CN112555902A - Dual-fuel vector igniter - Google Patents
Dual-fuel vector igniter Download PDFInfo
- Publication number
- CN112555902A CN112555902A CN202011596507.XA CN202011596507A CN112555902A CN 112555902 A CN112555902 A CN 112555902A CN 202011596507 A CN202011596507 A CN 202011596507A CN 112555902 A CN112555902 A CN 112555902A
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- Prior art keywords
- fuel
- nozzle
- igniter
- cavity
- liquid
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Classifications
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23Q—IGNITION; EXTINGUISHING-DEVICES
- F23Q9/00—Pilot flame igniters
- F23Q9/08—Pilot flame igniters with interlock with main fuel supply
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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
- F23R3/36—Supply of different fuels
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
A dual-fuel vector igniter belongs to the field of gas turbines. The invention aims to solve the problems of single ignition fuel and ignition channel and fixed fire outlet direction in the prior art. When liquid fuel is used for ignition, liquid fuel is introduced from a transverse cavity in a liquid nozzle shell, after impurities are filtered by a filter element, the liquid fuel enters a vertical cavity along the inner wall of the vertical cavity, then enters a liquid fuel annular cavity from a liquid fuel inlet, enters a swirl groove from the liquid fuel annular cavity, and enters a liquid fuel nozzle from the swirl groove. It enables dual fuel ignition.
Description
Technical Field
The invention relates to a dual-fuel vector igniter ignited by a combustion chamber of a gas turbine, belonging to the field of gas turbines.
Background
With the development of industrial modernization and diversification of energy types, gas turbines are increasingly widely applied in the fields of ship propulsion, petrochemical industry, thermal power generation, oil and gas exploitation, aerospace, distributed energy and the like. The performance of the combustion chamber, which is one of three major components of the gas turbine, directly affects the overall performance of the unit. The ignition of the combustion chamber is an important part of the starting process of the gas turbines, and any gas turbine is equipped with a special ignition device by means of which a certain energy can be input into the combustion chamber to ignite the fuel and air mixture in the combustion chamber. In order to meet the demand for diversification of gas turbine fuel and high reliability of ignition, an igniter having excellent performance capable of arbitrarily igniting gas or liquid fuel is required.
Disclosure of Invention
The invention aims to solve the problems of single ignition fuel and ignition channel and fixed fire outlet direction in the prior art. A dual fuel vector igniter is now provided.
A dual fuel vector igniter, the igniter comprises an igniter housing 1, a sleeve 2, a vector flame tube 3, an ignition torch 4, a liquid nozzle housing 8, a pinch cock 11, a swirler 12, a liquid fuel nozzle 13, a gaseous fuel nozzle 14 and a filter element 15,
a vertical cavity and a horizontal cavity are arranged in the liquid nozzle shell 8, the horizontal cavity is communicated with the vertical cavity, a filter element 15 is arranged in the horizontal cavity,
a liquid fuel nozzle 13, a swirler 12 and a compression cock 11 are sequentially arranged in a vertical cavity, the liquid fuel nozzle 13 is arranged at the bottom in the vertical cavity, the liquid fuel nozzle 13 is a cylinder, the swirler 12 is arranged in the cylinder, a liquid fuel annular cavity 12-1 is formed between the swirler 12 and the liquid fuel nozzle 13, a plurality of liquid fuel inlets 13-1 are circumferentially arranged on the liquid fuel nozzle 13 corresponding to the liquid fuel annular cavity 12-1, the liquid fuel inlets 13-1 are communicated with the liquid fuel annular cavity 12-1, a swirl groove 12-2 is arranged on the swirler 12, an outlet of the liquid fuel annular cavity 12-1 is connected with an inlet of the swirl groove 12-2, and an outlet of the swirl groove 12-2 is connected with the liquid fuel nozzle 13-2; a pinch cock 11 is arranged at the top of the cyclone 12, the pinch cock 11 being used to fix the cyclone 12 in position in the centre axis of the vertical chamber;
