hole radial line corresponding with itself, which tilts, to be extended, and each described evaporation tube and the angle α of the via hole radial line corresponding to itself are all larger than 0 °.Combustion stability and efficiency of combustion in burner inner liner can be improved in the burning chamber assembly.The invention also discloses a kind of micro gas turbine engines using above-mentioned burning chamber assembly.
Description
Technical field
The present invention relates to micro gas turbine engine Combustion chamber design fields, more particularly to one kind to be suitable for miniature gas
The toroidal combustion chamber of the evaporation tubular type of turbogenerator.
Background technique
Micro gas turbine engine (Micro-turbine-engine, MTE), with light-weight, power is big, thrust ratio
The advantages that high.Compared with conventional engine, since minute vehicle has, size is small, revolving speed is high, number of components is few, the working time
It is long, thrust is easily adjusted, infra-red radiation is low, the advantages that capable of reusing.In unmanned battle aircraft, antiaircraft weapon target, essence
It is really widely applied on the equipments such as strike ammunition, test vehicle, either in military field still in civil field, it has ten
Divide tempting application prospect.
Currently, each state is all stepping up design and research to micro gas turbine engine.And as one of key technology
Combustion chamber, due to the micromation (grade to Centimeter Level) of size, so that its area-capacity is than big, heat transfer loss is increased
Add.The case where it is short that this will lead to combustion residence time, fuel burn incompletely.Therefore, improve its adequacy of burning, improve it
There are also very big rooms for promotion for efficiency of combustion etc..
Summary of the invention
An object of the present invention is to provide a kind of burning chamber assembly of micro gas turbine engine, so as to improve
The burning adequacy of micro gas turbine engine combustion chamber, improves the efficiency of combustion of fuel.
Another object of the present invention, which also resides in, provides a kind of gas-turbine unit using above-mentioned burning chamber assembly.
In order to achieve the above objectives, the burning chamber assembly of micro gas turbine engine provided by the invention, including burner inner liner
And casing is offered on the burner inner liner and multiple is sprayed into the combustion chamber with the combustion chamber of circular ring shape in the burner inner liner
The combustion chamber oil supplying hole of fuel oil is penetrated, the combustion chamber oil supplying hole is along the circumferentially distributed of the combustion chamber, and in the combustion chamber
It is additionally provided with the one-to-one evaporation tube of combustion chamber oil supplying hole, the first end of any one evaporation tube is each attached to described
Be connected on burner inner liner and with the corresponding combustion chamber oil supplying hole, the equal direction of second end via hole radial line corresponding with itself it is same
It rolls and tiltedly extends, and each described evaporation tube and the angle α of the via hole radial line corresponding to itself are all larger than 0 °, wherein institute
Via hole radial line is stated to be originated by the center of circle of the combustion chamber, and the straight line of the excessively described combustion chamber oil supplying hole.
Preferably, the casing has a circular casing interlayer, the casing interlayer by casing antetheca, casing rear wall,
Casing outer wall and casing inner wall are enclosed；
The burner inner liner is embedded in the casing interlayer by the casing antetheca, and the combustion chamber of the circular ring type is integrally embedding
In the casing interlayer, the combustion chamber is enclosed by burner inner liner antetheca, burner inner liner rear wall, flame drum outer wall and burner inner liner inner wall
It closes and is formed；
The burner inner liner and casing antetheca sealing cooperate, and are reserved between the burner inner liner and the casing interlayer
Airstream compartment, offers the inlet channel communicated with the airstream compartment on the casing outer wall, the flame drum outer wall and/or
The air inlet communicated with the airstream compartment is offered on the burner inner liner inner wall；
The fire hole for installing igniter, the combustion chamber are offered on the casing outer wall and the flame drum outer wall
Oil supplying hole is provided on the flame drum outer wall, and casing corresponding with the combustion chamber oil supplying hole is offered on the casing outer wall
Oil supplying hole.
Preferably, each described evaporation tube with itself corresponding to the angle α of via hole radial line be equal.
Preferably, any one evaporation tube and the angle α of the via hole radial line corresponding to itself meet: 30 ° < α < 60 °.
