CN106050433B - A kind of high-pressure turbine blade dust arrester and its application method - Google Patents
A kind of high-pressure turbine blade dust arrester and its application method Download PDFInfo
- Publication number
- CN106050433B CN106050433B CN201610484896.4A CN201610484896A CN106050433B CN 106050433 B CN106050433 B CN 106050433B CN 201610484896 A CN201610484896 A CN 201610484896A CN 106050433 B CN106050433 B CN 106050433B
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- Prior art keywords
- pressure turbine
- air
- turbine blade
- high pressure
- bleed
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- 239000000428 dust Substances 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title abstract description 13
- 230000007246 mechanism Effects 0.000 claims abstract description 21
- 238000004891 communication Methods 0.000 claims description 18
- 238000002347 injection Methods 0.000 claims description 15
- 239000007924 injection Substances 0.000 claims description 15
- 238000009423 ventilation Methods 0.000 claims description 2
- 238000000605 extraction Methods 0.000 claims 2
- 239000012535 impurity Substances 0.000 abstract description 8
- 238000009825 accumulation Methods 0.000 abstract description 3
- 238000004904 shortening Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 31
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000003749 cleanliness Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 239000002283 diesel fuel Substances 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/30—Preventing corrosion or unwanted deposits in gas-swept spaces
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention proposes a kind of high-pressure turbine blade dust arrester and its application method, it includes at least one the jet mechanism being arranged on high-pressure turbine guider, the jet mechanism includes the sole piece along the high-pressure turbine guider radially assembled in sequence from inside to outside, base ring, bleed pipe joint, bleed sleeve pipe, thread ending cover, L-type locking plate and locking tab, pneumatic hammer moving up and down is provided with the bleed pipe joint, the bleed casing pipe sleeve is on the outside of the bleed pipe joint, the pneumatic hammer is T-shaped column structure, the pneumatic hammer is provided with a centre bore, the pneumatic hammer middle part of sliding channel is provided with least one passage connected with the centre bore with bottom sidewall.A kind of high-pressure turbine blade dust arrester provided by the present invention, solves the problem of high-pressure turbine blade is because of accumulation impurity reduction efficiency and shortening leaf longevity.Present invention also offers the application method of above-mentioned high-pressure turbine blade dust arrester.
Description
Technical Field
The invention relates to the technical field of vehicle gas turbines, in particular to a device for removing dust of high-pressure turbine blades on a vehicle gas turbine.
Background
Various complex road conditions, such as deserts, mountain roads, grasslands, highways and the like, can be met in the driving process of the vehicle, which means that air required by the gas turbine to work contains a large amount of impurities, so that the performance of the engine is influenced, and therefore, the dust removal system of the gas turbine is very important. At present, the common dust removal mode of the vehicle gas turbine is to design an external dust removal device outside the gas turbine, design an internal dust removal device inside the gas compressor and remove dust through a high-pressure air system in the gas turbine, so that the air cleanliness inside the gas turbine can be greatly improved, and the performance of the gas compressor and a combustion chamber is improved. However, because the air after dust removal is not 100% clean, and the fuel oil (diesel oil and kerosene) after filtration also contains tiny particle impurities, the fuel gas formed after the air and the fuel oil are mixed and combusted in the combustion chamber still contains impurities, and the impurities can be attached to the high-pressure turbine blades, so that the efficiency of the high-pressure turbine is reduced, and the service life of the blades is shortened due to corrosion.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a high-pressure turbine blade dust removal device and a use method thereof, so as to reduce or avoid the problems mentioned above.
