CN106907741A - A kind of chamber structure - Google Patents
A kind of chamber structure Download PDFInfo
- Publication number
- CN106907741A CN106907741A CN201710084584.9A CN201710084584A CN106907741A CN 106907741 A CN106907741 A CN 106907741A CN 201710084584 A CN201710084584 A CN 201710084584A CN 106907741 A CN106907741 A CN 106907741A
- Authority
- CN
- China
- Prior art keywords
- oil
- fuel nozzle
- inner liner
- diffuser
- fuel
- 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.)
- Pending
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The present invention provides a kind of chamber structure, including combustion box (1) and burner inner liner (2), combustion box (1) outside is provided with oil-feed and connects mouth (4), diffuser (5) and fuel nozzle (6) are then provided with the combustion box (1) inner side, diffuser (5) one end connects mouth (4) and is connected with oil-feed, diffuser (5) other end is provided with the fuel nozzle (6) for being introduced into fuel oil in burner inner liner (2), oil-feed connects mouth (4), diffuser (5) and fuel nozzle (6) three are connected by being integrated in the internal fuel gallery (3) of combustion box (1), the jet stem (7) being arranged in parallel with burner inner liner (2) is internally provided with fuel nozzle (6).Chamber structure provided by the present invention, reduces number of parts, improves reliability, reduces the pressure loss, improves the uniformity of burner inner liner air inlet.
Description
Technical field
The invention belongs to gas turbine design field, more particularly to gas-turbine combustion chamber design field, and in particular to one
Plant chamber structure.
Background technology
Gas turbine combustors need worked under conditions of HTHP and kept its reliability, its main work(
Can be that the chemical energy of fuel is converted into heat energy.It is to combustion chamber and combustion chamber is often provided with the fuel nozzle 6 of more than 10
Fuel is provided, conventional solution is the pipe-line system 8 that complexity is set on combustion box 1 at present, and fuel nozzle 6 is assembled
On combustion box 1, as shown in Figure 1, the shortcoming of the method is：1) part is excessive, poor reliability；To meet each fuel oil
The fuel supply of nozzle 6, it is necessary first to which the oil feed line of respective numbers is set；To ensure the reliability of pipeline itself to adapt to
Engine complicated thermal environment and vibration environment, also need to optimize the cast of pipeline, and set sufficient amount of clip, branch
The auxiliary components such as frame, pad, locking plate, to ensure that pipeline will not be damaged；And the auxiliary component itself such as support, clip for introducing can
Equally it is difficult to ensure that by property.2) complicated pipeline causes airflow pressure losses big in engine runner；Fuel nozzle 6
And the pipe-line system 8 of complexity, in engine by-pass air duct, the high velocity air (more than 100 meter per seconds) of by-pass air duct impacts shape
During the obstruction of shape complexity, turbulent flow, flow velocity can be produced to significantly reduce, cause the larger pressure loss, acting ability to decline, start
Engine efficiency reduction.3) jet stem 7 causes the air inlet of burner inner liner 2 uneven before burner inner liner 2.Fuel nozzle 6 is in burner inner liner 2
Fuel feeding must set the structure of jet stem 7, and jet stem 7 is vertically arranged with burner inner liner 2, inevitably impacts on jet stem 7, makes
Into turbulent flow, the generation pressure loss, and the uniformity of air-flow is had influence on, be unfavorable for that fuel oil burns.
The content of the invention
Shortcoming it is an object of the invention to overcome prior art, there is provided one kind reduces number of parts, improves reliability, drop
Low pressure loss, improves the chamber structure of burner inner liner air inlet uniformity degree.
The purpose of the present invention is achieved through the following technical solutions：Including combustion box and burner inner liner, the combustion chamber machine
Casket outside is provided with oil-feed and connects mouth, and diffuser and fuel nozzle, the diffuser one are then provided with the inside of the combustion box
End connects mouth and is connected with oil-feed, and the diffuser other end then connects with fuel nozzle, while the fuel nozzle coordinates with burner inner liner install,
Fuel nozzle be internally provided with burner inner liner be arranged in parallel jet stem, for fuel oil to be introduced into burner inner liner, oil-feed connect mouth,
Diffuser and fuel nozzle three are connected by being integrated in the fuel gallery inside combustion box.
Preferably, the oil-feed connects unrounded number for 1~5.
Preferably, the fuel nozzle quantity is 5~30.
