CN108779918A - For generate energy, particularly electric energy turbine, especially include storage heater the turbine with thermodynamic cycle combustion chamber - Google Patents
For generate energy, particularly electric energy turbine, especially include storage heater the turbine with thermodynamic cycle combustion chamber Download PDFInfo
- Publication number
- CN108779918A CN108779918A CN201780016328.4A CN201780016328A CN108779918A CN 108779918 A CN108779918 A CN 108779918A CN 201780016328 A CN201780016328 A CN 201780016328A CN 108779918 A CN108779918 A CN 108779918A
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- CN
- China
- Prior art keywords
- combustion chamber
- turbine
- hole
- diffuser
- row
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Spray-Type Burners (AREA)
Abstract
The present invention relates to for generate energy, be specifically electric energy turbine, especially with storage heater thermodynamic cycle turbine combustion chamber (18), shell (50) including accommodating flame tube (58), diffusion wall (60) of the flame tube with carrying flameholder (72), the flameholder includes perforation air diffuser (78) and mixing tube (88), the combustion chamber further include the injection apparatus (64) at least one fuel.According to the present invention, perforation diffuser (78) includes the hole (84 of circumferential at least two rows of (C1, C2)；84a,84b).
Description
The present invention relates to turbine, the especially thermodynamics with storage heater for generating energy, especially electric energy to follow
The combustion chamber of ring turbine.
The present invention relates more specifically to the miniature turbine with the storage heater for being produced electricl energy from liquid or gaseous fuel
Machine.
Usually, Microturbine is understood to be low-power turbine machine, usually less than 200kW.
It is such as better described in patent application WO-202/039,611, the turbine with storage heater generally includes band
Have at least one compression stage of at least one compressor, combustion chamber (or burner), at least one expansion turbine at least
Heat-exchanger rig (or storage heater) between one expansion stages, compressor and burner, the heat-exchange device allow to by compressor
The gas of compression is heated, and the gas with higher temperature is sent to burner, and the switch is by from turbine
Hot gas cross.
As described in aforementioned application, burner includes external shell, and hot compressed air is from being arranged in outside the shell
Storage heater and fire tube flow through the external shell, burn in the external shell.
The fire tube includes main region and dilution region, which receives a part for total heat compressed air stream, and
And burning occurs wherein, and occur in the dilution region burning waste gas from main region with from being arranged on pipe
The mixing of the hot compressed gas of dilution holes.
Main region further includes perforation diffuser, allows hot compressed air and from the (liquid being arranged in diffuser upstream
State or gaseous state) fuel of fuel injection system passes through.
Usually, relative to high power aircraft gas turbine machine or fixed gas turbine gener ator, the whirlpool with storage heater
Turbine has lower compression ratio (in the pressure of 3 to 5 bars of the order of magnitude) and the lower temperature at turbine inlet.
One of consequence of these operation characteristics is that whole abundant intensity (degree of enrichment) in a combustion chamber is generally less than 0.20,
That is, following below the fuel ignitability limit.
In addition, there is fuel prevapourising in the case of liquid fuel.
Usually, the combustion mode for allowing for low emission is lean premixed combustion.
However, this incendiary type led to the problem of in terms of flame holding it is great.These problems are by the dynamic of storage heater
It aggravates, storage heater improves the air themperature at burner by increasing the risk of instability of flame.
In addition, design cost also represents a kind of obstacle.In fact, this kind of combustion chamber features are between flame and wall by force
Strong interaction, this requirement select expensive material and the cooling system for burner wall, the combustion in large volume
Burner wall generally comprises multiple holes, it is intended that generates the mattress between flame and wall.The cooling system is related in manufacturing process side
The significant fringe cost in face and implementation complexity.
All these disadvantages make it difficult to realize completely burned and meet nitrogen oxides (NOx), carbon monoxide (CO), unburned
Low emission requirement in terms of hydrocarbon object (HC) and particle (PM).
In order to improve above-mentioned turbine, applicant has been presented for a kind of combustion chamber of the innovation for turbine, such as special
It is preferably described in profit application FR-15/59,314.