Preferably, the combustion chamber oil supplying hole is uniformly distributed in the circumferential direction of the combustion chamber.
Preferably, the flame drum outer wall and casing antetheca sealing cooperate, and the burner inner liner inner wall is connected by casing
It connects arm and casing interlayer sealing cooperates, the casing linking arm and the burner inner liner antetheca form gas outlet channel, institute
Combustion chamber oil supplying hole is stated to be located at close to one end of the burner inner liner rear wall.
Preferably, the center line of the casing oil supplying hole with and the angle of its corresponding via hole radial line be β, and
β is unequal with α.
Preferably, the center line of the casing oil supplying hole with and its corresponding via hole radial line angle β meet:
15°<β<45°。
Preferably, its axis is parallel to horizontal plane when the burning chamber assembly is installed, and in installation condition, the igniting
The angle of hole and vertical plane is γ, wherein 15 ° < γ < 45 °.
Preferably, the burner inner liner rear wall and the casing rear wall are arc-shaped bending, so that the airstream compartment
Rear end formed arc baffling end.
Preferably, the combustion chamber oil supplying hole includes six.
It preferably, further include the gear flame structure being arranged on the burner inner liner inner wall, in cutting for the burner inner liner axis excessively
On face, the gear flame structure is wedge shaped, wherein the gear flame structure is the wedge shape close to one end of the burner inner liner rear wall
Closed angle end.
Disclosed in this invention micro gas turbine engine, including burning chamber assembly, the burning chamber assembly be it is upper
State the burning chamber assembly disclosed in any one.
As can be seen from the above technical solutions, the burning chamber assembly of micro gas turbine engine disclosed in this invention
In, multiple combustion chamber oil supplying holes are distributed in the combustion chamber of circular ring shape in the circumferential, and each combustion chamber oil supplying hole correspondence is set
It is equipped with an evaporation tube, the first end of multiple evaporation tubes is connected with burner inner liner, the equal direction of second end and the mistake corresponding to itself
The same side of hole radial line, which tilts, to be extended, each described evaporation tube with itself corresponding to via hole radial line angle α it is big
In 0 °, the evaporation of evaporation tube being provided with conducive to fuel oil improves atomizing effect when fuel oil enters combustion chamber, this can be effective
Fuel oil is improved to evaporate simultaneously in the residence time of flame tube head to improve blending and the burning time of fuel oil and air
The arrangement form of pipe makes the fuel oil in burner inner liner form eddy flow, and combustion stability and burning effect in burner inner liner can be improved in this
Rate.
Micro gas turbine engine disclosed in this invention is due to using above-mentioned burning chamber assembly, the miniature whirlpool
Turbine has both the above-mentioned corresponding technological merit of burning chamber assembly, is no longer repeated this herein.
Detailed description of the invention
Fig. 1 is the section view signal of the burning chamber assembly of the micro gas turbine engine disclosed in the embodiment of the present invention
Figure；
Fig. 2 is the left side schematic cross-sectional view of Fig. 1；
Wherein, 1 be casing antetheca, 2 be casing rear wall, 3 be casing outer wall, 4 be casing inner wall, 5 be burner inner liner antetheca, 6
It is flame drum outer wall for burner inner liner rear wall, 7,8 be burner inner liner inner wall, and 9 be casing linking arm, and 10 be gear flame structure, and 11 be evaporation
Pipe, 12 be fire hole, and 13 be casing oil supplying hole, and 14 be combustion chamber oil supplying hole.
Specific embodiment
Core of the invention first is that a kind of burning chamber assembly for micro gas turbine engine, so as to improve micro-
The burning adequacy of type gas turbine combustors, improves the efficiency of combustion of fuel.
Another core of the invention, which also resides in, provides a kind of gas-turbine unit using above-mentioned burning chamber assembly.
In order to enable those skilled in the art to better understand the solution of the present invention, with reference to the accompanying drawings and detailed description
The present invention is described in further detail.