In order to solve the technical problem, the invention provides a dust removal device for a high-pressure turbine blade, which is used for removing dust of the high-pressure turbine blade of a gas turbine, wherein the gas turbine is provided with a high-pressure air system, the gas turbine comprises a front casing and a high-pressure turbine guider which are connected with each other, the dust removal device comprises at least one air injection mechanism which is arranged on the high-pressure turbine guider, the air injection mechanism comprises a bottom block, a bottom ring, a gas-introducing pipe joint, a gas-introducing sleeve pipe, a threaded end cover, an L-shaped locking plate and a top locking plate which are sequentially assembled from inside to outside along the radial direction of the high-pressure turbine guider, an air hammer which can move up and down is arranged in the gas-introducing pipe joint, the gas-introducing sleeve pipe is sleeved outside the gas-introducing pipe joint, the front casing is provided with a ring cavity which is connected with, the high-pressure air system is provided with an electromagnetic valve for controlling the pipeline, the high-pressure turbine guider is provided with a second communication hole, the first communication hole is connected with the second communication hole, the inner wall of the air entraining sleeve is provided with a first annular groove, the outer wall of the air entraining sleeve is provided with a boss, the boss is provided with a third communication hole communicated with the first annular groove, the outer wall of the air entraining pipe joint is provided with a second annular groove, the second annular groove is communicated with an upper cavity of an I-shaped inner cavity of the air entraining pipe joint through at least one inclined hole, the air hammer is of a T-shaped columnar structure and is provided with a central hole, and the middle side wall and the bottom side wall of the air hammer are both provided with at least one air vent communicated with the central hole.
In a preferred embodiment, eight air injection mechanisms are uniformly distributed on the high-pressure turbine guider.
In a preferred embodiment, four inclined holes are uniformly distributed in the bleed air pipe joint.
In a preferred embodiment, four vent holes are uniformly distributed on the side wall of the middle part and the side wall of the bottom part of the air hammer.
In a preferred embodiment, the four uniformly distributed vent holes arranged on the side wall of the middle part or the side wall of the bottom part of the air hammer are two in size and two in size.
In a preferred embodiment, the first communication hole and the second communication hole each have a diameter of 4 mm.
The invention also provides a using method of the high-pressure turbine blade dust removal device, which comprises the following steps,
step A, setting the high-pressure air system to enable the pressure of high-pressure air entering the annular cavity through the pipeline to be larger than 5 MPa;
b, after the gas turbine is started and operated, turning on the electromagnetic valve for 10 seconds after 30 minutes to enable high-pressure air to enter the annular cavity through the pipeline, and removing dust on the high-pressure turbine blade through the air injection mechanism;
step C, closing the electromagnetic valve,
and D, operating the gas turbine for 30 minutes again, and repeating the step B, C until the gas turbine stops operating.
The dust removal device for the high-pressure turbine blade can effectively solve the problems that the efficiency of the high-pressure turbine blade is reduced and the service life of the blade is shortened due to the accumulation of a large amount of impurities in the high-pressure turbine blade in the long-term work of a gas turbine. The invention also provides a using method of the high-pressure turbine blade dust removal device.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
FIG. 1 is a partially sectioned, diagrammatic, schematic structural view showing a high pressure turbine blade dust collector in use, according to an embodiment of the present invention;
FIG. 2 is a schematic partially exploded perspective view of the high pressure turbine blade dust collector of FIG. 1;
FIG. 3 is a partially exploded perspective view of another angle of the air injection mechanism of FIG. 2;
FIG. 4 is a partially exploded perspective view of a further angle of the air injection mechanism of FIG. 2;
fig. 5 is a schematic sectional view a-a of the air injection mechanism of fig. 1.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
As mentioned in the background of the invention, the prior art does not provide any means for removing dust from the high pressure turbine blades of a vehicle gas turbine at all, and therefore the present invention provides a new design of a high pressure turbine blade dust removing apparatus and a method for using the same for removing dust from the high pressure turbine blades of a vehicle gas turbine.