the bottom of a liquid nozzle shell 8 is connected with an igniter shell 1 through a screw 6, a wedge-shaped cavity and an inclined cavity communicated with the wedge-shaped cavity are arranged in the igniter shell 1 by taking a central opening at the bottom of the liquid nozzle shell 8 as an axis, a sleeve 2 is inserted into the igniter shell 1, the sleeve 2 is communicated with the bottom of the wedge-shaped cavity, a vector flame tube 3 is inserted into the sleeve 2 from the bottom of the sleeve 2, the matching surface of the vector flame tube 3 and the sleeve 2 is spherical, and the vector flame tube 3 can deflect relative to the sleeve 2,
the gas fuel nozzle piece 14 is arranged in the igniter shell 1, a gas fuel annular cavity 14-1 is formed between the gas fuel nozzle piece 14 and the igniter shell 1, a plurality of gas fuel nozzles 14-2 are circumferentially arranged on the gas fuel nozzle piece 14, the gas fuel annular cavity 14-1 is communicated with the sleeve 2 through the gas fuel nozzles 14-2, the ignition electric nozzle 4 is inserted into the inclined cavity, and the nozzle of the ignition electric nozzle 4 faces the sleeve 2.
Preferably, the igniter further comprises a nut washer 9 and a nut 10,
the top of vertical chamber is followed to the pressure cock 11 and is inserted, and the top of pressure cock 11 is exposed outside liquid nozzle shell 8, through the internal thread of nut 10 and the external screw thread fit at pressure cock 11 top, will press cock 11 to fix on liquid nozzle shell 8, and the cover has nut gasket 9 on the pressure cock 11, seals through nut gasket 9 between nut 10 and the liquid nozzle shell 8.
Preferably, the igniter further comprises a mouthpiece gasket 5,
the cover has electric mouth gasket 5 on the electric mouth 4 of ignition, fixes electric mouth 4 of ignition on the inclined cavity through the external screw thread of electric mouth 4 of ignition and the internal thread in inclined cavity, and it is sealed through electric mouth gasket 5 between electric mouth 4 of ignition and the inclined cavity.
Preferably, the igniter further comprises a gas fuel through pipe 16,
the gas fuel through pipe 16 is connected with the ring cavity 14-1.
Preferably, liquid fuel inlet 13-1 has a diameter of 0.5mm to 1.5mm and liquid fuel nozzle 13-2 has a diameter of 0.5mm to 1 mm.
Preferably, gaseous fuel jets 14-2 are 1mm to 2mm in diameter and liquid fuel jets 13-2 are 15 to 45 degrees from the central axis of gaseous fuel jets 14-2.
The invention has the beneficial effects that:
this application both can realize using gaseous fuel ignition also can use liquid fuel ignition, when using liquid fuel ignition, liquid fuel lets in from the horizontal chamber in the liquid nozzle casing, after filter impurity through the filter core, along the inner wall entering vertical chamber in vertical chamber, and later get into liquid fuel ring chamber by the liquid fuel entry, get into the whirl groove by the liquid fuel ring chamber again, get into the liquid fuel spout by the whirl groove, because the space of liquid fuel spout and whirl groove is all very little, liquid fuel passes through liquid fuel spout and whirl groove, what come out from the liquid fuel spout is the oil mist after the atomizing, this oil mist and the air mixture back in the sleeve, can form flame after igniting by the ignition electric nozzle and be used for gas turbine to start the ignition. The vector flame tube can deflect relative to the sleeve, so that the purpose of changing the flame direction is achieved. The fire outlet direction is changeable.
When gas fuel is used for ignition, gas fuel is introduced into the gas fuel through pipe, enters the gas fuel nozzle through the gas fuel annular cavity, is sprayed into the sleeve through the gas fuel nozzle, is mixed with air in the sleeve, and can be ignited by the ignition electric nozzle to form flame for starting and igniting the gas turbine.
