CN110300872A - Burner and gas turbine - Google Patents
Burner and gas turbine Download PDFInfo
- Publication number
- CN110300872A CN110300872A CN201880012407.2A CN201880012407A CN110300872A CN 110300872 A CN110300872 A CN 110300872A CN 201880012407 A CN201880012407 A CN 201880012407A CN 110300872 A CN110300872 A CN 110300872A
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- CN
- China
- Prior art keywords
- burner
- circumferential
- main burning
- mouth
- configuration
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
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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
-
- 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
-
- 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
- F23R3/34—Feeding into different combustion zones
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
Abstract
Burner of the invention is used as main burning mouth (16) for the first burner (16A) and the second burner (16B), first burner (16A) makes primary air circle round and generate gaseous mixture, and second burner (16B) makes primary air generate gaseous mixture to the direction convolution opposite with the first burner (16A).The main burning mouth (16) is circumferentially spaced to be positioned apart from multiple, is configured with first burner (16A) and second burner (16B) on the circumferential complete cycle with acyclic configuration mode.
Description
Technical field
The present invention relates to burner and gas turbines.
The application CLAIM OF PRIORITY based on 2 21st, 2017 Patents 2017-029640 in Japanese publication, and will
Its content is incorporated herein.
Background technique
In the burner of gas turbine, have multiple main burnings of circumferentially the same shape arranged at equal interval sometimes
Mouth.
Describe following technology in patent document 1, that is, realized to form large-scale combustion flame stability and
Low emission, by make fuel supply nozzle downstream it is different from the mixing passage shape of air, so that it is short to form big outer diameter
Flame and elongated flame.
Following technology is described in patent document 2, that is, multiple is had and centerline axis parallel configures along axial be equipped with
Rotary shaft cyclone burner in, generation when in order to reduce the outer rim interflow by the swirling flow of adjacent cyclone generation
Shearing and realize NOx, CO discharge reduction, is assigned respectively for each cyclone and the convolution direction of adjacent cyclone each other
The swirling flow of opposite direction.
Citation
Patent document
Patent document 1: No. 6931853 specifications of U.S. Patent No.
Patent document 2: No. 9500368 specifications of U.S. Patent No.
Summary of the invention
Subject to be solved by the invention
For example, the flame that is formed by the multiple main burning mouths being circumferentially arranged all identical characteristics the case where
Under, the shape of the flame in circumferential direction becomes the same, and the axial length of flame also becomes the same in the circumferential.
Main burning mouth documented by patent document 2 is configured to the mutual convolution direction of main burning mouth adjacent in the circumferential
Opposite direction.But the flame that main burning mouth is formed as documented by patent document 2 also becomes the same in the circumferential.
In this way, when main burning mouth generates pressure oscillation, flame can be in circumferential direction if forming the same flame in the circumferential
It is upper to generate identical variation.Mutual flame is with same Xiang Biandong, so that the amplitude of the variation of the heat liberation rate, heat release rate in burner becomes larger, combustion
Vibration is burnt to become larger.
It is such in burner as described in Patent Document 1, multiple shapes are used not to make the change in shape of flame
In the case where same main burning mouth, there are the working hours that the manufacture of main burning mouth is spent to increase such project.
The present invention provides a kind of working hour that the manufacture for being able to suppress main burning mouth is spent increase, and inhibits combustion vibration
Generation burner and gas turbine.
Solution for solving the problem
First scheme according to the present invention, burner are standby: so that primary air is circled round and generate the main combustion of conduct of gaseous mixture
First burner of burner；And primary air is made to generate gaseous mixture to the direction convolution opposite with first burner
The second burner as main burning mouth.The main burning mouth is circumferentially spaced be positioned apart from it is multiple, described circumferential
First burner and second burner are configured with acyclic configuration mode on complete cycle.
In this way, passing through first burner and the second burner in the direction direction opposite each other that primary air will be made to circle round
It is aperiodically configured on circumferential complete cycle, be able to suppress becomes the same flame in the circumferential.It is therefore not necessary to use shape
Different a variety of main burning mouths.
Therefore, it is able to suppress the working hour increase that the manufacture of main burning mouth is spent, and inhibits the generation of combustion vibration.
Alternative plan according to the present invention, the first burner and the second burner for being also possible to first scheme are in circumferential direction
On with asymmetrical configuration mode configuration.
Due to not configuring the first burner and the second burner in rotationally symmetrical fashion, it is able to suppress in the circumferential
As the same flame.
Third program according to the present invention, the first burner and the second burner for being also possible to first scheme are with multiple
The position of centre of gravity (concentration center) of the whole heat liberation rate, heat release rate of the main burning mouth is from the circumferential centre bit
Set the configuration mode configuration of offset.
By making with the position of centre of gravity of the heat liberation rate, heat release rate index of the flame based on each main burning mouth from configuring multiple main burnings
The Centre position deviation of mouth inhibits to become the same flame thus, it is possible to break the harmony of the flame in circumferential direction.
Fourth program according to the present invention is also possible to the first burner and the second burner of first scheme with respectively
The size for having synthesized resultant vector obtained from unit vector is the configuration mode configuration of the size of the unit vector or more, should
Unit vector is the radial flowing generated with the boundary of first burner and second burner in the circumferential
The corresponding vector in direction.
It is single by the way that the configuration mode of the first burner and the second burner in the circumferential to be set as to the size of resultant vector
The configuration mode more than size of bit vector inhibits to become the same fire so as to break the harmony of the flame in circumferential direction
Flame.
5th scheme according to the present invention, is also possible in the burner of first scheme, by circumferentially spaced compartment of terrain
Multiple main burning mouths of configuration are divided into the circumferential by one or mutual adjacent multiple main burning mouth structures in the circumferential
At and by identical quantity the group that constitutes of main burning mouth in the case where, the first burner and the second combustion at least one described group
The configuration relation of burner is different from described in other groups.
With this configuration, it is able to suppress and forms the same flame in the circumferential.
6th scheme according to the present invention, gas turbine have the burning of first scheme either a program into the 5th scheme
Device.
With this configuration, the situation for making operating condition become unstable because of combustion vibration can be reduced.
Invention effect
According to said burner and gas turbine, it is able to suppress the working hour increase that the manufacture of main burning mouth is spent, and
Inhibit the generation of combustion vibration.