FIG. 1 is a partially sectioned, diagrammatic, schematic structural view showing a high pressure turbine blade dust collector in use, according to an embodiment of the present invention; FIG. 2 is a schematic partially exploded perspective view of the high pressure turbine blade dust collector of FIG. 1; FIG. 3 is a partially exploded perspective view of another angle of the air injection mechanism of FIG. 2; FIG. 4 is a partially exploded perspective view of a further angle of the air injection mechanism of FIG. 2; fig. 5 is a schematic sectional view a-a of the air injection mechanism of fig. 1. Referring to fig. 1 to 5, the present invention provides a high pressure turbine blade dust removing apparatus, which is used for removing dust from a high pressure turbine blade 1 of a gas turbine, the gas turbine is provided with a high pressure air system (not shown), the gas turbine comprises a front casing 2 and a high pressure turbine guider 3 which are connected with each other, the gas turbine comprises at least one air injection mechanism which is installed on the high pressure turbine guider 3, the air injection mechanism comprises a bottom block 41, a bottom ring 42, a bleed air pipe joint 43, a bleed air sleeve 44, a threaded end cover 45, an L-shaped locking plate 46 and a top locking plate 47 which are sequentially assembled from inside to outside along the radial direction of the high pressure turbine guider 3, an air hammer 48 which can move up and down is arranged in the bleed air pipe joint 43, the bleed air sleeve 44 is sleeved outside the bleed air pipe joint 43, the front casing 2 is provided with a ring cavity 21 which is connected with the high pressure air system through a pipeline (not shown in the figure) and a A communication hole 22, said high pressure air system being provided with solenoid valves (not shown) for controlling said ducts, the high-pressure turbine guide 3 is provided with a second communication hole 31, the first communication hole 22 is connected with the second communication hole 31, the inner wall of the bleed sleeve 44 is provided with a first annular groove 441, the outer wall is provided with a boss 442, the boss 442 is provided with a third communication hole 443 communicating with the first annular groove 441, the outer wall of the bleed air pipe joint 43 is provided with a second annular groove 431, the second annular groove 431 is communicated with the upper cavity of the I-shaped inner cavity of the bleed air pipe joint 43 through at least one inclined hole 432, the air hammer 48 has a T-shaped cylindrical structure, the air hammer 48 is provided with a central hole 481, at least one vent 482 communicated with the central hole 481 is arranged on the side wall of the middle part and the side wall of the bottom part of the air hammer 48.
The working principle of the high-pressure turbine blade dust removal device provided by the invention is as follows: when the high-pressure air of the gas turbine provided with the high-pressure air system enters the annular cavity 21 through the pipeline for distribution balance, enters the second communication hole 31 on the high-pressure turbine guider 3 through the first communication hole 22 on the front mounting edge end surface of the front casing 2, then enters the annular cavity consisting of the first annular groove 441 and the second annular groove 431 through the third communication hole 443, and enters the i-shaped cavity of the bleed air pipe joint 43 through the inclined hole 432, the high-pressure air entering the i-shaped cavity pushes the air hammer 48 to move outwards, and when the vent hole 482 on the middle side wall of the air hammer 48 is communicated with the upper cavity of the i-shaped cavity, the high-pressure air flows towards the top of the i-shaped cavity through the central hole 481 and simultaneously towards the bottom of the i-shaped cavity through the vent hole 482 on the bottom side wall of the air hammer 48, the high-pressure air flowing to the top of the i-shaped inner cavity is gathered to push the air hammer 48 to move inwards, so that the vent holes 482 in the side wall of the middle of the air hammer 48 are disconnected with the upper cavity of the i-shaped inner cavity, and the high-pressure air flowing to the bottom of the i-shaped inner cavity is sprayed out from a gap between the fixing ring and the mounting edge of the high-pressure turbine guider 3. That is, continuous high-pressure air is intermittently ejected from the gap between the stationary ring and the mounting edge of the high-pressure turbine vane 3 after being pressure-regulated by the air hammer 48 by the reciprocating motion of the air hammer 48, thereby removing dust from the high-pressure turbine blade 1 and also having a certain cooling effect.
The bottom block 41 mounted in the bottom ring 42 limits the stroke of the air hammer 48, and prevents damage to the high pressure turbine nozzle 3 caused by the reciprocating movement of the air hammer 48.
The threaded end cap 45 is used to close the upper cavity of the i-shaped inner cavity of the bleed air connection 43.
The L-shaped locking tab 46 locks the bleed sleeve 44 by locking the boss 442.
