CN1187601A - Centerbody for two stream tangential entry nozzle - Google Patents
Centerbody for two stream tangential entry nozzle Download PDFInfo
- Publication number
- CN1187601A CN1187601A CN 97125242 CN97125242A CN1187601A CN 1187601 A CN1187601 A CN 1187601A CN 97125242 CN97125242 CN 97125242 CN 97125242 A CN97125242 A CN 97125242A CN 1187601 A CN1187601 A CN 1187601A
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- cylindrical passageway
- centerbody
- cylindrical
- frustum
- passageway
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Abstract
A centerbody for a tangential entry fuel nozzle includes a base having at least one air supply port extending therethrough, a radially outer surface including a frustum portion and a cylindrical portion, an internal passageway which communicates with an internal chamber through a swirler, and a fuel lance extending through the base, the internal chamber, and the swirler, and terminating within the second cylindrical passage. When the present invention is used in gas turbine, it prolongs using life obviously comparing with the traditional technique and reduce the trend of connection of the fire and the said centerbody obviously.
Description
The present invention relates to low Ox premixed fuel nozzle, especially for the centerbody of this type of nozzle.
Nitrogen oxide (calling " NOx " in the following text) is to produce by the burning under the high temperature.NOx makes the burner that produces NOx will observe strict emission control standards as notorious polluter.Therefore, many effort have been paid to reduce the formation of NOx in burner.
A kind of solution is with excessive air and fuel premixed, and burning is occurred in the local excessive air, causes relatively low ignition temperature, thereby reduces the generation of NOx.Yun Hang a kind of fuel nozzle is showed in U.S. Patent No. 5,307 like this, in 634, this patent disclosure a kind of vortice with conical centerbody.Such fuel nozzle is called tangential injection fuel nozzle, and it is connected by two end plates by the cylinder arc volute casing that two centers of circle do not overlap.Burning gases enter cyclone by the rectangular aperture that is formed by volute casing arranged side by side, and the inlet portion of burner flows out and enters burner on by end plate.One group is arranged on respect to the linearly aligned aperture that is on the outside volute casing of inboard trailing edge, and fuel is sprayed into the air stream in each import department from a house steward, produces uniform fuel air mixture before entering burner.
Tangential injection type pre-mixed fuel nozzle is verified, can produce lower NOx discharging with respect to the fuel nozzle of prior art.Yet disclosed this class A fuel A nozzle of patent when being used for combustion gas turbine, because the nozzle centerbody is positioned at the zone that contacts with flame, presents the of short duration service life that can not make us accepting as described above.Make this type of tangential injection type fuel nozzle not enter the commercial application field of combustion gas turbine as yet.
Thereby need a kind of centerbody that is used for tangentially injecting the type fuel nozzle, when being used for combustion gas turbine, it has the service life of obvious prolongation with respect to conventional art.
Therefore, one object of the present invention is to provide a kind of centerbody that is used for low NOx fuel nozzle, and this centerbody has the service life of obvious prolongation with respect to conventional art when being used for combustion gas turbine.
Another object of the present invention is, a kind of centerbody that is used for tangentially injecting the type fuel nozzle is provided, and it can obviously reduce the trend that flame contacts with this centerbody.
Thereby, centerbody of the present invention comprises a pedestal with air supply opening of at least one perforation, a radiation outer surface that comprises frustum body and cylindrical portion, article one, pass the inner passage that cyclone and inner chamber are linked up, one is passed pedestal, inner chamber, cyclone extends and ends at fuel nozzle in second cylindrical passageway.
Figure 1 shows that centerbody longitudinal cross-section of the present invention.
Figure 2 shows that among Fig. 1 cross section along the 2-2 line.
Figure 3 shows that the longitudinal cross-section of centerbody of the present invention along 3-3 line among Fig. 2.
With reference to figure 1, centerbody 10 of the present invention has a pedestal 12, has one on it at least, and the air supply port 14,16 of some perforations is preferably arranged, and pedestal 12 is vertical with the longitudinal axis of centerbody 10.Centerbody 10 also has an inner passage 20 coaxial with the longitudinal axis 18.In the preferred embodiment of the present invention, inner passage 20 comprises one first cylindrical passageway 22, and it has first end 24 and 26, one diameters of second end greater than second cylindrical passageway 28 of first cylindrical passageway 22, has one first end 30 and second end 32 equally.Second cylindrical passageway 28 is connected by a tapered channel 34 with first cylindrical passageway 22, and its first end 36 is identical with first cylindrical passageway, 22 diameters, and second end 38 is identical with second cylindrical passageway, 28 diameters.Each passage 22,28,34 is all coaxial with the longitudinal axis 18, and second end 26 of first end 36 of tapered channel 34 and first cylindrical passageway 22 is combined as a whole, and second end 38 of tapered channel 34 and first end 30 of second cylindrical passageway 28 are combined as a whole simultaneously.First cylindrical passageway 22 comprise a circle and with the longitudinal axis 18 flow exports 40 coaxial, that be arranged on first cylindrical passageway, 22 first ends 24.
