CN110043922A - A kind of micro gas turbine engine and its reverse-flow can type combustor assembly - Google Patents
A kind of micro gas turbine engine and its reverse-flow can type combustor assembly Download PDFInfo
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- CN110043922A CN110043922A CN201910334808.6A CN201910334808A CN110043922A CN 110043922 A CN110043922 A CN 110043922A CN 201910334808 A CN201910334808 A CN 201910334808A CN 110043922 A CN110043922 A CN 110043922A
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- casing
- wall
- combustion chamber
- inner liner
- burner inner
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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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/30—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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The present invention relates to a kind of reverse-flow can type combustor assemblies of micro gas turbine engine, including casing and the burner inner liner being nested in casing, flame drum outer wall, burner inner liner inner wall and burner inner liner rear wall are enclosed the combustion chamber of circular ring type, multiple combustion chamber oil supplying holes that fuel oil is sprayed into combustion chamber are offered on burner inner liner rear wall, combustion chamber oil supplying hole is along the circumferentially distributed of combustion chamber, and it is additionally provided in combustion chamber and the one-to-one evaporation tube of combustion chamber oil supplying hole, the first end of any one evaporation tube is each attached on burner inner liner rear wall and is connected to respective combustion chamber oil supplying hole, the side that second end is directed away from burner inner liner rear wall extends, and centerline axis parallel of the axis of each evaporation tube with combustion chamber.The reverse-flow can type combustor assembly can improve combustion stability and efficiency of combustion in burner inner liner under the premise of realizing micromation.The invention also discloses a kind of micro gas turbine engines using above-mentioned reverse-flow can type combustor assembly.
Description
Technical field
The present invention relates to micro gas turbine engine Combustion chamber design fields more particularly to a kind of micro gas turbine to send out
Motivation and its reverse-flow can type combustor assembly.
Background technique
Gas-turbine unit is a kind of dynamic power machine for being widely used in many industrial circles such as aviation, ship, electric power,
Play the role of in the development of national economy vital.Micro gas turbine engine has very compared with other engines
More advantages, in specific fuel consumption, noise, discharge has huge advantage in terms of vibration, cannot be only used for traditional distributed hair
Electricity, and can be used for generate electricity by way of merging two or more grid systems Deng multiple power-generating approaches, it is not only applicable in city, but also rely on carrying side in remote districts
Just it is also widely popularized the advantages of reliable operation；In addition in the communications and transportation such as extra large Lu Bianfang, micro gas turbine engine exists
New-energy automobile, electromechanical processing, metal material etc. is multi-field application, therefore by the concern of each military power.
Core of the reverse-flow can type combustor assembly as gas-turbine unit, its characteristic relation the property of entire engine
Can, for traditional combustion room, there is the micro- of many difficulties, especially combustion chamber for the combustion chamber of micro turbine engine
There is biggish contradictions between type and fuel residence time, specifically, the micromation of combustion chamber means that fuel is firing
It burns indoor residence time to shorten, causes fuel combustion to be not enough, utilization rate is lower；And if wanting to extend fuel in the combustion chamber
Residence time, improve fuel availability then need to make the volume of combustion chamber to increase.
How while realizing burning chamber assembly micromation, additionally it is possible to effectively extend fuel staying in burning chamber assembly
The time is stayed, the technical issues of fuel availability is current those skilled in the art's urgent need to resolve is improved.
Summary of the invention
An object of the present invention is to provide a kind of reverse-flow can type combustor assembly of micro gas turbine engine, so as to
While realizing burning chamber assembly micromation, additionally it is possible to effectively extend residence time of the fuel in burning chamber assembly, improve combustion
Expect utilization rate.
Another object of the present invention, which also resides in, to be provided a kind of gas turbine using above-mentioned reverse-flow can type combustor assembly and starts
Machine.