Therefore, the dual-fuel ignition device has the gas fuel channel and the liquid fuel channel, and can realize dual-fuel ignition. The ignition device can be mounted on a gas turbine and is used for meeting the requirement of starting and igniting a combustion chamber of the gas turbine; the starting ignition of the combustion chamber is not limited by the fuel type, and both liquid fuel and gas fuel can be used, so that the trouble that different fuel igniters need to be replaced according to different fuels in the combustion chamber is avoided; the fuel aperture of the liquid fuel nozzle and the gas fuel nozzle can be customized according to the flame energy of the igniter required by the combustion chamber; the vector flame tube of the igniter can carry out vector deflection according to the requirement of the combustion chamber to change the flame injection direction; the igniter has stable flame, large energy, adjustable spraying direction and high starting and igniting power.
Drawings
FIG. 1 is a schematic diagram of a dual fuel vector igniter configuration;
fig. 2 is a top view of fig. 1.
Fig. 3 is a partially enlarged view of the swirler of fig. 1.
Detailed Description
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 to 3, and the dual fuel vector igniter of the present embodiment includes an igniter housing 1, a sleeve 2, a vector flame tube 3, an ignition torch 4, a liquid nozzle housing 8, a pinch cock 11, a swirler 12, a liquid fuel nozzle member 13, a gas fuel nozzle member 14, and a filter element 15,
a vertical cavity and a horizontal cavity are arranged in the liquid nozzle shell 8, the horizontal cavity is communicated with the vertical cavity, a filter element 15 is arranged in the horizontal cavity,
a liquid fuel nozzle 13, a swirler 12 and a compression cock 11 are sequentially arranged in a vertical cavity, the liquid fuel nozzle 13 is arranged at the bottom in the vertical cavity, the liquid fuel nozzle 13 is a cylinder, the swirler 12 is arranged in the cylinder, a liquid fuel annular cavity 12-1 is formed between the swirler 12 and the liquid fuel nozzle 13, a plurality of liquid fuel inlets 13-1 are circumferentially arranged on the liquid fuel nozzle 13 corresponding to the liquid fuel annular cavity 12-1, the liquid fuel inlets 13-1 are communicated with the liquid fuel annular cavity 12-1, a swirl groove 12-2 is arranged on the swirler 12, an outlet of the liquid fuel annular cavity 12-1 is connected with an inlet of the swirl groove 12-2, and an outlet of the swirl groove 12-2 is connected with the liquid fuel nozzle 13-2; a pinch cock 11 is arranged at the top of the cyclone 12, the pinch cock 11 being used to fix the cyclone 12 in position in the centre axis of the vertical chamber;
the bottom of a liquid nozzle shell 8 is connected with an igniter shell 1 through a screw 6, a wedge-shaped cavity and an inclined cavity communicated with the wedge-shaped cavity are arranged in the igniter shell 1 by taking a central opening at the bottom of the liquid nozzle shell 8 as an axis, a sleeve 2 is inserted into the igniter shell 1, the sleeve 2 is communicated with the bottom of the wedge-shaped cavity, a vector flame tube 3 is inserted into the sleeve 2 from the bottom of the sleeve 2, the matching surface of the vector flame tube 3 and the sleeve 2 is spherical, and the vector flame tube 3 can deflect relative to the sleeve 2,
the gas fuel nozzle piece 14 is arranged in the igniter shell 1, a gas fuel annular cavity 14-1 is formed between the gas fuel nozzle piece 14 and the igniter shell 1, a plurality of gas fuel nozzles 14-2 are circumferentially arranged on the gas fuel nozzle piece 14, the gas fuel annular cavity 14-1 is communicated with the sleeve 2 through the gas fuel nozzles 14-2, the ignition electric nozzle 4 is inserted into the inclined cavity, and the nozzle of the ignition electric nozzle 4 faces the sleeve 2.
