CN202545021U - Fuel oil spraying device of combustion gas turbine - Google Patents
Fuel oil spraying device of combustion gas turbine Download PDFInfo
- Publication number
- CN202545021U CN202545021U CN 201120522998 CN201120522998U CN202545021U CN 202545021 U CN202545021 U CN 202545021U CN 201120522998 CN201120522998 CN 201120522998 CN 201120522998 U CN201120522998 U CN 201120522998U CN 202545021 U CN202545021 U CN 202545021U
- Authority
- CN
- China
- Prior art keywords
- oil
- gas turbine
- oil spraying
- fuel oil
- fuel injection
- 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.)
- Expired - Lifetime
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- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The utility model relates to a fuel oil spraying device of a combustion gas turbine. The fuel oil spraying device comprises a turbine rotor, an oil supply device and an oil flinger, wherein the oil flinger is in an annular shape containing an inner cavity and is fixedly arranged on the turbine rotor, the outer diameter part is provided with 6 to 10 radial oil spraying openings which are in uniform distribution and are communicated with the inner cavity, the diameter of each oil spraying opening is 0.6 to 1mm, and oil supply holes are arranged on the oil supply device and extend into the inner cavity of the oil flinger. The whole device omits a spray nozzle structure, the uniform and efficient fuel oil spraying effect is realized in the smaller annular space, and the fuel oil spraying device has the advantages that the structure is simple and compact, the assembly requirement is low, and the like.
Description
Technical field
The utility model relates to a kind of gas turbine fuel injection equipment.
Background technique
Existing microminiature gas turbine adopts centrifugal pressure nozzle to come fuel feeding, and such nozzle operation is stable, and it is less influenced by environmental change, is widely used.But such nozzle must be arranged on the outside of combustion machine, if the structure of firing chamber be an annular, for guaranteeing the uniformity of firing chamber interior flow field, just need place a plurality of nozzles along circumference, makes the complex structure of gas-turbine combustion chamber, the matching requirements height.And the structure of microminiature gas turbine is all compact, is unfavorable for arranging a plurality of nozzles.
Summary of the invention
The purpose of the utility model provides a kind of compact structure, matching requirements are low, is applicable to the gas turbine fuel injection equipment of small gas turbine.
The technological scheme of the utility model is; Device comprises turbine rotor, oil supplying device and disc; Described disc is the annular that includes inner chamber, is fixedly mounted on the turbine rotor, and outer radius is provided with 6～10 radially jets that are uniformly distributed with that communicate with inner chamber; The diameter of described jet is 0.6～1mm, and described oil supplying device is provided with oil supply hole and extend in the inner chamber of disc.Oil supply hole axis and turbine rotor on the described oil supplying device radially are 50～70 °, are preferably 60 °, and diameter is 0.6～0.8mm, is preferably 0.7mm.Described jet is preferably 8, and diameter is 0.8mm.
The utility model adopts oil supplying device and disc nozzle to form, and is simple in structure.Get rid of into the firing chamber through radially having an equally distributed nozzle opening, under centrifugal action, this port fuel atomizing effect is good, can realize the uniformity of this firing chamber interior flow field, makes oil inflame abundant; Through two oil supply holes that diameter is very little on the oil supplying device, the fuel oil with certain pressure is directly sprayed through aperture, get in the annular groove of top of chamber in the disc, need not sealing; The sense of rotation that oil supply hole axis on the oil supplying device and turbine rotor axis are 60 ° and injection direction and turbine rotor is identical, can prevent effectively that lubricating oil from splashing and outwards throw away from jet more easily.Whole device has been cancelled nozzle arrangements, has realized the fuel injection effect of uniform high-efficiency having advantages such as simple and compact for structure, that matching requirements are low at less annular space.
Description of drawings
Fig. 1 is the structural representation of the utility model;
Fig. 2 is the nozzle opening position view of the utility model.
Embodiment
As shown in the figure; This device comprises turbine rotor 3, oil supplying device 4 and disc 2; Described disc 2 is fixedly mounted on the turbine rotor 3 for including the annular of inner chamber, and outer radius is provided with 8 radially jets 1 that are uniformly distributed with that communicate with inner chamber; The diameter of described jet 1 is 0.8mm, and described oil supplying device 4 is that two and its are provided with oil supply hole 6 and extend in the inner chamber of disc 2.The axis of the oil supply hole 6 on the described oil supplying device 4 and turbine rotor radial line are 60 °, and injection direction is identical with the sense of rotation of turbine rotor, and diameter is 0.7mm.
Claims (7)
1. gas turbine fuel injection equipment; It is characterized in that; Described device comprises turbine rotor (3), oil supplying device (4) and disc (2); Described disc (2) is fixedly mounted on the turbine rotor (3) for including the annular of inner chamber, and outer radius is provided with 6～10 radially jets (1) that are uniformly distributed with that communicate with inner chamber; The diameter of described jet (1) is 0.6～1mm, and described oil supplying device (4) is provided with oil supply hole (6) and extend in the inner chamber of disc (2).
2. gas turbine fuel injection equipment as claimed in claim 1 is characterized in that, (6) axis of the oil supply hole on the described oil supplying device and turbine rotor (3) radially are 50～70 °, and diameter is 0.6～0.8mm.
3. according to claim 1 or claim 2 gas turbine fuel injection equipment is characterized in that, described oil supply hole axis (6) is 60 ° with turbine rotor (3).
4. according to claim 1 or claim 2 gas turbine fuel injection equipment is characterized in that the diameter of described oil supply hole (6) is 0.7mm.
5. according to claim 1 or claim 2 gas turbine fuel injection equipment is characterized in that, described oil supplying device (4) is two of symmetry.
6. gas turbine fuel injection equipment as claimed in claim 1 is characterized in that, described jet (1) is 8 that are uniformly distributed with.
7. gas turbine fuel injection equipment as claimed in claim 1 is characterized in that, described jet (1) diameter is 0.8mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120522998 CN202545021U (en) | 2011-12-13 | 2011-12-13 | Fuel oil spraying device of combustion gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120522998 CN202545021U (en) | 2011-12-13 | 2011-12-13 | Fuel oil spraying device of combustion gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202545021U true CN202545021U (en) | 2012-11-21 |
Family
ID=47165670
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120522998 Expired - Lifetime CN202545021U (en) | 2011-12-13 | 2011-12-13 | Fuel oil spraying device of combustion gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202545021U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102777263A (en) * | 2011-12-13 | 2012-11-14 | 哈尔滨东安发动机（集团）有限公司 | Fuel injection device of gas turbine |
| CN108151066A (en) * | 2017-11-24 | 2018-06-12 | 北京动力机械研究所 | Big extension atomization cone angle disc structure |
| CN112524640A (en) * | 2020-11-30 | 2021-03-19 | 北京动力机械研究所 | Secondary distribution oil supply structure |
-
2011
- 2011-12-13 CN CN 201120522998 patent/CN202545021U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102777263A (en) * | 2011-12-13 | 2012-11-14 | 哈尔滨东安发动机（集团）有限公司 | Fuel injection device of gas turbine |
| CN108151066A (en) * | 2017-11-24 | 2018-06-12 | 北京动力机械研究所 | Big extension atomization cone angle disc structure |
| CN112524640A (en) * | 2020-11-30 | 2021-03-19 | 北京动力机械研究所 | Secondary distribution oil supply structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121121 |