Detailed description of the invention
Fig. 1 is the figure for indicating the Sketch of gas turbine of first embodiment of the invention.
Fig. 2 is the figure for indicating the Sketch of burner of first embodiment of the invention.
Fig. 3 is the figure for indicating the configuration of main burning mouth of first embodiment of the invention.
Fig. 4 is the figure for indicating the convolution direction of the main burning mouth of first embodiment of the invention.
Fig. 5 is the figure for indicating the position of centre of gravity of heat liberation rate, heat release rate of first embodiment of the invention.
Fig. 6 is the figure for indicating the resultant vector of first embodiment of the invention.
Fig. 7 is the figure for being equivalent to Fig. 4 of second embodiment of the present invention.
Fig. 8 is the figure for being equivalent to Fig. 4 of third embodiment of the present invention.
Fig. 9 is the figure for being equivalent to Fig. 4 of the 4th embodiment of the invention.
Figure 10 is that the longitudinal axis in left side is set as to heat liberation rate, heat release rate center of gravity at a distance from burner centre, and the longitudinal axis on right side is set as closing
At the size of vector, horizontal axis is set as to the curve graph of example number.
Specific embodiment
(first embodiment)
Then, it is illustrated based on burner and gas turbine of the attached drawing to first embodiment of the invention.
As shown in Figure 1, gas turbine 1 has compressor 2, burner 3 and turbine 4.
2 compressed air A of compressor and generate compressed air.Burner 3 keeps fuel F empty in the compression generated by compressor 2
The burning gases of high temperature and pressure are burnt and generated in gas.The combustion gases drive that turbine 4 is generated by burner 3, by burning gases
Energy be converted to rotating energy.
Compressor 2 has compressor drum 6 and compressor case 7.In addition, turbine 4 has turbine rotor 8 and turbine case
9。
Compressor drum 6 is rotated centered on rotation axis Ar with 8 arranged in series of turbine rotor.Turbine rotor 8 and pressure
Contracting machine rotor 6 is joined into one.Gas turbine rotor 10 is constituted by above-mentioned compressor rotor 6 and turbine rotor 8.In the combustion gas
Turbine wheel 10 is for example linked with the rotor of generator GEN.
Compressor case 7 covers compressor drum 6, and is that can rotate by the bearing of compressor drum 6.Turbine case 9 is covered
Lid turbine rotor 8, and be that can rotate by the bearing of turbine rotor 8.Compressor case 7 and turbine case 9 link.By above-mentioned compression
Machine rotor 6 and turbine rotor 8 constitute gas turbine rotor 10.Burner 3 is fixed in the gas turbine shell 11.
As shown in Fig. 2, burner 3 has combustion barrel (or tail pipe) 13 and fuel jetting device 14A.Combustion barrel 13 makes fuel F
It burns inside it.Burning gases obtained from combustion barrel 13 will make fuel F burn are sent to turbine 4.Fuel jetting device 14A to
Fuel F and compressed air A is sprayed in combustion barrel 13.
As shown in figure 3, fuel jetting device 14A has pilot combustion mouth 15, main burning mouth 16 and burner holding cylinder 17.
Pilot combustion mouth 15 is configured on burner axis Ac, makes fuel diffusion combustion.The pilot combustion mouth 15, which has, to be drawn
Fire nozzle 18, pilot combustion mouth cylinder 19 and the cyclone that ignites (not shown).
Pilot burner 18 is formed as the Da extension in the axial direction centered on burner axis Ac.The pilot burner 18 is for example
There is the spray-hole 18a of fuel injection in side end downstream.
Pilot combustion mouth cylinder 19 has main part 21 and tapered portion 22.The periphery of the covering pilot burner 18 of main part 21.Cone
Shape portion 22 is configured at the downstream side of main part 21.It is gradually expanding that the tapered portion 22 is formed towards downstream side.
The cyclone (not shown) that ignites configures on axis direction Da the spray-hole 18a's than being formed with pilot burner 18
The position of position on the upstream side.The cyclone that ignites (not shown) makes compressed air (primary air) A come from upstream side flowing
It circles round by centre of gyration of burner axis Ac.Cyclone (not shown) ignite out of, pilot combustion mouth cylinder 19 main part 21
Circumferential surface extends to radially inner side.The above-mentioned cyclone that ignites (not shown) for example it is circumferentially spaced alternately formed it is multiple.
The compressed air A compressed by compressor 2 is out of, upstream side flows into pilot combustion mouth 15 pilot combustion mouth cylinder 19.Combustion
Material is sprayed from the spray-hole 18a of pilot burner 18.The fuel and the pressure that convolution ingredient is imparted by the cyclone that ignites (not shown)
Contracting air A together, sprays from pilot combustion mouth cylinder 19 towards combustion barrel 13, burning is diffused in combustion barrel 13.
Main burning mouth 16 is provided with multiple.Above-mentioned main burning mouth 16 is configured to surround the periphery of pilot combustion mouth 15.On
Stating main burning mouth 16 makes fuel pre-mixing combustion.Above-mentioned main burning mouth 16 is circumferentially spaced centered on burner axis Ac
Compartment of terrain configuration.More specifically, main burning mouth 16 equally spaced configures in the circumferential direction centered on burner axis Ac.
Main burning mouth 16 has main burner 23, main burning mouth cylinder 24 and main cyclone device 25.
Main burner 23 is extended parallel to burner axis Ac.Above-mentioned main burner 23 is for example sprayed in its outer peripheral surface with fuel
The spray-hole 23a penetrated.
The periphery of the covering main burner 23 of main burning mouth cylinder 24.In the main burning mouth cylinder 24 illustrated by Fig. 3, with burner
The part for being radially configured inside centered on axis Ac doubles as a part of pilot combustion mouth cylinder 19.
Main cyclone device 25 returns compressed air (primary air) A come from upstream side flowing with 23 centre of gyration of main burner
Rotation.Main cyclone device 25 extends from the inner peripheral surface of main burning mouth cylinder 24 towards main burner 23.Main cyclone device 25 is respectively arranged at setting
There is multiple main burning mouths 16.Main cyclone device 25 has been positioned apart from circumferentially spaced centered on main burner 23 more respectively
It is a.
