CN102777263A - Fuel injection device of gas turbine - Google Patents
Fuel injection device of gas turbine Download PDFInfo
- Publication number
- CN102777263A CN102777263A CN2011104211506A CN201110421150A CN102777263A CN 102777263 A CN102777263 A CN 102777263A CN 2011104211506 A CN2011104211506 A CN 2011104211506A CN 201110421150 A CN201110421150 A CN 201110421150A CN 102777263 A CN102777263 A CN 102777263A
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- Prior art keywords
- fuel injection
- oil
- gas turbine
- oil supply
- turbine rotor
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Abstract
The invention relates to a fuel injection device of a gas turbine. The fuel injection device comprises a turbine rotor, an oil supply device and an oil flinger, wherein the oil flinger is in the shape of a ring comprising an inner cavity and fixedly arranged on the turbine rotor; the outer diameter part of the oil flinger is provided with 6-10 evenly-distributed radial oil injection openings which are communicated with the inner cavity; the oil injection openings are 0.6mm-1mm in diameter; and a plurality of oil supply holes are arranged in the oil supply device and extend into the inner cavity of the oil flinger. With the adoption of the device, a nozzle structure is omitted from the whole device, an even and efficient fuel injection effect is realized in the small annular space; and the fuel injection device has the following advantages of simple and compact structure, low assembling requirement and the like.
Description
Technical field
The present invention 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 this invention is to provide a kind of compact structure, matching requirements are low, are applicable to the gas turbine fuel injection equipment of small gas turbine.
Technological scheme of the present invention 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 present invention 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 a structural representation of the present invention;
Fig. 2 is a nozzle opening position view of the present invention.
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 for including the annular of inner chamber; Be fixedly mounted on the turbine rotor (3); Outer radius is provided with 6～10 radially jets (1) that are uniformly distributed with that communicate with inner chamber, and 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. like claim 1 or 5 described gas turbine fuel injection equipments, it is characterized in that described jet (1) diameter is 0.8mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104211506A CN102777263A (en) | 2011-12-13 | 2011-12-13 | Fuel injection device of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104211506A CN102777263A (en) | 2011-12-13 | 2011-12-13 | Fuel injection device of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102777263A true CN102777263A (en) | 2012-11-14 |
Family
ID=47122335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011104211506A Pending CN102777263A (en) | 2011-12-13 | 2011-12-13 | Fuel injection device of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102777263A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151066A (en) * | 2017-11-24 | 2018-06-12 | 北京动力机械研究所 | Big extension atomization cone angle disc structure |
| CN111609424A (en) * | 2020-04-24 | 2020-09-01 | 西北工业大学 | Combined oil thrower |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004132200A (en) * | 2002-10-08 | 2004-04-30 | Toyota Central Res & Dev Lab Inc | Ignition device and method for gas turbine combustor |
| EP1509683B1 (en) * | 2002-05-14 | 2007-07-18 | Honda Giken Kogyo Kabushiki Kaisha | Gas turbine engine with active tip clearance control |
| CN201896664U (en) * | 2010-12-01 | 2011-07-13 | 哈尔滨东安发动机（集团）有限公司 | Electricity generating device of miniature gas turbine |
| CN202545021U (en) * | 2011-12-13 | 2012-11-21 | 哈尔滨东安发动机（集团）有限公司 | Fuel oil spraying device of combustion gas turbine |
-
2011
- 2011-12-13 CN CN2011104211506A patent/CN102777263A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1509683B1 (en) * | 2002-05-14 | 2007-07-18 | Honda Giken Kogyo Kabushiki Kaisha | Gas turbine engine with active tip clearance control |
| JP2004132200A (en) * | 2002-10-08 | 2004-04-30 | Toyota Central Res & Dev Lab Inc | Ignition device and method for gas turbine combustor |
| CN201896664U (en) * | 2010-12-01 | 2011-07-13 | 哈尔滨东安发动机（集团）有限公司 | Electricity generating device of miniature gas turbine |
| CN202545021U (en) * | 2011-12-13 | 2012-11-21 | 哈尔滨东安发动机（集团）有限公司 | Fuel oil spraying device of combustion gas turbine |
Non-Patent Citations (1)
| Title |
|---|
| 陈忠胜: ""涡旋式喷油嘴在柴油机上的应用"", 《现代车用动力》, no. 1, 28 February 2006 (2006-02-28), pages 24 - 29 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151066A (en) * | 2017-11-24 | 2018-06-12 | 北京动力机械研究所 | Big extension atomization cone angle disc structure |
| CN111609424A (en) * | 2020-04-24 | 2020-09-01 | 西北工业大学 | Combined oil thrower |
| CN111609424B (en) * | 2020-04-24 | 2022-06-14 | 西北工业大学 | Combined oil thrower |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121114 |