Please also refer to Fig. 1 and Fig. 2, disclosed in this invention micro gas turbine engine burning chamber assembly, packet
Include burner inner liner and casing, wherein burner inner liner has the combustion chamber that circular ring shape is surrounded around central point, and offers on burner inner liner more
A combustion chamber oil supplying hole 14 that fuel oil is sprayed into combustion chamber, circumferencial direction of the combustion chamber oil supplying hole 14 along combustion chamber are distributed, and
And be additionally provided in combustion chamber with the one-to-one evaporation tube 11 of combustion chamber oil supplying hole 14, the first end of each evaporation tube 11 is equal
It is fixed on burner inner liner, and is connected to corresponding combustion chamber oil supplying hole 14, to guarantee through combustion chamber oil supplying hole 14
Fuel oil is smoothly injected on the inner wall of evaporation tube 11, the second end of each evaporation tube 11 both with respect to itself corresponding to mistake
The inclination of hole radial line, and the same inclination of the equal direction of second end of all evapn pipe 11 and the via hole radial line corresponding to itself
Tiltedly, each evaporation tube 11 with and the angle α of the via hole radial line corresponding to itself be all larger than 0 °.
It needs to explain, so-called via hole radial line was exactly combustion chamber oil supplying hole 14, and extending direction is circle
The straight line of toroidal combustion chamber radial direction, more specifically, via hole radial line crosses the center of circle of annular-shaped combustor simultaneously and combustion chamber supplies
The center of circle of oilhole 14, in fact, offering how many a combustion chamber oil supplying holes 14 in the circumferential direction of combustion chamber, so that it may make how many
Via hole radial line actually shows four via hole radial line in Fig. 2, and the length of evaporation tube 11 can be according to the practical function of engine
Rate size and combustion chamber size are adjusted.
The same side of so-called via hole radial line just refer to the second end of evaporation tube 11 towards the left side of via hole radial line or
Right side offset, so as to form eddy flow by the fuel oil that evaporation tube 11 sprays.
In the burning chamber assembly of micro gas turbine engine disclosed in above-described embodiment, in the combustion chamber of circular ring shape
Multiple combustion chamber oil supplying holes 14 are distributed in the circumferential, and each combustion chamber oil supplying hole 14 is correspondingly arranged on an evaporation tube
11, the first end of multiple evaporation tubes 11 is connected with burner inner liner, the equal direction of second end and the via hole radial line corresponding to itself
The same side inclination extends, and the angle α of each described evaporation tube 11 and the via hole radial line corresponding to itself is all larger than 0 °, evaporation
The evaporation of pipe 11 being provided with conducive to fuel oil, improves atomizing effect when fuel oil enters combustion chamber, this can effectively improve combustion
Oil flame tube head residence time, to improve blending and the burning time of fuel oil and air, while evaporation tube 11
Arrangement form makes the fuel oil in burner inner liner form eddy flow, and combustion stability and efficiency of combustion in burner inner liner can be improved in this.
It please also refer to Fig. 1 and Fig. 2, further details of explanation, casing made to the solution of the present invention in the present embodiment
With circular casing interlayer, casing interlayer is enclosed by casing antetheca 1, casing rear wall 2, casing outer wall 3 and casing inner wall 4
It being formed, burner inner liner is embedded in casing interlayer by casing antetheca 1, and the combustion chamber of circular ring shape is integrally embedded in casing interlayer,
Combustion chamber is specifically enclosed by burner inner liner antetheca 5, burner inner liner rear wall 6, flame drum outer wall 7 and burner inner liner inner wall 8；
Burner inner liner and casing antetheca position seals cooperate, so as to form airstream compartment, machine between burner inner liner and casing interlayer
The inlet channel I communicated with airstream compartment is offered on casket outer wall 3, as shown in fig. 1, in flame drum outer wall 7 and/or burner inner liner
The air inlet communicated with air flow chamber is offered on wall 8, in order to guarantee that charge air flow is uniform, is recommended outside burner inner liner in the present embodiment
Air inlet is opened up on wall 7 and burner inner liner inner wall 8, more preferably, is offered on three rows respectively on burner inner liner inner and outer wall
Air inlet is stated, to guarantee combustion chamber abundance and uniform air inlet；
The fire hole 12 for installing igniter, combustion chamber oil supplying hole 14 are offered on casing outer wall 3 and flame drum outer wall 7
It is provided on flame drum outer wall 7, casing oil supplying hole 13 corresponding with combustion chamber oil supplying hole 14 is offered on casing outer wall 3.