Burner holding cylinder 17 keeps above-mentioned pilot combustion mouth 15 and main burning mouth 16.More specifically, burner is protected
It holds cylinder 17 and keeps pilot combustion mouth 15 and main burning mouth in such a way that multiple main burning mouths 16 surround the periphery of pilot combustion mouth 15
16。
The compressed air A compressed by compressor 2 is out of, upstream side flows into main burning mouth 16 main burning mouth cylinder 24.Fuel F
It is sprayed from the spray-hole 23a of main burner 23.Fuel F is mixed with the compressed air A for imparting convolution ingredient by main cyclone device 25.
Main cyclone device 25 can also assign convolution ingredient after spraying fuel F to compressed air A.It is mixed with above-mentioned fuel and compressed air
The pre-mixed gas of A is sprayed towards combustion barrel 13, and pre-mixing combustion is carried out in combustion barrel 13.
As shown in figure 4, fuel jetting device 14 has the work that the convolution direction based on main cyclone device 25 is opposite direction each other
The first burner 16A for main burner 16 and the second burner 16B as main burning mouth 16.In addition to convolution direction is each other
Other than opposite direction this point, above-mentioned first burner 16A and the second burner 16B are identical structure.In Fig. 4, omit
The diagram of pilot combustion mouth 15.The main burning mouth 16 used in this embodiment is only the combustion of the first burner 16A and second
Burner 16B both.
For first burner 16A of the first embodiment from 13 side of combustion barrel, convolution direction is left-handed.First reality
The second burner 16B of mode is applied from 13 side of combustion barrel, convolution direction is dextrorotation.The fuel of the first embodiment sprays
Device 14A is configured continuously in a circumferential there are five the first burner 16A.The fuel jetting device 14A of the first embodiment is circumferentially
Continuously there are three the second burner 16B for configuration.Fuel jetting device 14A shown in Fig. 4, which is shown, has eight main burning mouths 16
The case where, as long as but main burning mouth 16 quantity be it is multiple, such as or nine or more, seven or less.In Fig. 4
In, the position of eight main burning mouths 16 in circumferential direction is indicated with configuration number " 1 " to " 8 " respectively.
In fuel jetting device 14A, the first burner 16A and the second burner 16B are on circumferential complete cycle with aperiodic
Property configuration mode configuration.Here, " periodic configuration mode " refer to centered on burner axis Ac circumferentially around one
During week, the mode for the sequence that the first burner 16A and the second burner 16B are configured is only with the repetition of identical mode.Make
For an example of periodic situation, the feelings of the first burner 16A and the second circumferentially alternating configuration of burner 16B can be enumerated
Condition only configures the case where the first burner 16A, only configures the case where the second burner 16B etc..
That is, the configuration mode of the main burning mouth 16 in the fuel jetting device 14A of the first embodiment is with combustion
Circumferentially around the sequence that during one week, the first burner 16A and the second burner 16B are configured centered on burner axis Ac
Mode is not with the repetition of identical mode.
In fuel jetting device 14A, the first burner 16A and the second burner 16B are centered on burner axis Ac
Circumferential direction on asymmetrical configuration mode configuration.Asymmetrical configuration mode refers to not with so-called rotation pair in the circumferential for this
The the first burner 16A and the second burner 16B that is arranged in order claimed.In the explanation of the following embodiments and the accompanying drawings, as the first combustion
An example of the acyclic index of the configuration mode of burner 16A and the second burner 16B, has used heat liberation rate, heat release rate center of gravity and synthesis
Vector, but can also be using only either in heat liberation rate, heat release rate center of gravity and resultant vector.
In fuel jetting device 14A, the first burner 16A and the second burner 16B are with the entirety of multiple main burning mouths 16
Heat liberation rate, heat release rate the configuration mode that is deviated from the burner axis Ac as circumferential center of position of centre of gravity g (referring to Fig. 5)
Configuration.Main burning mouth 16 all in the circumferential direction centered on burner axis Ac be the first burner 16A in the case where,
In the case that all main burning mouths 16 are the second burner 16B in circumferential direction centered on burner axis Ac and the
One burner 16A and the second burner 16B in the circumferential direction centered on burner axis Ac in the case where being alternately arranged, whole
Heat liberation rate, heat release rate is balanced on week.Therefore, the position of centre of gravity g and burner axis Ac of heat liberation rate, heat release rate are substantially consistent.
In Fig. 5, " 8-1 ", " 1-2 ", " 2-3 ", " 3-4 ", " 4-5 ", " 5-6 ", " 6-7 " be respectively with master shown in Fig. 4
Corresponding position is numbered in the configuration of burner 16.If showing an example, " 8-1 " shows position set and " 8 " of main burning mouth 16
Between position.
There are three the second burner 16B of the fuel jetting device 14A of first embodiment is configured continuously in a circumferential.Fuel
There are five the first burner 16A of jetting device 14A is configured continuously in a circumferential.Therefore, as shown in figure 5, fuel jetting device 14A
Heat liberation rate, heat release rate generate deviation in the circumferential, deviated outward at position " 8-1 ".The deviation for thinking the heat liberation rate, heat release rate is by circumferential direction
Caused by the direction of the vortex of the boundary of upper adjacent the first burner 16A and the second burner 16B.The fuel jetting device
The position of centre of gravity g of the heat liberation rate, heat release rate of 14A is from burner axis Ac to the lateral offset of position " 8-1 ".Here, in Fig. 5, with combustion
(the case where aftermentioned example 0 in the case where the first burner 16A is provided on circumferential complete cycle centered on burner axis Ac
Under), heat liberation rate, heat release rate is " 1 " (indicated by the solid line in Fig. 5) on the complete cycle of the circumferential direction.In this case, the position of centre of gravity g of heat liberation rate, heat release rate
It is Chong Die with burner axis Ac.Centered on burner axis Ac radially, in the case where the vortex towards outside is strong,
Heat liberation rate, heat release rate is 1.5, and in the case where the vortex towards radially inner side is strong, heat liberation rate, heat release rate is 0.5 (being represented by dashed line in Fig. 5).