The combustion chamber includes accommodating flame tube, flameholder, burning gases circulation canal, mixing tube and fuel injection dress
The shell set, the flame tube band be useful for hot compressed air by perforation diffuser.
Applicant still further improves the combustion chamber of above-mentioned patent application, to realize that the more of burning pollutant subtract
Less, there is no soot particulates, combustion noise to reduce and at turbine inlet in exhaust gas in the case of standard assay techniques
Temperature gradient reduces.
Invention content
Present invention is accordingly directed to a kind of for generating the turbine of energy, especially electric energy, especially with storage heater
The combustion chamber of thermodynamic cycle turbine, the combustion chamber include the shell for accommodating the flame tube with diffusion wall, the diffusion wall packet
The flameholder of perforation air diffuser and mixing tube is included, the combustion chamber further includes the injection dress at least one fuel
It sets, is characterized in that, which includes circumferential at least two rows of hole.
Diffuser may include for fuel by hole, and the circumferential row of hole may be configured as it is concentric with the hole.
Diffuser may include a round hole, opening of the opening less than another round hole.
Diffuser may include that a round hole, the number in the round hole are more than the number in another round hole.
Diffuser may include the hole in closed curve shape.
Diffuser may include that hole, the angle spacing between two adjacent holes of one row are the two circular cavities of another row
Between angle spacing multiple or approximate number.
Diffuser of perforating can carry mixing tube by arm.
The present invention also relates to a kind of for generating the turbine of energy, especially electric energy, especially with the heat of storage heater
Kinetic loop turbine includes at least one compression stage at least one gas compressor, heat exchanger, by least one
A case is supplied with the combustion chamber of fuel, at least one expansion at least one expansion turbine by axis connection to compressor
Grade and energy producing unit, are characterized in that, which includes combustion chamber as defined above.
Other features and advantages of the present invention will by way of non-limiting example provide from reading with reference to attached drawing following
It is apparent from description, in attached drawing：
- Fig. 1 is shown with combustion chamber according to the present invention, the turbine for generating energy, especially electric energy
Schematic diagram,
- Fig. 2 is the axial sectional view for showing combustion chamber according to the present invention,
- Fig. 3 is the stereogram of the element of combustion chamber according to the present invention, and
- Fig. 4 is the element of combustion chamber shown in Fig. 3 along the side view of arrow A.
In Fig. 1, shown turbine is specifically micro-turbine 10, by least one operating fuel, such as diesel oil
The fuel gas of the liquid fuel of fuel type or such as natural gas.
The turbine include at least one compression stage 12 of at least one gas compressor 14, heat exchanger 16 (or
Storage heater), by least one case 20 supply the combustion chamber 18 (or burner) of fuel, at least one expansion stages 22, the expansion stages
22 include at least one expansion turbine 24 that compressor is connected to by axis 26.The turbine also includes that energy (being electric energy herein) produces
Generating apparatus, the energy producing unit include generator 28, are advantageously disposed on the axis 26 between compressor and turbine.
Certainly, the generator is alternatively by axis connection to expansion turbine or compressor, but the axis be not by turbine with
That root axis of compressor connection.
Compressor 14 includes oxygen-containing fresh air inlet 30 and leads to the compression of the compressed air inlet 34 of exchanger 16
Air outlet slit 32, here, extraneous air is generally under environment temperature.Burning is led in the hot compressed air outlet 36 of exchanger 16
The hot compressed air air inlet 38 of device 18.The overfire air outlet 40 of burner is connected to the entrance 42 of turbine, which goes out
Mouth 44 is connected to another exchanger entrance 46.Exchanger 16 also includes cooled gas vent 48, and gas is sent to any row
It puts and processing unit, such as chimney (not shown).
With reference to Fig. 2, burner 18 includes the external shell 50 for being cylindrical herein, and the external shell is at one end
It is closed, and is closed by the wall 54 with opening 56 at its other end, the diameter which has by injector holder wall 52
Than the diameter smaller of shell 50.The burner further include also be herein generally cylindrical in shape flame tube 58, the flame tube is same
It accommodates to axis in the housing, has than shell smaller but diameter identical with the diameter of the opening of annular wall 54 56.