It needs to be illustrated, the diameter of combustion chamber oil supplying hole 14 should be not more than the diameter of evaporation tube 11, it is preferred that
The diameter of combustion chamber oil supplying hole 14 is equal with the diameter of evaporation tube 11 or is slightly less than the diameter of evaporation tube 11, this can guarantee by
The fuel oil that casing oil supplying hole 13 sprays into passes through combustion chamber oil supplying hole 14 and enters evaporation tube 11；In above-described embodiment " preceding,
Afterwards, inside and outside " these nouns of locality are really to be named according to the state after burning chamber assembly installation, burning chamber assembly installation
State afterwards is as shown in fig. 1, and left end is usually the front end of aircraft, and right end is the rear end of aircraft, therefore casing and burner inner liner
Wall surface positioned at front end is known as antetheca, and the wall surface positioned at rear end is known as rear wall, and practical annular-shaped combustor's center line is aircraft
Inside, therefore casing and burner inner liner are known as inner wall close to the wall surface of combustion chamber centerline, avoid claiming far from combustion chamber centerline
For outer wall.
In above-described embodiment, casing antetheca 1, casing rear wall 2, casing outer wall 3 and the casing inner wall 4 of casing interlayer are constituted
Can be split type structure, by assembling after be combined together, such as can by the welding processing of gradation formed casing interlayer,
Certainly, casing interlayer itself can also be an integral structure；Similarly, burner inner liner can also be split type structure or integral type knot
Structure, no matter casing or burner inner liner, size can according to different requirements carry out adaptive change.
With continued reference to FIG. 1, flame drum outer wall 7 and the sealing of casing antetheca 1 cooperate, burner inner liner inner wall 8 is connected by casing
Arm 9 and the sealing of casing interlayer cooperate, and to form said flow cavity, casing linking arm 9 and burner inner liner antetheca 5 form gas outlet
Channel O, combustion chamber oil supplying hole 14 are located at flame drum outer wall 7 close to one end of burner inner liner rear wall 6, to make evaporation tube 11 be located at combustion
In the primary zone for burning room, burner inner liner rear wall 6 and casing rear wall 2 are arc-shaped bending, so that the rear end of air flow chamber be made to be formed
Arc baffling end.
Incoming air is entered in airstream compartment by inlet channel I, and inlet channel I and airstream compartment can be according to realities
The watt level of border engine adjusts to be designed, and incoming air is formed by arc by burner inner liner rear wall 6 and casing rear wall 2
Shape baffling end carries out baffling, and then enters in combustion chamber from the air inlet on burner inner liner inner wall 8 and flame drum outer wall 7 and fired
Burn, at the same time, fuel oil by casing oil supplying hole 13, combustion chamber oil supplying hole 14 enter evaporation tube 11 in, in evaporation tube 11 into
It is sprayed into after row adequately evaporation atomization and participates in burning in combustion chamber, the combustion gas after burning is discharged by gas outlet channel O, combustion gas
Exit passageway O is actually the installation site of turbo blade, therefore the size of gas outlet channel O can be according to the ruler of turbine
It is very little to be adjusted.
In order to advanced optimize the technical solution in above-described embodiment, also it is arranged on burner inner liner inner wall 8 in the present embodiment
Gear flame structure 10, on the section for crossing burner inner liner axis, gear flame structure 10 is wedge shaped, and keeps off flame structure 10 close to burner inner liner
One end of rear wall 6 is the closed angle end of wedge shape, as shown in fig. 1.The setting of gear flame structure 10 can be formed in combustion chamber low
Fast recirculating zone, is conducive to the combustion stability for improving combustion chamber, and gear flame structure 10 can guide outside high-temperature fuel gas impacting flame cylinder
Wall 7 and burner inner liner antetheca 5, this can be with the air in pre-heated air flow cavity, to be conducive to tissue burning.