It is more than size of the first burner 16A and the second burner 16B of fuel jetting device 14A to become unit vector
The configuration mode of resultant vector configures.Here, unit vector refers to and the in the circumferential direction centered on burner axis Ac
The corresponding vector in direction for the radial flowing that the boundary of one burner 16A and the second burner 16B generate.Resultant vector refers to
Vector obtained from unit vector has been respectively synthesized in fuel jetting device 14A.
That is, becoming the configuration mode of the size of unit vector or more with the size of resultant vector configured with the first combustion
Burner 16A and the second burner 16B, the resultant vector be respectively synthesized in the circumferential direction centered on burner axis Ac
The first burner 16A and the second burner 16B the corresponding unit vector in direction of radial flowing that generates of boundary and obtain
The vector arrived.
For example, in the identical situation in convolution direction of adjacent main burning mouth 16, on the side of adjacent main burning mouth 16
Boundary plays a role in such a way that mutual swirling flow cancels each other out, therefore does not generate radial flowing substantially.In adjacent master
In the case that the convolution direction of burner 16 is opposite direction, on the boundary of adjacent main burning mouth 16, mutual swirling flow is in diameter
Upwardly toward identical direction.That is, generating on the boundary of the first burner 16A and the second burner 16B with burning
Centered on device axis Ac axially towards inwardly or the flowing in outside.If being indicated with the unit vector that size is " 1 " on the side
The radial flowing that boundary generates can then describe the unit vector UA as shown in Figure 4 towards radial outside and inside towards diameter
The unit vector UB of side.
As shown in fig. 6, in the fuel jetting device 14A of the first embodiment, if the position of burner axis Ac is set
It is (0,0) coordinate for origin, then unit vector UA is from (0,0) coordinate to (0,1) coordinate.Unit vector UB is from (- 0.71,0.71)
Coordinate is to (0,0) coordinate.Above-mentioned unit vector UA, UB and (hereinafter referred to as resultant vector SV) size is 1.8 or so.That is,
The size of the resultant vector SV of unit vector UA, UB is 1 or more.
In fuel jetting device 14A, such as multiple main burning mouths 16 that circumferentially spaced compartment of terrain is configured are in the circumferential
Segmentation becomes by adjacent multiple main burning mouths 16 are constituted and are made of the main burning mouth 16 of identical quantity in the circumferential each other
" group ".In this case, the first burning in the fuel jetting device 14A of first embodiment of the invention, at least one set
Configuration sequence (configuration relation) in the circumferential direction of mouth 16A and the second burner 16B is different from other groups.
As shown in figure 4, in the fuel jetting device 14A of the first embodiment, if by two adjacent in the circumferential masters
Burner 16 is used as one group, then can set four groups in the circumferential.In this case, the direction in circumferential direction is (such as right
Rotation) on when observing, can set and be made of the configuration of main burning mouth 16 number " 8 " and " 7 " the two second burner 16B
First group of G1 and by configuration number " 6 " and " 5 " a second burner 16B and a first burner 16A constitute second
Group G2.It is only made of the configuration of main burning mouth 16 number " 4 " and " 3 " the two first burner 16A further, it is possible to set
Third group G3 and the 4th group of G4 being only made of configuration number " 2 " and " 1 " the two first burner 16A.First group of G1 is opposite
Any group in second group of G2 to the 4th groups of G4, the configuration sequence of the first burner 16A and the second burner 16B in circumferential direction
It is different.The main burning mouth 16 that group is combined into group is not limited to above-mentioned configuration number.Each group is for example with the configuration of main burning mouth 16
Numbering " 7 " is circumferential starting point, and it is also same for being made of configuration number " 7 " and " 6 ", " 5 " and " 4 ", " 3 " and " 2 ", " 1 " and " 8 " etc.
Sample.
The fuel jetting device 14A of the first embodiment has eight main burning mouths 16, therefore can be by multiple main burnings
Mouth 16 in the circumferential equal part number be two or four.Although not shown, but four situation also with two situation phases
Together, the first burner 16A in each group is different from the configuration sequence of the second burner 16B.It should be noted that a group
It can be made of a main burning mouth 16.
According to first embodiment, with acyclic configuration on the circumferential complete cycle centered on burner axis Ac
Pattern configurations have the first burner 16A and the second burner 16B.
Fuel jetting device 14A can be formed different in the circumferential without using the different a variety of main burning mouths of shape as a result,
The flame of sample.
As a result, the working hour that the manufacture for being able to suppress main burning mouth 16 is spent increases, and inhibit combustion vibration
It generates.
In addition, not configuring the first burner 16A and the second burner 16B in rotationally symmetrical fashion, therefore it is able to suppress
Flame becomes the same in the circumferential.
Also, it is more from configuring with the position of centre of gravity g of the heat liberation rate, heat release rate index of the flame based on each main burning mouth 16 by making
The center of a main burning mouth 16, that is, burner axis Ac offset, presses down thus, it is possible to break the harmony of the flame in circumferential direction
It is made for the same flame.
In addition, the configuration mode of the first burner 16A and the second burner 16B in the circumferential is to make that resultant vector SV's is big
The configuration mode more than small size for unit vector UA, therefore the harmony of flame in circumferential direction can be broken and inhibit to become
The same flame.
Also, the multiple main burning mouths 16 for configuring circumferentially spaced compartment of terrain are divided by one or mutual in the circumferential
In the circumferential adjacent multiple main burning mouths 16 constitute and the group that is made of the main burning mouth 16 of identical quantity in the case where, at least
The configuration relation of the first burner 16A and the second burner 16B in one group are different from other groups.Therefore, it is able to suppress
It is upwardly formed the same flame week.
(second embodiment)
Second embodiment of the present invention is illustrated based on attached drawing.The second embodiment is relative to above-mentioned first
Embodiment changes the configuration mode of main burning mouth.Therefore, part same as the first embodiment is marked identical attached
Icon note is illustrated, and the repetitive description thereof will be omitted.
As shown in fig. 7, the fuel jetting device 14B of the second embodiment and the fuel of above-mentioned first embodiment spray
Device 14A similarly, has the first burner 16A and the second burner 16B as multiple main burning mouths 16.In addition to convolution direction that
This is other than opposite direction this point, above-mentioned first burner 16A and the second burner 16B is identical structure.