The radiation outer surface 42 of centerbody 10 comprises a frustum body 44, it has determined the outer surface with the coaxial frustum of the longitudinal axis 18, and opens to pedestal 12 directions, the cylindrical portion 46 that is combined as a whole with frustum body 44, determined the outer surface of cylinder, and coaxial with axle 18.In preferred embodiment, cylindrical portion 46 ends in the plane of flow export 40 settings, frustum body 44 is 2.65 times of its top ends diameter at the diameter of pedestal 12, and the height 48 of frustum body 44 (plane that pedestal 12 and frustum body 44 intersect and the distance between the plane, place, frustum body 44 top) is approximately frustum body 44 1.3 times at the diameter at pedestal 12 places.Cylindrical portion 46 is between frustum body 44 and flow export 40.Inner passage 20 is positioned at the inner radial of the radially outer surface 42 of centerbody 10, and frustum body 44 is coaxial with the longitudinal axis 18, and centerbody 10 is connected with pedestal 12, and frustum body 44 is upwards come to a point, and ends in cylindrical portion 46.The base portion of frustum body 44 is installed in to have on the annular 50 of the central point on the longitudinal axis 18 52, as shown in Figure 2.
Be arranged on centerbody 10 inside with reference to 3, one inner chambers 58 of figure, between second end 32 and pedestal 12 that terminate in inner chamber 58 of second cylindrical passageway 28. Air supply port 14,16 in the pedestal 12 and inner chamber 58 are linked up, and link up mutually with inner passage 20 by second end 32 of second cylindrical passageway 28 successively again.A cyclone 60 preferably uses known radial type, and is coaxial with the longitudinal axis 18, and directly second end 32 with second cylindrical passageway 28 is adjacent to be arranged in inner chamber 58, makes inner passage 20 link up mutually with inner chamber 58 by cyclone 60.
A fuel nozzle 62, same coaxial with the longitudinal axis 18, and pass second cylindrical passageway 28 that pedestal 12, inner chamber 58 and cyclone 60 enter inner passage 20.Second cylindrical passageway, 28 bigger diameters hold the cross-sectional area of fuel nozzle 62, make the circulation area of second cylindrical passageway 28 equal the circulation area of first cylindrical passageway 22 substantially.Fuel nozzle 62 has an internal channel 64, and is arranged at the fuel nozzle ports 66 on the fuel nozzle 62, as the passage of internal channel 64 with inner passage 20 communications.
Detection to centerbody 10 of the present invention proves, by the contact trend of reduction flame with centerbody 10, when making centerbody 10 be used for gas turbine, has obviously improved service life than prior art.Therefore, the invention provides the problem that tangential entry nozzle is widely used in gas turbine that hinders that solves.
Though the present invention it will be appreciated by those skilled in the art that in not departing from interest field of the present invention by example details being showed and describing, the various variations of form and details can occur.
Claims (1)
1, a kind of centerbody that is used for tangentially injecting fuel nozzle comprises:
A longitudinal axis,
A centerbody pedestal, described centerbody pedestal have at least one and pass wherein air supply hole,
A radially outer surface, comprise a frustum body and a cylindrical portion that defines the frustum outer surface, frustum is coaxial with the longitudinal axis, and spread towards frustum pedestal direction, cylindrical portion and frustum body are in aggregates, and having determined the outer surface of cylinder rightly, described frustum portion is positioned between described cylindrical portion and the described axis
An inner passage coaxial with the longitudinal axis, comprise one first cylindrical passageway, one second cylindrical passageway, and tapered channels, each passage all has first end and second end, the diameter of described second cylindrical passageway is greater than first cylindrical passageway, described second cylindrical passageway is linked up by the described tapered channels and first cylindrical passageway, first end of described tapered channels combines with second end of described first cylindrical passageway, second end of described tapered channels combines with first end of described second cylindrical passageway, the diameter of described tapered channels first end is identical with the diameter of first cylindrical passageway, the diameter of described tapered channels second end is identical with the diameter of second cylindrical passageway, described each passage is all coaxial with the longitudinal axis, described first cylindrical passageway has a circular tap hole and described axis coaxle, and be positioned at first end of first cylindrical passageway
An inner chamber, between second end of described centerbody base portion and described second cylindrical passageway, described air supply hole is linked up by the described inner chamber and second cylindrical passageway,
Cyclone with axis coaxle, it is arranged in the inner chamber, nestles up second end of second cylindrical passageway, and,
Fuel nozzle with axis coaxle, it passes described centerbody base portion, described inner chamber and described cyclone, and ends in second cylindrical passageway.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97125242 CN1187601A (en) | 1996-12-20 | 1997-12-19 | Centerbody for two stream tangential entry nozzle |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US770282 | 1996-12-20 | ||
| CN 97125242 CN1187601A (en) | 1996-12-20 | 1997-12-19 | Centerbody for two stream tangential entry nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1187601A true CN1187601A (en) | 1998-07-15 |
Family
ID=5177210
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97125242 Pending CN1187601A (en) | 1996-12-20 | 1997-12-19 | Centerbody for two stream tangential entry nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1187601A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111765032A (en) * | 2020-06-12 | 2020-10-13 | 沈阳航空航天大学 | Sliding arc plasma-high disturbance cross structure fuel oil atomizing nozzle |
-
1997
- 1997-12-19 CN CN 97125242 patent/CN1187601A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111765032A (en) * | 2020-06-12 | 2020-10-13 | 沈阳航空航天大学 | Sliding arc plasma-high disturbance cross structure fuel oil atomizing nozzle |
| CN111765032B (en) * | 2020-06-12 | 2022-06-14 | 沈阳航空航天大学 | Sliding arc plasma-high disturbance cross structure fuel oil atomizing nozzle |
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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 |