In order to achieve the above objectives, the reverse-flow can type combustor assembly of micro gas turbine engine provided by the invention, including
Casing and the burner inner liner being nested in the casing, the burner inner liner includes flame drum outer wall, burner inner liner inner wall and burner inner liner
Rear wall, the flame drum outer wall, burner inner liner inner wall and burner inner liner rear wall are enclosed the combustion chamber of circular ring type, the combustion chamber
Front end there is opening, multiple combustion chamber fuel feeding that fuel oils are sprayed into the combustion chamber are offered on the burner inner liner rear wall
Hole, the combustion chamber oil supplying hole are additionally provided with and the burning along the circumferentially distributed of the combustion chamber, and in the combustion chamber
The one-to-one evaporation tube of room oil supplying hole, the first end of any one evaporation tube be each attached on the burner inner liner rear wall and with
The corresponding combustion chamber oil supplying hole connection, the side that second end is directed away from the burner inner liner rear wall extend, and each
Centerline axis parallel of the axis of the evaporation tube with the combustion chamber.
Preferably, the casing have circular ring type 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 flame drum outer wall and casing antetheca sealing cooperate, and the burner inner liner inner wall and the casing inner wall seal
Cooperation, the opening of the burner inner liner front end and the casing antetheca constitute gas outlet channel, and outside the burner inner liner
Airstream compartment is reserved between wall and the casing interlayer, offered on the casing outer wall communicated with the airstream compartment into
Offered on gas channel, the flame drum outer wall and/or the burner inner liner inner wall primary holes communicated with the airstream compartment and
Blending hole；
The fire hole for installing igniter is offered on the casing outer wall and the flame drum outer wall, after the casing
It is offered on wall and the one-to-one casing oil supplying hole of the combustion chamber oil supplying hole.
Preferably, the axis of the casing oil supplying hole passes through the combustion chamber oil supplying hole and the inner wall phase with the evaporation tube
It hands over, the angle between the axis of the casing oil supplying hole and the axis of the evaporation tube is α, and the casing oil supplying hole is described in
The distance of casing outer wall is less than the casing oil supplying hole to the distance of the casing inner wall.
Preferably, the angle α between the axis of casing oil supplying hole and the axis of the evaporation tube meets: 15 ° < α < 45 °.
Preferably, the combustion chamber oil supplying hole is uniformly distributed in the circumferential direction of the combustion chamber.
Preferably, burner inner liner inner wall front end is additionally provided with the flanging extended towards the flame drum outer wall, the folding
Side constitutes the flame baffle for delaying combustion gas to be discharged.
Preferably, its axis is parallel to horizontal plane when the burning chamber assembly is installed, and in installation condition, the igniting
Hole and the angle of the vertical plane of the axis of the excessively described burning chamber assembly are β, wherein 15 ° < β < 45 °.
Preferably, the burner inner liner rear wall and the casing rear wall are semicircular arc, and the casing rear wall and institute
It states burner inner liner rear wall and constitutes the arc baffling end for making air-flow turn back to the front end of the combustion chamber.
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.
Preferably, the second end of the evaporation tube has the flaring of bell mouth shape.
Preferably, the evaporation tube includes 3~8.
Preferably, the diameter of the combustion chamber oil supplying hole is equal with the diameter of the evaporation tube.
Disclosed in this invention micro gas turbine engine, including reverse-flow can type combustor assembly, the reverse-flow type combustion
Burning chamber assembly is the burning chamber assembly disclosed in above-mentioned 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 type in the circumferential, and each combustion chamber oil supplying hole correspondence is set
It is equipped with an evaporation tube, the first end of evaporation tube is connected with burner inner liner, and second end is directed away from the side of burner inner liner rear wall
Extend, in Fuel injection system, fuel oil is injected in first on the inner wall of evaporation tube, then evaporation rapidly at high temperature, evaporation tube
It is provided with the evaporation conducive to fuel oil, improves atomizing effect when fuel oil enters combustion chamber, this can effectively improve fuel oil in fire
The residence time on flame cylinder head, to improve blending and the burning time of fuel oil and air, while the axis of each evaporation tube
Centerline axis parallel of the line with the combustion chamber, this kind layout allow entire combustion chamber to keep lesser size, improve
The compactedness of reverse-flow can type combustor assembly.