In this embodiment, the liquid fuel outlet is axially open. Thereby meeting the requirements of sufficient atomization and injection of the liquid fuel.
The vector flame tube is in spherical surface fit with the sleeve, and can deflect relative to the igniter body.
The igniter body of the application forms a channel and an air supply ring cavity of gas fuel, and the gas fuel sprayed out from the gas fuel nozzle 14 is mixed with air and can be ignited by the ignition electric nozzle 4 to form flame for starting and igniting the gas turbine.
The second embodiment is as follows: this embodiment is a dual fuel vector igniter as described for the first embodiment, the igniter further comprising a nut washer 9 and a nut 10,
the top of vertical chamber is followed to the pressure cock 11 and is inserted, and the top of pressure cock 11 is exposed outside liquid nozzle shell 8, through the internal thread of nut 10 and the external screw thread fit at pressure cock 11 top, will press cock 11 to fix on liquid nozzle shell 8, and the cover has nut gasket 9 on the pressure cock 11, seals through nut gasket 9 between nut 10 and the liquid nozzle shell 8.
The third concrete implementation mode: the present embodiment is a dual fuel vector igniter as described in the first embodiment, the igniter further comprising an electric nozzle gasket 5,
the cover has electric mouth gasket 5 on the electric mouth 4 of ignition, fixes electric mouth 4 of ignition on the inclined cavity through the external screw thread of electric mouth 4 of ignition and the internal thread in inclined cavity, and it is sealed through electric mouth gasket 5 between electric mouth 4 of ignition and the inclined cavity.
The fourth concrete implementation mode: the present embodiment is a dual fuel vector igniter as described in the first embodiment, the igniter further includes a gaseous fuel through pipe 16,
the gas fuel through pipe 16 is connected with the ring cavity 14-1.
The fifth concrete implementation mode: in the embodiment, the diameter of the liquid fuel inlet 13-1 is 0.5mm-1.5mm, and the diameter of the liquid fuel nozzle 13-2 is 0.5mm-1 mm.
The sixth specific implementation mode: the dual-fuel vector igniter is characterized in that the diameter of a gas fuel nozzle 14-2 is 1mm-2mm, and the central axis of a liquid fuel nozzle 13-2 and the central axis of the gas fuel nozzle 14-2 form an angle of 15-45 degrees.
Claims (6)
1. A dual fuel vector igniter is characterized by comprising an igniter shell (1), a sleeve (2), a vector flame tube (3), an ignition electric nozzle (4), a liquid nozzle shell (8), a pressing cock (11), a swirler (12), a liquid fuel nozzle piece (13), a gas fuel nozzle piece (14) and a filter element (15),
a vertical cavity and a transverse cavity are arranged in the liquid nozzle shell (8), the transverse cavity is communicated with the vertical cavity, a filter element (15) is arranged in the transverse cavity,
a liquid fuel nozzle piece (13), a swirler (12) and a compression cock (11) are sequentially arranged in a vertical cavity, the liquid fuel nozzle piece (13) is arranged at the bottom in the vertical cavity, the liquid fuel nozzle piece (13) is a cylinder, the swirler (12) is arranged in the cylinder, a liquid fuel annular cavity (12-1) is formed between the swirler (12) and the liquid fuel nozzle piece (13), a plurality of liquid fuel inlets (13-1) are circumferentially arranged on the liquid fuel nozzle piece (13) corresponding to the liquid fuel annular cavity (12-1), the plurality of liquid fuel inlets (13-1) are communicated with the liquid fuel annular cavity (12-1), a swirl groove (12-2) is arranged on the swirler (12), an outlet of the liquid fuel annular cavity (12-1) is connected with an inlet of the swirl groove (12-2), the outlet of the swirl groove (12-2) is connected with a liquid fuel nozzle (13-2); the compression cock (11) is arranged at the top of the cyclone (12), and the compression cock (11) is used for fixing the cyclone (12) at the position of the central axis of the vertical cavity;