There are six the first burner 16A of the fuel jetting device 14B of the second embodiment is configured continuously in a circumferential.Combustion
There are two the second burner 16B of material jetting device 14B is configured continuously in a circumferential.Fuel jetting device 14B and Fig. 4 shown in Fig. 7
Similarly, show and have the case where eight main burning mouths 16, as long as but main burning mouth 16 quantity be it is multiple, such as
It can be nine or more, seven or less.
Fuel jetting device 14B is in the same manner as fuel jetting device 14A, with acyclic configuration mode on circumferential complete cycle
Configure the first burner 16A and the second burner 16B.
Fuel jetting device 14B also (is not with asymmetrical configuration mode in the circumferential direction centered on burner axis Ac
The configuration mode of rotational symmetry) configuration the first burner 16A and the second burner 16B.
Fuel jetting device 14B is in the same manner as the fuel jetting device 14A of first embodiment, the position of centre of gravity g of heat liberation rate, heat release rate
It is deviated from burner axis Ac.
In the same manner as the fuel jetting device 14A of first embodiment, unit vector UA is become with the size of resultant vector SV
The configuration mode more than size of (or UB) is configured with main burning mouth 16 (the first burner 16A, second of fuel jetting device 14B
Burner 16B), resultant vector SV is to be respectively synthesized and the first burner 16A and the second burner 16B in the circumferential
Vector obtained from corresponding unit vector UA, UB in direction for the radial flowing that boundary generates.
It, can be in week if regarding two adjacent in the circumferential main burning mouths 16 as one group in fuel jetting device 14B
Four groups of setting upwards.In this case, it when being observed on the direction (such as dextrorotation) in circumferential direction, can set by two
First group of G1 that two burner 16B are constituted and second group of G2 to the 4th groups of G4 being made of two the first burner 16A.The
First burner 16A and second burner 16B of one group of G1 relative to any group in second group of G2 to the 4th groups of G4, in circumferential direction
Configuration sequence it is different.The fuel jetting device 14B of the second embodiment also in the same manner as first embodiment, has eight
Main burning mouth 16.I.e. it is capable to by multiple main burning mouths 16 in the circumferential equal part number be two or four.
According to above-mentioned second embodiment, in the same manner as first embodiment, centered on burner axis Ac
The first burner 16A and the second burner 16B is configured with acyclic configuration mode on circumferential complete cycle.
Fuel jetting device 14B can be formed different in the circumferential without using the different a variety of main burning mouths of shape as a result,
The flame of sample.
As a result, the working hour that the manufacture for being able to suppress main burning mouth 16 is spent increases, and inhibit combustion vibration
It generates.
In addition, not configuring the first burner 16A and the second burner 16B in rotationally symmetrical fashion, therefore it is able to suppress
Flame becomes the same in the circumferential.
It also, is the position of centre of gravity g of index from configuring multiple main combustions using the heat liberation rate, heat release rate of the flame based on each main burning mouth 16
The center of burner 16, that is, burner axis Ac offset.Therefore, the harmony of the flame in circumferential direction can be broken and inhibit fire
Flame becomes the same in the circumferential.
In addition, the configuration mode of the first burner 16A and the second burner 16B in the circumferential is to make that resultant vector SV's is big
The configuration mode more than small size for unit vector UA (or UB).Therefore, the harmony of the flame in circumferential direction can be broken and
Flame is inhibited to become the same in the circumferential.
Also, the multiple main burning mouths 16 for configuring circumferentially spaced compartment of terrain are divided by one or mutual in the circumferential
In the circumferential adjacent multiple main burning mouths 16 constitute and the group that is made of the main burning mouth 16 of identical quantity in the case where, at least
The configuration relation of the first burner 16A and the second burner 16B in one group are different from other groups.Therefore, it is able to suppress fire
Flame is formed as the same in the circumferential.
(third embodiment)
Third embodiment of the present invention is illustrated based on attached drawing.The third embodiment and second embodiment are same
Sample, the configuration mode of main burning mouth is changed relative to above-mentioned first embodiment.Therefore, implement to above-mentioned first
The identical part of mode is labelled with identical appended drawing reference and is illustrated, and the repetitive description thereof will be omitted.
As shown in figure 8, the fuel jetting device of the fuel jetting device 14C of third embodiment and above-mentioned first embodiment
14A similarly, has the first burner 16A and the second burner 16B as multiple main burning mouths 16.Each other in addition to convolution direction
Other than opposite direction this point, above-mentioned first burner 16A and the second burner 16B are identical structure.
There are four the first burner 16A of the fuel jetting device 14C of third embodiment is configured continuously in a circumferential.The combustion
There are four the second burner 16B of material jetting device 14C is configured continuously in a circumferential.Fuel jetting device 14C and Fig. 4 shown in Fig. 8
Similarly, showing has the case where eight main burning mouths 16, as long as but main burning mouth 16 quantity be it is multiple, such as
It can be nine or more, seven or less.
In the same manner as fuel jetting device 14A, the first burner 16A and the second burner 16B of fuel jetting device 14C is in week
To complete cycle on acyclic configuration mode configuration.
Here, the configuration mode of the first burner 16A and the second burner 16B of third embodiment seem and seem
Periodic configuration mode.But periodic configuration mode mentioned here refers to, in the circumferential the first burner 16A with
In second burner 16B adjacent configuration mode, for example, in the circumferential the first burner 16A, the second burner 16B sequence,
Or any configuration mode in the sequence of the second burner 16B, the first burner 16A occurs during circumferentially around one week
Configuration mode more than twice.
The the first burner 16A and the second burner 16B of fuel jetting device 14B is in the week centered on burner axis Ac
Upwards with asymmetrical configuration mode (not being the configuration mode of rotational symmetry) configuration.
In the same manner as the fuel jetting device 14A of first embodiment, the position of centre of gravity g of the heat liberation rate, heat release rate of fuel jetting device 14B
It is deviated from burner axis Ac.
Although illustration omitted, in fuel jetting device 14C, will be fired with the first burner 16A and second in the circumferential
Corresponding unit vector UA, UB in direction for the radial flowing that the boundary of burner 16B generates synthesizes arrow obtained from being respectively synthesized
The size for measuring SV is the size of unit vector UA (or UB) or more.That is, the main burning mouth 16 (of fuel jetting device 14C
One burner 16A, the second burner 16B) with the configuration as resultant vector the SV more than size of unit vector UA (or UB)
Pattern configurations.It should be noted that the size of the resultant vector SV of the third embodiment is relative to unit vector UA (or UB)
For twice of size.