It can be seen that disclosed in this invention reverse-flow can type combustor assembly, not only extend fuel burning chamber assembly
Interior residence time improves fuel availability, but also combustion chamber is made to be maintained at lesser size, improves burning chamber assembly
Compactedness, realize burning chamber assembly micromation.
Micro gas turbine engine disclosed in this invention, should due to using above-mentioned reverse-flow can type combustor assembly
Micro turbine engine has both the above-mentioned corresponding technological merit of reverse-flow can type combustor assembly, is no longer repeated this herein.
Detailed description of the invention
Fig. 1 is the section view of the reverse-flow can type combustor assembly of the micro gas turbine engine disclosed in the embodiment of the present invention
Schematic diagram；
Fig. 2 is the left side schematic cross-sectional view of Fig. 1；
Wherein, 1 be casing antetheca, 2 be casing outer wall, 3 be casing rear wall, 4 be casing inner wall, 5 be flame drum outer wall, 6
It is burner inner liner inner wall for burner inner liner rear wall, 7,8 be gear flame structure, and 9 be evaporation tube, and 10 be combustion chamber oil supplying hole, and 11 supply for casing
Oilhole, 12 be fire hole.
Specific embodiment
Core of the invention first is that a kind of reverse-flow can type combustor assembly for micro gas turbine engine, so as in reality
Now while the micromation of burning chamber assembly, additionally it is possible to effectively extend residence time of the fuel in burning chamber assembly, improve fuel
Utilization rate.
Another core of the invention, which also resides in, to be provided a kind of gas turbine using above-mentioned reverse-flow can type combustor assembly and starts
Machine.
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 reverse-flow can type combustor it is total
At including casing and the burner inner liner that is nested in casing, wherein burner inner liner include flame drum outer wall 5, burner inner liner inner wall 7 and
Burner inner liner rear wall 6, flame drum outer wall 5, burner inner liner inner wall 7 and burner inner liner rear wall 6 are enclosed the combustion chamber of circular ring shape, burning
The front end of room has opening, and multiple combustion chamber oil supplying holes that fuel oil is sprayed into combustion chamber are offered on burner inner liner rear wall 6
10, circumferencial direction of the combustion chamber oil supplying hole 10 along combustion chamber is distributed, and is additionally provided in combustion chamber and combustion chamber oil supplying hole 10
One-to-one evaporation tube 9, the first end of each evaporation tube 9 are fixed on burner inner liner rear wall 6, and with it is corresponding
Combustion chamber oil supplying hole 10 is connected to, to guarantee smoothly to be injected on the inner wall of evaporation tube 9 by the fuel oil of combustion chamber oil supplying hole 10, often
The side that the second end of one evaporation tube 9 is directed away from burner inner liner rear wall 6 extends, and the axis of each evaporation tube 9 is equal
With the centerline axis parallel of combustion chamber.
As shown in fig. 1, as preferred mode, the second end of evaporation tube 9 is provided with trumpet flare, to improve fuel oil
Evaporation effect.
It needs to explain, the front end of Flame cylinder of the present invention refers to the one end of burner inner liner far from burner inner liner rear wall 6.
In the reverse-flow can type combustor assembly of micro gas turbine engine disclosed in above-described embodiment, the combustion of circular ring type
It burns interior and multiple combustion chamber oil supplying holes 10 is distributed in the circumferential, and each combustion chamber oil supplying hole 10 is correspondingly arranged on a steaming
Pipe 9 is sent out, the first end of evaporation tube 9 is connected with burner inner liner, and the side that second end is directed away from burner inner liner rear wall 6 extends, and steams
The evaporation being provided with conducive to fuel oil for sending out pipe 9, improves atomizing effect when fuel oil enters combustion chamber, this can effectively improve combustion
Oil is in the residence time of flame tube head, to improve blending and the burning time of fuel oil and air, while each is evaporated
Centerline axis parallel of the axis of pipe 9 with the combustion chamber, this kind layout allow entire combustion chamber to keep lesser ruler
It is very little, improve the compactedness of reverse-flow can type combustor assembly.