In the present embodiment, combustion chamber oil supplying hole 14 specifically includes six, and six combustion chamber oil supplying holes 14 are along combustion chamber
Circumferencial direction is uniformly distributed, correspondingly, casing oil supplying hole 13 and evaporation tube 11 should also be as being six, as shown in Figure 2, and certainly,
Those skilled in the art can also be arranged the combustion chamber oil supplying hole 14 and casing oil supplying hole 13 of other numbers, in the embodiment of the present invention
With no restriction to this.
Its axis is parallel to horizontal plane to burning chamber assembly during installation, as shown in fig. 1, in installation condition, fire hole
12 and the angle of vertical plane are γ, wherein 15 ° < γ < 45 °.
It will be appreciated to those of skill in the art that the angle of all evapn pipe 11 and the via hole radial line corresponding to itself
α can be equal or unequal, as long as can guarantee that the fuel oil sprayed by evaporation tube 11 forms eddy flow, in the present embodiment
In, recommend by all evapn pipe 11 with itself corresponding to via hole radial line angle α be designed to it is equal, and angle [alpha] satisfaction:
30 ° < α < 60 °, in the range, the indoor combustion stability of burning can be improved to the greatest extent.
The center line of casing oil supplying hole 13 with and the angle of the corresponding via hole radial line of the casing oil supplying hole 13 be β, and
Angle β and above-mentioned angle α are unequal, and as shown in Figure 2, this is conducive to fuel oil and is injected on the wall surface of evaporation tube 11, thus
Improve fuel atomization effect, it is preferred that angle β meets: 15 ° < β < 45 °, six evaporation tubes 11 are circumferentially uniformly distributed, fuel oil
It can circumferentially be sprayed into combustion chamber by evaporation tube 11, so that eddy flow is formed, so that the residence time of head of combustion chamber air-flow increases
Add, improves the efficiency of combustion in head of combustion chamber region, and then improve the Exit temperature distribution of combustion chamber, the performance of combustion chamber obtains
Larger promotion.
Above to it is provided by the present invention it is miniature talk turbogenerator and its burning chamber assembly be described in detail.This
Apply that a specific example illustrates the principle and implementation of the invention in text, the explanation of above example is only intended to
It facilitates the understanding of the method and its core concept of the invention.It should be pointed out that for those skilled in the art,
Without departing from the principles of the invention, can be with several improvements and modifications are made to the present invention, these improvement and modification are also fallen
Enter in the protection scope of the claims in the present invention.
Claims (13)
1. a kind of burning chamber assembly of micro gas turbine engine, including burner inner liner and casing, which is characterized in that the flame
There is the combustion chamber of circular ring shape in cylinder, multiple combustion chambers for spraying fuel oils into the combustion chamber are offered on the burner inner liner and are supplied
Oilhole (14), the combustion chamber oil supplying hole (14) are additionally provided with along the circumferentially distributed of the combustion chamber, and in the combustion chamber
The one-to-one evaporation tube (11) of the combustion chamber oil supplying hole (14), the first end of any one evaporation tube (11) are each attached to
It is connected on the burner inner liner and with the corresponding combustion chamber oil supplying hole (14), the equal direction of second end via hole corresponding with itself is radial
The same side of line, which tilts, to be extended, and each described evaporation tube (11) with itself corresponding to via hole radial line angle α it is big
In 0 °, wherein the via hole radial line is to be originated by the center of circle of the combustion chamber, and the excessively described combustion chamber oil supplying hole (14) is straight
Line.