the bottom of the liquid nozzle shell (8) is connected with the igniter shell (1) through a screw (6), a wedge-shaped cavity and an inclined cavity communicated with the wedge-shaped cavity are arranged in the igniter shell (1) by taking a central opening at the bottom of the liquid nozzle shell (8) as an axis, the sleeve (2) is inserted into the igniter shell (1), the sleeve (2) is communicated with the bottom of the wedge-shaped cavity, the vector flame tube (3) is inserted into the sleeve (2) from the bottom of the sleeve (2), the matching surface of the vector flame tube (3) and the sleeve (2) is spherical, and the vector flame tube (3) can deflect relative to the sleeve (2),
the gas fuel nozzle piece (14) is arranged in the igniter shell (1), a gas fuel annular cavity (14-1) is formed between the gas fuel nozzle piece (14) and the igniter shell (1), a plurality of gas fuel nozzles (14-2) are circumferentially arranged on the gas fuel nozzle piece (14), the gas fuel annular cavity (14-1) is communicated with the sleeve (2) through the gas fuel nozzles (14-2), the ignition electric nozzle (4) is inserted into the inclined cavity, and the nozzle of the ignition electric nozzle (4) faces the sleeve (2).
2. The dual fuel vector igniter as claimed in claim 1 wherein the igniter further comprises a nut washer (9) and a nut (10),
the top of vertical chamber is inserted from the top of compressing tightly cock (11), and the top of compressing tightly cock (11) exposes outside liquid nozzle casing (8), through the internal thread of nut (10) and the external screw thread cooperation at compressing tightly cock (11) top, will compress tightly cock (11) and fix on liquid nozzle casing (8), and the cover has nut gasket (9) on compressing tightly cock (11), seals through nut gasket (9) between nut (10) and liquid nozzle casing (8).
3. The dual fuel vector igniter as claimed in claim 1 wherein the igniter further comprises an electric mouth washer (5),
the cover has electric mouth gasket (5) on ignition electric mouth (4), fixes ignition electric mouth (4) on oblique chamber through the external screw thread of ignition electric mouth (4) and the internal thread in oblique chamber, seals through electric mouth gasket (5) between ignition electric mouth (4) and the oblique chamber.
4. The dual fuel vector igniter as claimed in claim 1 wherein the igniter further comprises a gaseous fuel through pipe (16),
the gas fuel through pipe (16) is connected with the ring cavity (14-1).
5. The dual fuel vector igniter as claimed in claim 1 wherein the liquid fuel inlet (13-1) has a diameter of 0.5mm to 1.5mm and the liquid fuel nozzle orifice (13-2) has a diameter of 0.5mm to 1 mm.
6. The dual fuel vector igniter as claimed in claim 5 wherein the gaseous fuel nozzle (14-2) has a diameter of 1mm to 2mm and the liquid fuel nozzle (13-2) is located at 15 to 45 ° from the central axis of the gaseous fuel nozzle (14-2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011596507.XA CN112555902A (en) | 2020-12-28 | 2020-12-28 | Dual-fuel vector igniter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011596507.XA CN112555902A (en) | 2020-12-28 | 2020-12-28 | Dual-fuel vector igniter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112555902A true CN112555902A (en) | 2021-03-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011596507.XA Pending CN112555902A (en) | 2020-12-28 | 2020-12-28 | Dual-fuel vector igniter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112555902A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116928698A (en) * | 2023-07-17 | 2023-10-24 | 中国航发燃气轮机有限公司 | Nozzle head, dual-fuel nozzle and combustion chamber |
-
2020
- 2020-12-28 CN CN202011596507.XA patent/CN112555902A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116928698A (en) * | 2023-07-17 | 2023-10-24 | 中国航发燃气轮机有限公司 | Nozzle head, dual-fuel nozzle and combustion chamber |
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