The reverse-flow can type combustor assembly not only extends residence time of the fuel in burning chamber assembly, improves fuel
Utilization rate, but also combustion chamber is made to be maintained at lesser size, the compactedness of burning chamber assembly is improved, it is total to realize combustion chamber
At micromation.
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
Casing interlayer with circular ring type, casing interlayer are enclosed by casing antetheca 1, casing rear wall 3, casing outer wall 2 and casing inner wall 4
It is formed, burner inner liner is embedded in casing interlayer by casing antetheca 1, and the combustion chamber of circular ring type is integrally embedded in casing interlayer；
Flame drum outer wall 5 and 1 position seals of casing antetheca cooperate, and burner inner liner inner wall 7 and the sealing of casing inner wall 4 cooperate, with
Make to form airstream compartment between burner inner liner and casing interlayer, the inlet channel communicated with airstream compartment is offered on casing outer wall 2
I offers the master communicated with air flow chamber on one of both flame drum outer wall 5 and burner inner liner inner wall 7 as shown in fig. 1
Combustion offers primary holes and blending hole on hole and blending hole, or both, in order to guarantee that charge air flow is uniform, in the present embodiment
Recommendation opens up primary holes and blending hole on flame drum outer wall 5 and burner inner liner inner wall 7, more preferably, 7 He of burner inner liner inner wall
Row's primary holes and two rows of blending holes are offered on flame drum outer wall 5, it is sufficiently uniform with blending with guarantee burning；
The fire hole 12 for installing igniter is offered on casing outer wall 2 and flame drum outer wall 5, is opened on casing rear wall 3
Equipped with the one-to-one casing oil supplying hole 11 of combustion chamber oil supplying hole 10.
As shown in fig. 1, the extended line of the axis of casing oil supplying hole 11 by combustion chamber oil supplying hole 10 and with evaporation tube 9
Inner wall intersection guarantees atomization and evaporation effect so that fuel oil is injected in first on the inner wall of evaporation tube 9, extends fuel and is burning
Indoor residence time, casing oil supplying hole 11 and evaporation tube 9 are not face in the axial direction, but have angle between each other, such as
Shown in Fig. 1, the angle between the axis of casing oil supplying hole 11 and the axis of evaporation tube 9 is α, and casing oil supplying hole 11 arrives machine
The distance of casket outer wall 2 is less than casing oil supplying hole 11 and arrives the distance between casing inner wall 4, implies that casing oil supplying hole 11 outside casing
Wall 2 is arranged.
It needs to be illustrated, the diameter of combustion chamber oil supplying hole 10 should be not more than the diameter of evaporation tube 9, it is preferred that
The diameter of combustion chamber oil supplying hole 10 is equal with the diameter of evaporation tube 9 or is slightly less than the diameter of evaporation tube 9, this can guarantee by machine
The fuel oil that casket oil supplying hole 11 sprays into passes through combustion chamber oil supplying hole 10 and enters evaporation tube 9；In above-described embodiment " forward and backward,
It is inside and outside " these nouns of locality are really to be named according to the state after burning chamber assembly installation, after burning chamber assembly installation
State 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 are located at
The wall surface of front end is known as antetheca, and the wall surface positioned at rear end is known as rear wall, circular ring type combustion chamber centerline is practical be aircraft inside,
Therefore casing and burner inner liner are known as inner wall close to the wall surface of combustion chamber centerline, avoiding far from combustion chamber centerline is referred to as outer
Wall.