The top locking tab 47 is used to lock the threaded end cap 45 and the L-shaped locking tab 46.
In a preferred embodiment, eight jet mechanisms are uniformly distributed on the high-pressure turbine guider 3. This allows good dust removal of the high-pressure turbine blade 1.
In a preferred embodiment, the bleed air connections 43 are each provided with four angled holes 432. This provides a relatively uniform passage of high pressure air.
In a preferred embodiment, four vent holes 482 are uniformly distributed on the side wall of the middle part and the side wall of the bottom part of the air hammer 48. This provides a relatively uniform passage of high pressure air.
In a preferred embodiment, the four uniformly distributed air holes 482 formed in the middle or bottom side wall of the air hammer 48 may have different diameters, such as two sizes, so that the air hammer 48 can rotate during the air ventilation process, thereby making the high pressure air flow more uniform.
In a preferred embodiment, the diameters of the first communication hole 22 and the second communication hole 31 are both 4mm, so that it is possible to avoid the influence of these increased structures on the structural strength of the front case 2 and the high-pressure turbine guide 3.
The invention also provides a using method of the high-pressure turbine blade dust removal device, which comprises the following steps,
step A, setting the high-pressure air system to enable the pressure of the high-pressure air entering the annular cavity 21 through the pipeline to be larger than 5 MPa;
step B, after the gas turbine is started and operated, after 30 minutes, the electromagnetic valve is opened for 10 seconds, so that high-pressure air enters the annular cavity 21 through the pipeline, and the high-pressure turbine blade 1 is subjected to dust removal through the air injection mechanism;
step C, closing the electromagnetic valve,
and D, operating the gas turbine for 30 minutes again, and repeating the step B, C until the gas turbine stops operating.
The gas pressure at the high-pressure turbine blades 1 of a gas turbine is usually below 1MPa, so that the high-pressure air discharged via the jet mechanism can completely clean impurities on the high-pressure turbine blades 1. The dust removal process is only 10s, so that the performance of the gas turbine is not influenced.
The dust removal device for the high-pressure turbine blade can effectively solve the problems that the efficiency of the high-pressure turbine blade is reduced and the service life of the blade is shortened due to the accumulation of a large amount of impurities in the high-pressure turbine blade in the long-term work of a gas turbine. The invention also provides a using method of the high-pressure turbine blade dust removal device.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (7)
1. The utility model provides a high pressure turbine blade dust collector, it is used for removing dust to the high pressure turbine blade of gas turbine, gas turbine is provided with the high-pressure air system, gas turbine includes interconnect's preceding casket and high pressure turbine director, its characterized in that, it is including installing at least one jet mechanism on the high pressure turbine director, jet mechanism includes along bottom block, bottom ring, bleed pipe joint, bleed sleeve pipe, threaded end cover, L type locking plate and the top locking plate of high pressure turbine director radial from inside to outside order assembly, be provided with the air hammer that can reciprocate in the bleed pipe joint, the bleed sleeve pipe suit is in the bleed pipe joint outside, preceding casket be provided with the high pressure air system passes through the ring chamber of pipe connection and with the first connecting hole of ring chamber intercommunication, the high pressure air system is provided with the solenoid valve that is used for controlling the pipeline, the high-pressure turbine guider is provided with a second communicating hole, the first communicating hole is connected with the second communicating hole, a first annular groove is formed in the inner wall of the air entraining sleeve, a boss is arranged on the outer wall of the air entraining sleeve, a third communicating hole communicated with the first annular groove is formed in the boss, a second annular groove is formed in the outer wall of the air entraining pipe joint, the second annular groove is communicated with an upper cavity of an I-shaped inner cavity of the air entraining pipe joint through at least one inclined hole, the air hammer is of a T-shaped columnar structure and is provided with a central hole, and at least one vent hole communicated with the central hole is formed in the middle side wall and the bottom side wall of the air hammer.
2. The high pressure turbine blade dust collector of claim 1 wherein eight of said air injection mechanisms are uniformly distributed on said high pressure turbine guide.