The pipe include by end that is opposite with injector holder wall 52 and being closed away from the diffusion wall of one section distance 60 and
Open end 62, the open end extend through annular wall, at the same hermetically with the interior diameter associated of the annular wall, to
Form the outlet 40 of the burner.
The shell carries hot compressed air air inlet 38 on its circumference and close to annular wall 54, which is used for will
The air is fed to the space being arranged between shell and flame tube, and is fed to and is arranged in injector holder wall and diffusion
Space between wall.
As being better shown in fig. 2, injector holder wall includes plate 64, the spray for spraying at least one fuel
Injection device 66 is installed across the plate, and the injection apparatus is herein in the form of the injector coaxial with flame tube.The plate is turned by air
It is surrounded to (deflection) wall 68, which is semicircular herein, and concave surface is directed toward flame tube and is connected to the circumference of shell.
Flame tube includes the circumferential radial diffusion hole 70 respectively arranged, and is positioned as away from 60 a distance of diffusion wall and close
The annular wall of shell, while it is advantageously relatively uniformly distributed with air inlet 38.
Flame tube also includes flameholder 72, by being accommodated in the hole 74 being arranged in the diffusion wall 60
Setting is on diffusion wall 60 and on the inside of pipe.
Burner also include for fuel mixture igniter 76 for example, which can be used for spark point
The spark plug of the type of fiery formula internal combustion engine, heater plug (glow plug), ignitor etc..
Referring now additionally to Fig. 3 and Fig. 4, the example embodiment of flameholder 72 is shown.
The stabilizer includes the perforation air diffuser 78 in the form of flat circular bottom plate 80, it is expected that being contained in
In the hole 74 of diffusion wall 60.
The bottom plate includes central shaft string holes 82 and multiple holes 84, and the hole 82 is for keeping the fuel from injector 64 logical
It crosses, and multiple hole 84 extends through the thickness of the bottom plate with axial distance identical with (brill) hole.
As from it can more preferably see in these figures, hole 84 is distributed in multiple circumferential rows concentric with hole 82.
Example shown in the drawings shows that these holes are uniformly circumferentially distributed with two circumferential C1 and C2 that arrange.
Row's C1 holes in these rows, the outer edge closer to bottom plate are referred to as external row, including hole 84a,
The opening smaller of the hole 84b of another row C2 holes of aperture efficiency.
More precisely, hole has circular shape, and the diameter D1 that the hole 84a of external row has is than another row C2
The diameter D2 smallers of the hole 84b of hole.
The hole 84a advantageously numbers of outside row C1 are more than the number of the hole of internal row C2.In the example shown, hole
Hole 84a is twice of the numbers of hole of internal row.
Certainly, the shape of hole 84a, 84b is not limited to circle as shown in the figure, can be have closed curve any
Other shapes, such as square, oval, trapezoidal, triangle etc..
Similar, the circumferential angle spacing between two adjacent holes can be constant or variable in entire row.
Finally, the angle spacing between two adjacent holes of a row can be the angle between the two circular cavities of another row
Spend the multiple or approximate number of spacing.
Therefore, outside is arranged, the angle spacing α between two adjacent hole 84a of outside row is the two of internal row
The half of angle beta between a adjacent hole.
If referring now to Fig. 3, bottom plate 80 is in axial direction and opposite with the wall by 86 institutes of axial arm (holding),
This, three arms are set as being in 120 °, and carry mixing tube 88 in their end, which has outer straight
Interior diameter smaller of the diameter than flame tube 58.
Mixing tube 88 can be also connected to flame tube 58, without being attached to bottom plate by radial arm.
In operation, fuel (be in a liquid state form herein) sprays to perforation plate 80 by injector 64, to flow through center
Hole 82.Hot compressed air from air inlet 38 enters the space 90 between each wall, then which is turned to by turn-around wall 68.It should
Air then flows through the hole 84a and 84b of bottom plate, and it is sent to mixing tube 88, and liquid fuel occurs in the mixing tube
Evaporation, followed by burn.