In above-described embodiment, casing antetheca 1, casing rear wall 3, casing outer wall 2 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 5 and the sealing of casing antetheca 1 cooperate, burner inner liner inner wall 7 and casing inner wall 4 are close
Envelope cooperation, the two positions can mode through the joint of the seam allowance realize positioning and sealing, casing antetheca 1 and burner inner liner front end
Opening form gas outlet channel O, burner inner liner rear wall 6 and casing rear wall 3 are semicircular arc, and casing rear wall 3 and fire
Flame cylinder rear wall 6 constitutes the arc baffling end for making air-flow turn back to the front end of the combustion chamber.
As preferred mode, the angle α between the axis of casing oil supplying hole 11 and the axis of the evaporation tube 9 meets:
15 ° < α < 45 °, within this range by angle setting, the indoor combustion stability of burning can be improved to the greatest extent.
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 3
Shape baffling end carry out baffling, and then from burner inner liner inner wall 7 and flame drum outer wall 5 primary holes and blending hole enter combustion chamber
It inside burns, at the same time, fuel oil is entered in evaporation tube 9 by casing oil supplying hole 11, combustion chamber oil supplying hole 10, in evaporation tube
It carries out spraying into after adequately evaporation is atomized in 9 and participates in burning in combustion chamber, the combustion gas after burning is arranged by gas outlet channel O
Out, gas outlet channel O is actually the installation site of turbo blade, therefore the size of gas outlet channel O can basis
The size of turbine is adjusted.
In order to advanced optimize the technical solution in above-described embodiment, also in the front end of burner inner liner inner wall 7 in the present embodiment
Provided with flanging, which constitutes the flame baffle for delaying combustion gas to be discharged, as shown in fig. 1, further, burner inner liner
Gear flame structure 8 is additionally provided on inner wall 7, on the section for crossing burner inner liner axis, gear flame structure 8 is wedge shaped, and keeps off flame structure 8
It is the closed angle end of wedge shape close to one end of burner inner liner rear wall 6.The setting of gear flame structure 8 can to form low speed time in combustion chamber
Area is flowed, the combustion stability for improving combustion chamber is conducive to；In addition to this, flame baffle can preferably export high-temperature fuel gas to whirlpool
Acting is taken turns, while keeping off flame structure 8 to guide high-temperature fuel gas impacting flame drum outer wall 5 and casing antetheca 1, this can pre- hot gas
The air in cavity is flowed, to improve ignition performance.
The quantity of combustion chamber oil supplying hole 10 is 3~8, and in the embodiment shown in Figure 2, combustion chamber oil supplying hole 10 specifically wraps
Six are included, circumferencial direction of six combustion chamber oil supplying holes 10 along combustion chamber is uniformly distributed, correspondingly, casing oil supplying hole 11 and evaporation
Pipe 9 should also be as being six, and certainly, the combustion chamber oil supplying hole 10 of other numbers can also be arranged in those skilled in the art and casing supplies
Oilhole 11, in the embodiment of the present invention with no restriction to this.
Its axis (i.e. the central axis of circular ring type combustion chamber) is parallel to horizontal plane to reverse-flow can type combustor assembly during installation,
As shown in fig. 1, in installation condition, fire hole 12 and the angle for crossing the vertical plane of burning chamber assembly are β, wherein 15 ° < β <
45°。
In addition to this, a kind of micro gas turbine engine, including reverse-flow can type combustor assembly are also disclosed in the present invention,
And the reverse-flow can type combustor assembly is the reverse-flow can type combustor assembly disclosed in above-mentioned any one embodiment.
Due to using above-mentioned reverse-flow can type combustor assembly, which has both above-mentioned reverse-flow type
Burn the corresponding technological merit of chamber assembly, is no longer repeated this herein.