It, can be in week if regarding two adjacent in the circumferential main burning mouths 16 as one group in fuel jetting device 14B
Four groups of setting upwards.In this case, it when being observed on the direction (such as dextrorotation) in circumferential direction, can set by main burning
The allocation position of mouth 16 be " 1 " and " 8 " a first burner 16A and a second burner 16B composition first group of G1,
Second group of G2 being made of two the first burner 16A, it is made of a second burner 16B and a first burner 16A
Third group G3 and the 4th group of G4 being made of two the first burner 16A.First group of G1 is relative to second group of G2 to the 4th
Any group in group G4, the first burner 16A and the configuration sequence of the second burner 16B in circumferential direction are different.The third is real
The fuel jetting device 14C of mode is applied also in the same manner as first embodiment, there are eight main burning mouths 16.I.e. it is capable to
By multiple main burning mouths 16 in the circumferential equal part number be two or four.
According to above-mentioned third embodiment, in the same manner as first embodiment, centered on burner axis Ac
The first burner 16A and the second burner 16B is configured with acyclic configuration mode on circumferential complete cycle.
Fuel jetting device 14C can be formed different in the circumferential without using the different a variety of main burning mouths of shape as a result,
The flame of sample.
As a result, the working hour that the manufacture for being able to suppress main burning mouth 16 is spent increases, and inhibit combustion vibration
It generates.
In addition, not configuring the first burner 16A and the second burner 16B in rotationally symmetrical fashion, therefore it is able to suppress
Flame becomes the same in the circumferential.
Also, make with the position of centre of gravity g of the heat liberation rate, heat release rate index of the flame based on each main burning mouth 16 from configuring multiple masters
The offset of the center of burner 16, that is, burner axis Ac, therefore the harmony of flame in circumferential direction can be broken and inhibit fire
Flame becomes the same.
In addition, by the way that the configuration mode of the first burner 16A and the second burner 16B in the circumferential is set as resultant vector
For the size of SV as the configuration mode more than size of unit vector UA (or UB), thus, it is possible to break the equal of the flame in circumferential direction
Weighing apparatus property and inhibit flame to become the same.
Also, the multiple main burning mouths 16 for configuring circumferentially spaced compartment of terrain are divided by one or mutual in the circumferential
In the circumferential adjacent multiple main burning mouths 16 constitute and the group that is made of the main burning mouth 16 of identical quantity in the case where, at least
The configuration relation of the first burner 16A and the second burner 16B in one group are different from other groups.Therefore, it is able to suppress fire
Flame is formed as the same in the circumferential.
(the 4th embodiment)
Then, the 4th embodiment of the invention is illustrated based on attached drawing.4th embodiment is relative to above-mentioned
First embodiment change the configuration mode of main burning mouth.4th embodiment is different from the first embodiment place and is
The size of resultant vector is less than " 1 ".Therefore, identical appended drawing reference is marked to part identical with above-mentioned first embodiment
It is illustrated, and the repetitive description thereof will be omitted.
As shown in figure 9, the fuel jetting device 14D of the 4th embodiment and the fuel of above-mentioned first embodiment spray
Device 14A similarly, has the first burner 16A and the second burner 16B as multiple main burning mouths 16.In addition to convolution direction that
This is other than opposite direction this point, above-mentioned first burner 16A and the second burner 16B is identical structure.
The fuel jetting device 14D of 4th embodiment is configured with seven the first burner 16A continuously in a circumferential, and
Configured with a second burner 16B.That is, the only one in the multiple main burning mouths 16 configured in the circumferential is second
Burner 16B, other all first burner 16A.Fuel jetting device 14D shown in Fig. 9 shows tool in the same manner as Fig. 4
There is the case where eight main burning mouths 16.But as long as the quantity of main burning mouth 16 be it is multiple, such as or nine with
Above, seven or less.
In the same manner as fuel jetting device 14A, the first burner 16A and the second burner 16B of fuel jetting device 14D is in week
To complete cycle on acyclic configuration mode configuration.
Also, the first burner 16A and the second burner 16B of fuel jetting device 14D in being with burner axis Ac
With asymmetrical configuration mode (not being the configuration mode of rotational symmetry) configuration in the circumferential direction of the heart.
In addition, in the same manner as the fuel jetting device 14A of first embodiment, the center of gravity of the heat liberation rate, heat release rate of fuel jetting device 14D
Position g is deviated from burner axis Ac.
It, can if regarding two adjacent in the circumferential main burning mouths 16 as one group also, in fuel jetting device 14D
It is enough to set four groups in the circumferential.In this case, when being observed on the direction (such as dextrorotation) in circumferential direction, can set by
First group of G1 that one the second burner 16B and a first burner 16A are constituted (the configuration number " 8 " of main burning mouth 16 and
" 7 ") and be made of two the first burner 16A second group of G2 to the 4th groups of G4 (main burning mouth 16 configuration number " 6 "
And " 5 ", " 4 " and " 3 ", " 2 " and " 1 ").Moreover, first group of G1 is relative to any group in second group of G2 to the 4th groups of G4, it is circumferential
On the first burner 16A and the configuration sequence of the second burner 16B it is different.The fuel jetting device of 4th embodiment
14D also in the same manner as first embodiment, has eight main burning mouths 16.I.e. it is capable to which multiple main burning mouths 16 are existed
The number of equal part is two or four in circumferential direction.
According to the 4th above-mentioned embodiment, in the same manner as first embodiment, centered on burner axis Ac
The first burner 16A and the second burner 16B is configured with acyclic configuration mode on circumferential complete cycle.
Fuel jetting device 14D can be formed different in the circumferential without using the different a variety of main burning mouths of shape as a result,
The flame of sample.
As a result, the working hour that the manufacture for being able to suppress main burning mouth 16 is spent increases, and inhibit combustion vibration
It generates.
In addition, not configuring the first burner 16A and the second burner 16B in rotationally symmetrical fashion, therefore it is able to suppress
Flame becomes the same in the circumferential.