The layout in each round hole promotes the recycling around flame holder, and provides relatively high air flowing speed
Degree.
In addition, the position in the round hole flushed with flame holder pipe allows circular flow to increase.
Therefore, by promoting recycling and with enough air velocitys：
The stabilization in flame holder Flame is avoided, diffusion type jet flame type structure can be caused,
Promote to evaporate and be more generally recycled for the mixed burning waste gas of promotion, and fuel droplet reaches flame
Front evaporator,
Realize the burning of opposite premix, that is, there is no rich region, and therefore there is low stain object to generate,
Combustion chamber can be run in the case where harmonic(-)mean is enriched with angle value, such as 0.35 in limit of stability.
Claims (8)
1. it is a kind of for generate energy, be specifically electric energy turbine, the thermodynamic cycle turbine especially with storage heater
Combustion chamber (18), the combustion chamber include accommodate flame tube (58) shell (50), the flame tube carry diffusion wall (60),
It carries flameholder (72), and the flameholder includes perforation air diffuser (78) and mixing tube (88), the combustion
It further includes injection apparatus (64) at least one fuel to burn room, which is characterized in that perforation diffuser (78) include it is circumferential extremely
The hole (84 of few two rows (C1, C2)；84a,84b).
2. combustion chamber as described in claim 1, which is characterized in that the diffuser include for fuel by hole (82),
And the circumferential row (C1, C2) of described hole is set as concentric with the hole.
3. combustion chamber as claimed in claim 1 or 2, which is characterized in that the diffuser includes the described hole of a row (C1)
(84a), opening (D1) are less than the opening (D2) of the described hole (84b) of another row (C2).
4. combustion chamber as described in any one of the preceding claims, which is characterized in that the diffuser includes a row's (C1)
Described hole (84a), quantity are more than the quantity of the described hole (84b) of another row.
5. combustion chamber as described in any one of preceding claims, which is characterized in that the diffuser includes bent in being closed
The described hole (84 of the form of line；84a,84b).
6. combustion chamber as described in any one of preceding claims, which is characterized in that the diffuser include hole (84a,
8b), the angle spacing (α, β) between two adjacent described holes (84a) of one row is two described holes of another row
The multiple or approximate number of angle spacing (β, α) between (84b).
7. combustion chamber as described in any one of preceding claims, which is characterized in that the perforation diffuser (78) by
Arm (86) carries mixing tube (88).
8. a kind of turbine, thermodynamic cycle turbine especially with storage heater for generating energy, especially electric energy
Machine, including carry at least one compression stage (12) of at least one gas compressor (14), heat exchanger (16), by least one
Case (20) is supplied with the combustion chamber (18) of fuel, at least one expansion turbine for being connected to the compressor by axis (26)
(24) at least one expansion stages (22) and energy producing unit (28), which is characterized in that the turbine includes such as aforementioned power
Combustion chamber (18) described in any one of profit requirement.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1652294A FR3049044B1 (en) | 2016-03-18 | 2016-03-18 | COMBUSTION CHAMBER OF A TURBINE, IN PARTICULAR OF A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, PARTICULARLY ELECTRICAL ENERGY. |
| FR1652294 | 2016-03-18 | ||
| PCT/EP2017/054167 WO2017157631A1 (en) | 2016-03-18 | 2017-02-23 | Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108779918A true CN108779918A (en) | 2018-11-09 |