Preferably, the diffuser is provided with support plate, and the fuel nozzle is integrated on the support plate.
Preferably, the combustion box is casting, forges or 3D printing shaping.
A kind of beneficial effect of chamber structure provided by the present invention is, 1) the oil feed line system of complexity is eliminated
System, reduces the spare part quantity of combustion chamber, improves reliability；The obstruction in engine by-pass air duct is reduced simultaneously, is dropped
The low pressure loss.Because oil feed line is integrated into combustion box, it is no longer necessary to extra to set outdoor independently of burning
Complicated pipe-line system；Combustion box has stronger rigidity and intensity, it is no longer necessary to extra complementary part, subtracts significantly
Engine part quantity is lacked；Outdoor complicated pipe-line system of burning is cancelled simultaneously after, by-pass air duct becomes smooth, spaciousness, air-flow
By when be no longer influenced by extra resistance, pressure loss reduction improves engine efficiency.2) fuel oil flows in combustion box
It is dynamic, it is possible to decrease casing wall temperature, increase reliability.About 200 DEG C of fuel oil temperature, and then up to 400 DEG C of the temperature of combustion box A,
Fuel oil flows in combustion box can play cooling effect, and its material property is accordingly lifted after the reduction of casing temperature, casing
Reliability increases.3) before fuel nozzle bar no longer stands on burner inner liner, but it is parallel with burner inner liner, improve the equal of burner inner liner air inlet
Evenness.After fuel nozzle is integrated on combustion box, jet stem can directly stretch out from diffuser support plate, so as to parallel to entering
Enter the high velocity air of burner inner liner, it is not necessary to be separately provided jet stem, additionally increase flow perturbation.So can effectively reduce air-flow damage
Lose, improve air inlet uniformity degree.Whole combustion chamber is only made up of combustion box and the big component of burner inner liner two, and number of parts is significantly
Reduce, reliability is accordingly improved, surfaces externally and internally is smooth succinct, and flow losses are small, can effectively improve engine performance.
Brief description of the drawings
Fig. 1 is the structural representation of existing chamber structure；
Fig. 2 is the structural representation of chamber structure of the invention；
Fig. 3 is the sectional view of chamber structure of the invention；
Fig. 4 is the front view of chamber structure of the invention.
Reference：
1- combustion boxes, 2- burner inner liners, 3- fuel galleries, 4- oil-feeds connect mouth, 5- diffusers, 6- fuel nozzles, 7- sprays
Mouth bar, 8- pipe-line systems.
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
Chamber structure of the invention is described in further details below in conjunction with the accompanying drawings.
As shown in Figures 2 to 4, a kind of chamber structure, including combustion box 1 and burner inner liner 2, outside combustion box 1
Side is provided with oil-feed and connects mouth 4, and diffuser 5 and fuel nozzle 6 are then provided with the inner side of combustion box 1, the one end of diffuser 5 with enter
Oil connects mouth 4 and is connected, and the other end of diffuser 5 then connects with fuel nozzle 6, while the fuel nozzle 6 coordinates with burner inner liner 2 install,
The jet stem 7 being arranged in parallel with burner inner liner 2, for fuel oil to be introduced into burner inner liner 2, oil-feed are internally provided with fuel nozzle 6
Meet mouth 4, diffuser 5 and the three of fuel nozzle 6 and connected by being integrated in the fuel gallery 3 inside combustion box 1.Simultaneously
Combustion box 1 comprising the three is molded by the mode of casting, forging or 3D printing.Oil-feed in the present invention connects mouth 4
Can select to set 1~5, fuel nozzle 6 can select to set 5~30, then to connect mouth 4 excellent for oil-feed in the present embodiment
First select 1,6 prioritizing selection of fuel nozzle 20.
When chamber structure of the invention works, fuel oil connects mouth 4 and flows into fuel gallery 3 by oil-feed, via diffuser 5
Plate is distributed into 20 fuel nozzles 6, then finally penetrating burner inner liner 2 is burnt through the jet stem 7 in fuel nozzle 6.Fuel oil
Passage 3 is arranged in combustion box 1, it is no longer necessary to is set complicated pipe-line system 8 and the various auxiliary component of quantity, is increased
Having added the high-speed air (i.e. A in Fig. 2 to 4) of reliability, by-pass air duct can be flowed through with smooth, reduce the pressure loss, jet stem 7
Parallel to the air-flow (i.e. B in Fig. 2 to 3) for entering burner inner liner 2, the pressure loss is reduced, improve into burner inner liner interior air-flow
Uniformity, fuel oil temperature is relatively low (about 200 DEG C), and casing can be played preferably when flowing through combustion box 1 (about 400 DEG C)
Cooling effect, improves the casing strength of materials, increases reliability.