3. The high pressure turbine blade dust extraction system of claim 1 wherein four of said angled holes are provided in said bleed air connection.
4. The high pressure turbine blade dust extraction system of claim 1 wherein four evenly spaced vent holes are provided in both the air hammer middle sidewall and the air hammer bottom sidewall.
5. The high pressure turbine blade dust collector of claim 4, wherein the four evenly distributed ventilation holes provided in the side wall of the air hammer middle part or the side wall of the air hammer bottom are two in size and two in size.
6. The high pressure turbine blade dust removing device according to claim 1, wherein the first communication hole and the second communication hole each have a diameter of 4 mm.
7. Use of a high pressure turbine blade dust removal device according to any one of claims 1 to 6, characterised in that it comprises the steps of,
step A, setting the high-pressure air system to enable the pressure of high-pressure air entering the annular cavity through the pipeline to be larger than 5 MPa;
b, after the gas turbine is started and operated, turning on the electromagnetic valve for 10 seconds after 30 minutes to enable high-pressure air to enter the annular cavity through the pipeline, and removing dust on the high-pressure turbine blade through the air injection mechanism;
step C, closing the electromagnetic valve,
and D, operating the gas turbine for 30 minutes again, and repeating the step B, C until the gas turbine stops operating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610484896.4A CN106050433B (en) | 2016-06-28 | 2016-06-28 | A kind of high-pressure turbine blade dust arrester and its application method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610484896.4A CN106050433B (en) | 2016-06-28 | 2016-06-28 | A kind of high-pressure turbine blade dust arrester and its application method |
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| Publication Number | Publication Date |
|---|---|
| CN106050433A CN106050433A (en) | 2016-10-26 |
| CN106050433B true CN106050433B (en) | 2017-10-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610484896.4A Active CN106050433B (en) | 2016-06-28 | 2016-06-28 | A kind of high-pressure turbine blade dust arrester and its application method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113176085B (en) * | 2021-04-30 | 2024-01-02 | 江苏江航智飞机发动机部件研究院有限公司 | Aeroengine hot end turbine hollow blade profile detection device |
| CN114483310B (en) * | 2022-01-25 | 2023-07-04 | 中国联合重型燃气轮机技术有限公司 | Dustproof structure of heavy-duty gas turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3637060A1 (en) * | 1986-10-31 | 1988-05-05 | Wacker Chemie Gmbh | Device for spraying or injecting liquid into a container and use thereof |
| CN201092868Y (en) * | 2007-11-07 | 2008-07-30 | 成都发动机（集团）有限公司 | Dust removal and desalination injection mechanism for turbine movable blades |
| CN201385001Y (en) * | 2009-01-16 | 2010-01-20 | 青岛双桃精细化工（集团）有限公司 | Water pressure type self-cleaning spray gun |
| CN102297026A (en) * | 2011-07-28 | 2011-12-28 | 中国南方航空工业(集团)有限公司 | Dust collector and ground gas turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100464868C (en) * | 2003-01-24 | 2009-03-04 | 图柏特克有限公司 | Method and injection nozzle for interspersing a gas flow with liquid droplets |
-
2016
- 2016-06-28 CN CN201610484896.4A patent/CN106050433B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3637060A1 (en) * | 1986-10-31 | 1988-05-05 | Wacker Chemie Gmbh | Device for spraying or injecting liquid into a container and use thereof |
| CN201092868Y (en) * | 2007-11-07 | 2008-07-30 | 成都发动机（集团）有限公司 | Dust removal and desalination injection mechanism for turbine movable blades |
| CN201385001Y (en) * | 2009-01-16 | 2010-01-20 | 青岛双桃精细化工（集团）有限公司 | Water pressure type self-cleaning spray gun |
| CN102297026A (en) * | 2011-07-28 | 2011-12-28 | 中国南方航空工业(集团)有限公司 | Dust collector and ground gas turbine |
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| Publication number | Publication date |
|---|---|
| CN106050433A (en) | 2016-10-26 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
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