It also, is the position of centre of gravity g of index from configuring multiple main combustions using the heat liberation rate, heat release rate of the flame based on each main burning mouth 16
The center of burner 16, that is, burner axis Ac offset.Therefore, the harmony of the flame in circumferential direction can be broken and inhibit fire
Flame becomes the same.
Also, the multiple main burning mouths 16 for configuring circumferentially spaced compartment of terrain are divided by one or mutual in the circumferential
In the circumferential adjacent multiple main burning mouths 16 constitute and the group that is made of the main burning mouth 16 of identical quantity in the case where, at least
The configuration relation of the first burner 16A and the second burner 16B in one group are different from other groups.Therefore, it is able to suppress fire
Flame is formed as the same in the circumferential.
Embodiment
Then, the embodiment of the burner of the fuel jetting device with above-mentioned each embodiment is illustrated.
For example 1 shown in table below configuration the first burner 16A into example 22 and the second burner 16B
Configuration mode, finds out the size of center of gravity (the heat liberation rate, heat release rate center of gravity) and resultant vector of heat liberation rate, heat release rate respectively, and has found out combustion vibration
Size.In table below, the number with above-mentioned each embodiment of " 1 " to " 8 " documented by the top in each column
The position of main burning mouth 16 in circumferential direction is corresponding.In table below, " inversely circle round radical " documented by the leftmost side refers to one
The radical of the second burner 16B in a fuel jetting device.In addition, " heat liberation rate, heat release rate center of gravity " is indicated from burner axis Ac to heat release
The distance of rate center of gravity.When calculating heat liberation rate, heat release rate center of gravity, in the case where the vortex towards radial outside is strong, heat liberation rate, heat release rate 1.5,
Towards radially inner side vortex it is strong in the case where, heat liberation rate, heat release rate 0.5.
[table 1]
(embodiment)
In the table, main burning mouth 16 in the fuel jetting device 14A of above-mentioned first embodiment is configured to example
"6".Main burning mouth 16 in the fuel jetting device 14B of second embodiment is configured to example " 2 ".The combustion of third embodiment
That expects the main burning mouth 16 in jetting device 14C is configured to example " 13 ".Main combustion in the fuel jetting device 14D of 4th embodiment
Burner 16 is configured to example " 1 ".
In the table, the case where the case where being configured with the first burner 16A is indicated with " 0 ", is configured with the second burner 16B
It is indicated with " 1 ".
(comparative example)
Example " 0 ", example " 5 ", example " 20 ", example " 22 " in above-mentioned table is respectively on circumferential complete cycle with the period
Property configuration mode be configured with the first burner 16A and the second burner 16B.
(heat liberation rate, heat release rate center of gravity)
It is as the example " 0 " of comparative example, the value of the heat liberation rate, heat release rate center of gravity of example " 5 ", example " 20 ", example " 22 "
“0.0000”。
On the other hand, to whole examples other than comparative example, the value of heat liberation rate, heat release rate center of gravity is greater than " 0.0000 ".
(size of resultant vector)
In Figure 10, solid line indicates the value of heat liberation rate, heat release rate center of gravity.In Figure 10, dotted line indicates the size of resultant vector.Scheming
In 10, the left part of horizontal axis is example " 0 ", and right part is example " 22 ".That is, on transverse axis, example number gets over direction
Right side is bigger.In Figure 10, horizontally extending heavy line is the value of above-mentioned heat liberation rate, heat release rate center of gravity and the size of resultant vector
A reference value an example.
As shown in Figure 10, it is known that, the size (dotted line) of resultant vector has correlation with the value (solid line) of heat liberation rate, heat release rate center of gravity.On
The size of resultant vector and the value of heat liberation rate, heat release rate center of gravity are stated in example corresponding with the first, second, third above-mentioned embodiment
In " 2 ", " 6 ", " 13 ", become extra high numerical value.Although the numerical value lower than above-mentioned example " 2 ", " 6 ", " 13 ", with
In the case where the corresponding example of four embodiments " 1 ", the size of resultant vector and the value of heat liberation rate, heat release rate center of gravity are more sufficiently high than " 0 "
Value.
By simulate calculate demonstrate the value of the pressure oscillation as caused by combustion vibration, as a result example " 1 ", " 2 ", " 6 ",
In " 13 ", combustion vibration is confirmed respectively than tendency that example " 0 " reduces.
In above-mentioned example " 1 ", " 2 ", " 6 ", " 13 ", the equal right and wrong of configuration of the first burner 16A and the second burner 16B
Periodically, and not symmetrically, and then the value of respective heat liberation rate, heat release rate center of gravity and the size of resultant vector are greater than example " 0 "
The case where.Especially in example " 2 ", " 6 ", the reduction of combustion vibration is significant.
That is, confirming the aperiodicity and combustion in the configuration mode of the first burner 16A and the second burner 16B
There are correlations between the reduction of burning vibration.
The present invention is not limited to the structures of above-mentioned each embodiment, can be designed within the scope of its spirit
Change.
For example, being not limited to the configuration mode of first embodiment to the 4th embodiment.That is, be not limited to example " 1 ", " 2 ",
The configuration mode of " 6 ", " 13 ".As long as other example (configurations other than example " 0 ", example " 5 ", example " 20 ", example " 22 "
Mode), then the configuration mode being also possible to other than example " 1 ", " 2 ", " 6 ", " 13 ".
Industrial availability
The present invention can be applied to burner and gas turbine.In accordance with the invention it is possible to inhibit the manufacture institute of main burning mouth
The working hour of cost increases, and inhibits the generation of combustion vibration.
Description of symbols
1 gas turbine
2 compressors
3 burners
4 turbines
6 compressor drums
7 compressor cases
8 turbine rotors
9 turbine cases
10 gas turbine rotors
11 gas turbine shells
13 combustion barrels
14A, 14B, 14C, 14D fuel jetting device
15 pilot combustion mouths
16 main burning mouths
The first burner of 16A
The second burner of 16B
17 burner holding cylinder
18 pilot burners
The spray-hole of 18a fuel injection
19 pilot combustion mouth cylinders
21 main parts
22 tapered portion
23 main burners
The spray-hole of 23a fuel injection
24 main burning mouth cylinders
25 main cyclone devices
A compressed air (primary air)
Ac burner axis
Ar rotation axis
Da axis direction
F fuel
G position of centre of gravity
First group of G1
Second group of G2
G3 third group
The 4th group of G4
GEN generator
SV resultant vector
UA unit vector
UB unit vector
Claims (6)
1. a kind of burner, wherein
The burner is standby:
So that primary air is circled round and generates the first burner as main burning mouth of gaseous mixture；And
Primary air is set to generate the as main burning mouth of gaseous mixture to opposite with first burner direction convolution
Two burners,
The circumferentially spaced compartment of terrain of main burning mouth configured with multiple,
With acyclic configuration mode configured with first burner and second burning on the circumferential complete cycle
Mouth.