The above, specific embodiment only of the invention, but protection scope of the present invention is not limited thereto, and it is any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of the claims
It is accurate.
Claims (5)
1. a kind of chamber structure, including combustion box (1) and burner inner liner (2), it is characterised in that the combustion box
(1) outside is provided with oil-feed and connects mouth (4), and diffuser (5) and fuel nozzle (6) are then provided with the combustion box (1) inner side,
Described diffuser (5) one end connects mouth (4) and is connected with oil-feed, and diffuser (5) other end then connects with fuel nozzle (6), while should
Fuel nozzle (6) coordinates with burner inner liner (2) to be installed, and the spray being arranged in parallel with burner inner liner (2) is internally provided with fuel nozzle (6)
Mouth bar (7), for fuel oil to be introduced into burner inner liner (2), oil-feed meets mouth (4), diffuser (5) and fuel nozzle (6) three and leads to
The fuel gallery (3) being integrated in inside combustion box (1) is crossed to connect.
2. chamber structure according to claim 1, it is characterised in that the oil-feed connects mouth (4) quantity for 1~5.
3. chamber structure according to claim 1, it is characterised in that fuel nozzle (6) quantity is 5~30
It is individual.
4. chamber structure according to claim 1, it is characterised in that the diffuser (5) is provided with support plate, the combustion
Oil burner nozzle (6) is integrated on the support plate.
5. chamber structure according to claim 1, it is characterised in that the combustion box (1) be casting, forging or
3D printing is molded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710084584.9A CN106907741A (en) | 2017-02-16 | 2017-02-16 | A kind of chamber structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710084584.9A CN106907741A (en) | 2017-02-16 | 2017-02-16 | A kind of chamber structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106907741A true CN106907741A (en) | 2017-06-30 |
Family
ID=59209378
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710084584.9A Pending CN106907741A (en) | 2017-02-16 | 2017-02-16 | A kind of chamber structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106907741A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109632325A (en) * | 2018-12-17 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of main chamber flow allocation method |
| CN112065591A (en) * | 2020-09-11 | 2020-12-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Electromagnetic drive formula ignition for aeroengine |
| CN116557905A (en) * | 2023-05-06 | 2023-08-08 | 清华大学 | Annular diffuser and combustion chamber |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101650038A (en) * | 2009-09-02 | 2010-02-17 | 北京航空航天大学 | Integrated diffusion oriented combustion chamber |
| CN203615366U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Combustion chamber |
| CN203671656U (en) * | 2013-12-06 | 2014-06-25 | 中航商用航空发动机有限责任公司 | Aero-engine combustor |
| CN105042637A (en) * | 2015-07-09 | 2015-11-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber |
| CN105716114A (en) * | 2014-12-04 | 2016-06-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Detachable and replaceable rectangular diffuser |
-
2017
- 2017-02-16 CN CN201710084584.9A patent/CN106907741A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101650038A (en) * | 2009-09-02 | 2010-02-17 | 北京航空航天大学 | Integrated diffusion oriented combustion chamber |
| CN203671656U (en) * | 2013-12-06 | 2014-06-25 | 中航商用航空发动机有限责任公司 | Aero-engine combustor |
| CN203615366U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Combustion chamber |
| CN105716114A (en) * | 2014-12-04 | 2016-06-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Detachable and replaceable rectangular diffuser |
| CN105042637A (en) * | 2015-07-09 | 2015-11-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109632325A (en) * | 2018-12-17 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of main chamber flow allocation method |
| CN109632325B (en) * | 2018-12-17 | 2021-05-25 | 中国航发沈阳发动机研究所 | Main combustion chamber flow distribution method |
| CN112065591A (en) * | 2020-09-11 | 2020-12-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Electromagnetic drive formula ignition for aeroengine |
| CN116557905A (en) * | 2023-05-06 | 2023-08-08 | 清华大学 | Annular diffuser and combustion chamber |
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Application publication date: 20170630 |
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| RJ01 | Rejection of invention patent application after publication |