| CN108779918B CN108779918B (en) | 2020-10-30 |
Family
ID=55953278
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780016328.4A Active CN108779918B (en) | 2016-03-18 | 2017-02-23 | Turbine for generating energy and combustion chamber thereof |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP3430316B1 (en) |
| CN (1) | CN108779918B (en) |
| FR (1) | FR3049044B1 (en) |
| WO (1) | WO2017157631A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3084450B1 (en) | 2018-07-30 | 2020-07-31 | Ifp Energies Now | COMBUSTION CHAMBER INCLUDING A PASSAGE SECTION OF A MODIFIED FLAME TUBE IN PARTICULAR FOR A TURBINE INTENDED FOR ENERGY PRODUCTION, ESPECIALLY ELECTRICAL ENERGY |
| FR3084447B1 (en) | 2018-07-30 | 2020-07-31 | Ifp Energies Now | COMBUSTION CHAMBER FOR A GAS TURBINE INTENDED FOR ENERGY PRODUCTION, ESPECIALLY ELECTRICAL ENERGY, INCLUDING ASYMMETRICAL DILUTION HOLES IN A FLAME TUBE. |
| FR3088969B1 (en) | 2018-11-27 | 2021-02-19 | Ifp Energies Now | Fuel injector with cooling means |
| FR3119868B1 (en) | 2021-02-15 | 2023-01-13 | Ifp Energies Now | Combustion system with a tubular combustion chamber and an annular heat exchanger |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB624779A (en) * | 1946-01-09 | 1949-06-16 | Bendix Aviat Corp | An improved burner for gaseous, liquid or powdered solid fuel |
| US2517015A (en) * | 1945-05-16 | 1950-08-01 | Bendix Aviat Corp | Combustion chamber with shielded fuel nozzle |
| US3754393A (en) * | 1970-12-05 | 1973-08-28 | Nissan Motor | Gas turbine engine combustor |
| US20040018459A1 (en) * | 2000-12-22 | 2004-01-29 | Thomas Ruck | Burner with high flame stability |
| CN1601181A (en) * | 2003-09-22 | 2005-03-30 | 通用电气公司 | Method and apparatus for reducing gas turbine engine emissions |
| US20090031728A1 (en) * | 2007-04-26 | 2009-02-05 | Keisuke Miura | Combustor and a fuel supply method for the combustor |
| WO2012039611A1 (en) * | 2010-09-21 | 2012-03-29 | Micro Turbine Technology Bv | Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2621477A (en) * | 1948-06-03 | 1952-12-16 | Power Jets Res & Dev Ltd | Combustion apparatus having valve controlled passages for preheating the fuel-air mixture |
| DE1627878A1 (en) | 1967-03-14 | 1970-08-06 | Schloemann Ag | Device to compensate for the spring deflection on machines, in particular on forging presses or the like. |
| DE2020416A1 (en) * | 1970-04-27 | 1971-11-11 | Motoren Turbinen Union | Combustion chamber for gas turbine engines |
-
2016
- 2016-03-18 FR FR1652294A patent/FR3049044B1/en active Active
-
2017
- 2017-02-23 CN CN201780016328.4A patent/CN108779918B/en active Active
- 2017-02-23 WO PCT/EP2017/054167 patent/WO2017157631A1/en active Application Filing
- 2017-02-23 EP EP17705924.3A patent/EP3430316B1/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2517015A (en) * | 1945-05-16 | 1950-08-01 | Bendix Aviat Corp | Combustion chamber with shielded fuel nozzle |
| GB624779A (en) * | 1946-01-09 | 1949-06-16 | Bendix Aviat Corp | An improved burner for gaseous, liquid or powdered solid fuel |
| US3754393A (en) * | 1970-12-05 | 1973-08-28 | Nissan Motor | Gas turbine engine combustor |
| US20040018459A1 (en) * | 2000-12-22 | 2004-01-29 | Thomas Ruck | Burner with high flame stability |
| CN1601181A (en) * | 2003-09-22 | 2005-03-30 | 通用电气公司 | Method and apparatus for reducing gas turbine engine emissions |
| US20090031728A1 (en) * | 2007-04-26 | 2009-02-05 | Keisuke Miura | Combustor and a fuel supply method for the combustor |
| WO2012039611A1 (en) * | 2010-09-21 | 2012-03-29 | Micro Turbine Technology Bv | Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2017157631A1 (en) | 2017-09-21 |
| FR3049044B1 (en) | 2019-12-20 |
| EP3430316B1 (en) | 2020-10-21 |
| FR3049044A1 (en) | 2017-09-22 |
| EP3430316A1 (en) | 2019-01-23 |
| CN108779918B (en) | 2020-10-30 |
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