2. burner according to claim 1, wherein
First burner and second burner are in the circumferential with the configuration of asymmetrical configuration mode.
3. burner according to claim 1, wherein
First burner and second burner are with the position of centre of gravity of the whole heat liberation rate, heat release rate of multiple main burning mouths
It is configured from the configuration mode of the circumferential Centre position deviation.
4. burner according to claim 1, wherein
First burner and second burner are to be respectively synthesized the size of resultant vector obtained from unit vector
For configuration mode the configuration more than size of the unit vector, the unit vector is and first burning in the circumferential
Mouth vector corresponding with the radial direction of flowing that the boundary of second burner generates.
5. burner according to claim 1, wherein
Multiple main burning mouths that circumferentially spaced compartment of terrain is configured are divided into the circumferential by one or mutually in circumferential direction
In the case where upper adjacent multiple main burning mouths composition and the group being made of the main burning mouth of identical quantity,
The first burner and the configuration relation of the second burner at least one described group is different with described in other groups.
6. a kind of gas turbine, wherein
The gas turbine has burner described in any one of claims 1 to 5.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2017029640A JP6822868B2 (en) | 2017-02-21 | 2017-02-21 | Combustor and gas turbine |
| JP2017-029640 | 2017-02-21 | ||
| PCT/JP2018/006243 WO2018155496A1 (en) | 2017-02-21 | 2018-02-21 | Combustor and gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110300872A true CN110300872A (en) | 2019-10-01 |
| CN110300872B CN110300872B (en) | 2021-09-14 |
Family
ID=63254413
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201880012407.2A Active CN110300872B (en) | 2017-02-21 | 2018-02-21 | Combustor and gas turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20200056788A1 (en) |
| JP (1) | JP6822868B2 (en) |
| CN (1) | CN110300872B (en) |
| DE (1) | DE112018000929T5 (en) |
| WO (1) | WO2018155496A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112944396B (en) * | 2021-05-13 | 2021-07-09 | 中国人民解放军国防科技大学 | Method for measuring mixing efficiency of wall-injected gaseous fuel and supersonic incoming flow |
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|---|---|---|---|---|
| US1508718A (en) * | 1922-03-09 | 1924-09-16 | Ernest H Peabody | Apparatus for burning liquid fuel |
| JP2006258041A (en) * | 2005-03-18 | 2006-09-28 | Kawasaki Heavy Ind Ltd | Gas turbine combustor and its igniting method |
| US20080173019A1 (en) * | 2005-03-18 | 2008-07-24 | Kawasaki Jukogyo Kabushiki Kaisha | Gas Turbine Combustor and Ignition Method of Igniting Fuel Mixture in the Same |
| CN101818907A (en) * | 2009-01-30 | 2010-09-01 | 通用电气公司 | Be used for suppressing the system and method for turbine combustion instability |
| CN101858595A (en) * | 2009-04-03 | 2010-10-13 | 株式会社日立制作所 | Combustor and method for modifying the same |
| CN104566464A (en) * | 2013-10-25 | 2015-04-29 | 三菱日立电力系统株式会社 | Gas turbine combustor and gas turbine combustor control method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3872664A (en) * | 1973-10-15 | 1975-03-25 | United Aircraft Corp | Swirl combustor with vortex burning and mixing |
| JPS5124937A (en) * | 1974-08-27 | 1976-02-28 | Mitsubishi Heavy Ind Ltd | NENRYONEN SHOSOCHI |
| GB2319078B (en) * | 1996-11-08 | 1999-11-03 | Europ Gas Turbines Ltd | Combustor arrangement |
| EP2796789B1 (en) * | 2013-04-26 | 2017-03-01 | General Electric Technology GmbH | Can combustor for a can-annular combustor arrangement in a gas turbine |
-
2017
- 2017-02-21 JP JP2017029640A patent/JP6822868B2/en active Active
-
2018
- 2018-02-21 DE DE112018000929.7T patent/DE112018000929T5/en active Pending
- 2018-02-21 WO PCT/JP2018/006243 patent/WO2018155496A1/en active Application Filing
- 2018-02-21 CN CN201880012407.2A patent/CN110300872B/en active Active
- 2018-02-21 US US16/486,604 patent/US20200056788A1/en not_active Abandoned
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1508718A (en) * | 1922-03-09 | 1924-09-16 | Ernest H Peabody | Apparatus for burning liquid fuel |
| JP2006258041A (en) * | 2005-03-18 | 2006-09-28 | Kawasaki Heavy Ind Ltd | Gas turbine combustor and its igniting method |
| US20080173019A1 (en) * | 2005-03-18 | 2008-07-24 | Kawasaki Jukogyo Kabushiki Kaisha | Gas Turbine Combustor and Ignition Method of Igniting Fuel Mixture in the Same |
| CN101818907A (en) * | 2009-01-30 | 2010-09-01 | 通用电气公司 | Be used for suppressing the system and method for turbine combustion instability |
| CN101858595A (en) * | 2009-04-03 | 2010-10-13 | 株式会社日立制作所 | Combustor and method for modifying the same |
| JP2010256003A (en) * | 2009-04-03 | 2010-11-11 | Hitachi Ltd | Combustor and method for modifying combustor |
| CN104566464A (en) * | 2013-10-25 | 2015-04-29 | 三菱日立电力系统株式会社 | Gas turbine combustor and gas turbine combustor control method |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018155496A1 (en) | 2018-08-30 |
| JP2018136056A (en) | 2018-08-30 |
| JP6822868B2 (en) | 2021-01-27 |
| CN110300872B (en) | 2021-09-14 |
| US20200056788A1 (en) | 2020-02-20 |
| DE112018000929T5 (en) | 2019-10-31 |
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