2. burning chamber assembly according to claim 1, which is characterized in that
The casing has a circular casing interlayer, the casing interlayer by casing antetheca (1), casing rear wall (2), casing outside
Wall (3) and casing inner wall (4) are enclosed；
The burner inner liner is embedded in the casing interlayer by the casing antetheca (1), and the combustion chamber of the circular ring type is integrally embedding
In the casing interlayer, the combustion chamber is by burner inner liner antetheca (5), burner inner liner rear wall (6), flame drum outer wall (7) and fire
Flame cylinder inner wall (8) is enclosed；
The burner inner liner and casing antetheca sealing cooperate, and are reserved with air-flow between the burner inner liner and the casing interlayer
Cavity offers the inlet channel (I) communicated with the airstream compartment, the flame drum outer wall (7) on the casing outer wall (3)
And/or the air inlet communicated with the airstream compartment is offered on the burner inner liner inner wall (8)；
The fire hole (12) for installing igniter is offered on the casing outer wall (3) and the flame drum outer wall (7), it is described
Combustion chamber oil supplying hole (14) is provided on the flame drum outer wall (7), is offered and the combustion chamber on the casing outer wall (3)
The corresponding casing oil supplying hole (13) of oil supplying hole (14).
3. burning chamber assembly according to claim 1, which is characterized in that each described evaporation tube (11) and itself institute are right
The angle α for the via hole radial line answered is equal.
4. burning chamber assembly according to claim 3, which is characterized in that any one evaporation tube (11) and itself institute are right
The angle α for the via hole radial line answered meets: 30 ° < α < 60 °.
5. burning chamber assembly according to any one of claims 1-4, which is characterized in that the combustion chamber oil supplying hole (14)
It is uniformly distributed in the circumferential direction of the combustion chamber.
6. according to burning chamber assembly described in claim 2-4 any one, which is characterized in that the flame drum outer wall (7) with
Casing antetheca (1) the sealing cooperation, the burner inner liner inner wall (8) are sealed by casing linking arm (9) and the casing interlayer
Cooperation, the casing linking arm (9) and the burner inner liner antetheca (5) form gas outlet channel (O), the combustion chamber oil supplying hole
(14) it is located at close to one end of the burner inner liner rear wall (6).
7. burning chamber assembly according to claim 2, which is characterized in that the center line of the casing oil supplying hole (13) with and
The angle of its corresponding via hole radial line is β, and β and α is unequal.
8. burning chamber assembly according to claim 7, which is characterized in that the center line of the casing oil supplying hole (13) with and its is right
The angle β for the via hole radial line answered meets: 15 ° < β < 45 °.
9. burning chamber assembly according to claim 2, which is characterized in that its axis is parallel to water when the burning chamber assembly is installed
Plane, and in installation condition, the angle of the fire hole (12) and vertical plane is γ, wherein 15 ° < γ < 45 °.
10. burning chamber assembly according to claim 2, which is characterized in that the burner inner liner rear wall (6) and the casing rear wall
It (2) is arc-shaped bending, so that the rear end of the airstream compartment forms arc baffling end.
11. burning chamber assembly according to claim 1, which is characterized in that the combustion chamber oil supplying hole (14) includes six.
12. burning chamber assembly according to claim 2, which is characterized in that further include being arranged on the burner inner liner inner wall (8)
It keeps off flame structure (10), on the section of the excessively described burner inner liner axis, the gear flame structure (10) is wedge shaped, wherein the gear flame
Structure (10) is the closed angle end of the wedge shape close to one end of the burner inner liner rear wall (6).
13. a kind of micro gas turbine engine, including burning chamber assembly, which is characterized in that the burning chamber assembly is as weighed
Benefit requires burning chamber assembly described in 1-12 any one.
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| CN201810895086.7A CN108954387B (en) | 2018-08-08 | 2018-08-08 | Miniature gas turbine engine and combustion chamber assembly thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810895086.7A CN108954387B (en) | 2018-08-08 | 2018-08-08 | Miniature gas turbine engine and combustion chamber assembly thereof |
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| CN108954387B CN108954387B (en) | 2020-04-14 |
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Cited By (4)
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| CN110043922A (en) * | 2019-04-24 | 2019-07-23 | 北京航空航天大学 | A kind of micro gas turbine engine and its reverse-flow can type combustor assembly |
| CN111520754A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Novel miniature aeroengine combustion chamber |
| CN112902230A (en) * | 2021-03-11 | 2021-06-04 | 西北工业大学 | Inclined inlet double-head two-stage swirler combustion chamber |
| CN114484501A (en) * | 2022-02-16 | 2022-05-13 | 浙江意动科技股份有限公司 | Evaporation tube type combustion chamber |
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