Micro gas turbine engine provided by the present invention and its reverse-flow can type combustor assembly have been carried out in detail above
It introduces.Used herein a specific example illustrates the principle and implementation of the invention, the explanation of above embodiments
It is merely used to help understand method and its core concept of the invention.It should be pointed out that for the ordinary skill people of the art
Member for, without departing from the principle of the present invention, can with several improvements and modifications are made to the present invention, these improve and
Modification is also fallen within the protection scope of the claims of the present invention.
Claims (10)
1. the reverse-flow can type combustor assembly of a kind of micro gas turbine engine, including casing and the fire being nested in the casing
Flame cylinder, the burner inner liner include flame drum outer wall (5), burner inner liner inner wall (7) and burner inner liner rear wall (6), which is characterized in that institute
State the combustion chamber that flame drum outer wall (5), burner inner liner inner wall (7) and burner inner liner rear wall (6) are enclosed circular ring type, the burning
The front end of room has opening, and multiple combustion chambers that fuel oil is sprayed into the combustion chamber are offered on the burner inner liner rear wall (6)
Oil supplying hole (10), the combustion chamber oil supplying hole (10) also set up along the circumferentially distributed of the combustion chamber, and in the combustion chamber
Have and is fixed with the one-to-one evaporation tube (9) of the combustion chamber oil supplying hole (10), the first end of any one evaporation tube (9)
It is connected on the burner inner liner rear wall (6) and with the corresponding combustion chamber oil supplying hole (10), second end is directed away from the fire
The side of flame cylinder rear wall (6) extends, and the axis of each evaporation tube (9) is flat with the central axis of the combustion chamber
Row.
2. reverse-flow can type combustor assembly according to claim 1, which is characterized in that
The casing have circular ring type casing interlayer, the casing interlayer by casing antetheca (1), casing rear wall (3), casing outside
Wall (2) 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 flame drum outer wall (5) and the casing antetheca (1) sealing cooperate, in the burner inner liner inner wall (7) and the casing
Wall (4) sealing cooperation, the opening of the burner inner liner front end and the casing antetheca (1) constitute gas outlet channel, and
It is reserved with airstream compartment between the flame drum outer wall (5) and the casing interlayer, is offered on the casing outer wall (2) and institute
The inlet channel that airstream compartment communicates is stated, is offered on the flame drum outer wall (5) and/or the burner inner liner inner wall (7) and institute
State the primary holes and blending hole that airstream compartment communicates；
The fire hole (12) for installing igniter is offered on the casing outer wall (2) and the flame drum outer wall (5), it is described
It is offered on casing rear wall (3) and the one-to-one casing oil supplying hole (11) of the combustion chamber oil supplying hole (10).
3. reverse-flow can type combustor assembly according to claim 1, which is characterized in that the axis of the casing oil supplying hole (11)
Intersect by the combustion chamber oil supplying hole (10) and with the inner wall of the evaporation tube (9), the axis of the casing oil supplying hole (11)
Angle between the axis of the evaporation tube (9) is α, and the casing oil supplying hole (11) to the casing outer wall (2) away from
It is arrived with a distance from the casing inner wall (4) from the casing oil supplying hole (11) is less than.
4. reverse-flow can type combustor assembly according to claim 3, which is characterized in that the axis of casing oil supplying hole (11) and institute
The angle α stated between the axis of evaporation tube (9) meets: 15 ° < α < 45 °.
5. reverse-flow can type combustor assembly according to any one of claims 1-4, which is characterized in that the combustion chamber fuel feeding
Hole (10) is uniformly distributed in the circumferential direction of the combustion chamber.
6. reverse-flow can type combustor assembly according to any one of claims 1-4, which is characterized in that the burner inner liner inner wall
(7) front end is additionally provided with the flanging extended towards the flame drum outer wall (5), and the flanging is constituted for delaying combustion gas to be discharged
Flame baffle.
7. reverse-flow can type combustor assembly according to claim 2, which is characterized in that the reverse-flow can type combustor assembly installation
When its axis be parallel to horizontal plane, and in installation condition, the fire hole (12) and the excessively described reverse-flow can type combustor assembly
The angle of the vertical plane of axis is β, wherein 15 ° < β < 45 °.
8. reverse-flow can type combustor assembly according to claim 2, which is characterized in that the burner inner liner rear wall (6) and institute
Stating casing rear wall (3) is semicircular arc, and the casing rear wall (3) and the burner inner liner rear wall (6) composition make air-flow to institute
State the arc baffling end that the front end of combustion chamber is turned back.
9. reverse-flow can type combustor assembly according to claim 2, which is characterized in that further include being arranged in the burner inner liner
Gear flame structure (8) on wall (7), on the section of the excessively described burner inner liner axis, the gear flame structure (8) is wedge shaped, wherein institute
State closed angle end of gear flame structure (8) close to one end of the burner inner liner rear wall (6) for the wedge shape.
10. a kind of micro gas turbine engine, including reverse-flow can type combustor assembly, which is characterized in that the reverse-flow type burning
Chamber assembly is reverse-flow can type combustor assembly as described in any one of claims 1-9.
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| CN201910334808.6A CN110043922A (en) | 2019-04-24 | 2019-04-24 | A kind of micro gas turbine engine and its reverse-flow can type combustor assembly |
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| CN201910334808.6A CN110043922A (en) | 2019-04-24 | 2019-04-24 | A kind of micro gas turbine engine and its reverse-flow can type combustor assembly |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111023155A (en) * | 2019-12-31 | 2020-04-17 | 西安增材制造国家研究院有限公司 | Secondary flow evaporation tube type combustion chamber structure |
| CN112082176A (en) * | 2020-09-14 | 2020-12-15 | 清华大学 | Combustion chamber structure of micro turbojet engine |
| CN112902227A (en) * | 2021-03-04 | 2021-06-04 | 西北工业大学 | Multi-channel evaporating pipe of combustion chamber of micro engine |
| CN114110659A (en) * | 2021-11-30 | 2022-03-01 | 中国航发湖南动力机械研究所 | Evaporating pipe atomizing device and combustion chamber |
| CN114165813A (en) * | 2021-12-03 | 2022-03-11 | 北京航空航天大学 | Pneumatic auxiliary integrated support plate stabilizer with double oil way oil supply |
| CN116428615A (en) * | 2023-05-23 | 2023-07-14 | 浙江大学 | Circumferential circulation combustor between turbine stages |
| CN112082176B (en) * | 2020-09-14 | 2024-06-04 | 清华大学 | Combustion chamber of miniature turbojet engine |
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| CN112082176A (en) * | 2020-09-14 | 2020-12-15 | 清华大学 | Combustion chamber structure of micro turbojet engine |
| CN112082176B (en) * | 2020-09-14 | 2024-06-04 | 清华大学 | Combustion chamber of miniature turbojet engine |
| CN112902227A (en) * | 2021-03-04 | 2021-06-04 | 西北工业大学 | Multi-channel evaporating pipe of combustion chamber of micro engine |
| CN114110659A (en) * | 2021-11-30 | 2022-03-01 | 中国航发湖南动力机械研究所 | Evaporating pipe atomizing device and combustion chamber |
| CN114165813A (en) * | 2021-12-03 | 2022-03-11 | 北京航空航天大学 | Pneumatic auxiliary integrated support plate stabilizer with double oil way oil supply |
| CN114165813B (en) * | 2021-12-03 | 2022-08-30 | 北京航空航天大学 | Pneumatic auxiliary integrated support plate stabilizer with double oil way oil supply |
| CN116428615A (en) * | 2023-05-23 | 2023-07-14 | 浙江大学 | Circumferential circulation combustor between turbine stages |
| CN116428615B (en) * | 2023-05-23 | 2024-05-10 | 浙江大学 | Circumferential circulation combustor between turbine stages |
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Application publication date: 20190723 |