CN214145679U - Cooling device for high-temperature exhaust of gas turbine compressor - Google Patents
Cooling device for high-temperature exhaust of gas turbine compressor Download PDFInfo
- Publication number
- CN214145679U CN214145679U CN202022982877.9U CN202022982877U CN214145679U CN 214145679 U CN214145679 U CN 214145679U CN 202022982877 U CN202022982877 U CN 202022982877U CN 214145679 U CN214145679 U CN 214145679U
- Authority
- CN
- China
- Prior art keywords
- compressor
- air inlet
- gas
- gas turbine
- cooling
- 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.)
- Active
Links
Images
Abstract
The utility model discloses a cooling device for high-temperature exhaust of a gas turbine compressor, which comprises a cooling pipeline and a pipeline body fixing device; the main body of the cooling pipeline winds at least two circles, the outer diameter of each circle of cooling pipeline is similar to the inner wall of the air inlet duct of the air compressor and is 80% -99% of the inner diameter of the air inlet duct; the main body of the cooling pipeline is arranged in the air inlet duct, and the air inlet end and the air outlet end of the cooling pipeline respectively penetrate out of the air inlet duct of the compressor; each circle of the cooling pipeline is detachably fixed to the side wall of the air inlet duct through at least 2 pipeline body fixing devices; and the air inlet end of the cooling pipeline is connected with the exhaust of the compressor. The utility model discloses the cooling device of gas turbine compressor high temperature exhaust who solves can cool off the high temperature high-pressure gas of drawing forth from the compressor exhaust end more high-efficiently, and simple structure is reliable, the maintenance of being convenient for.
Description
Technical Field
The utility model relates to a gas turbine, in particular to cooling device of gas turbine compressor high temperature exhaust.
Background
The gas turbine consists of a gas compressor, a combustion chamber and a turbine, wherein the gas compressor compresses air during working, the air enters the combustion chamber to be mixed and combusted with fuel to push the turbine to rotate, and the turbine outputs work.
The micro gas turbine is a heat engine capable of continuously rotating to do work, and compared with other engines, the micro gas turbine has the advantages of energy conservation, environmental protection, high power density, simplicity in maintenance, high reliability and the like.
The gas turbine provides high-pressure air for the gas turbine, the high-pressure air and fuel are mixed and combusted to generate larger kinetic energy, and when the gas turbine works, if lubricating oil of a lubricating system is sucked into the gas compressor by the gas compressor and is combusted in a combustion chamber, the turbine is influenced, and in serious cases, knocking is generated to cause damage to a unit. And the constant burning of the lubricating oil increases the running cost.
In order to improve efficiency and reduce energy consumption, the exhaust of a gas turbine compressor can be generally used for mechanisms needing compressed air, such as bearing lubricating oil seal, valve action, air inlet filtering system back flushing and the like, but the air supply requirement cannot be met due to high exhaust temperature of the compressor, for example, the phenomenon of lubricating oil coking can be caused by overhigh temperature of the compressed air used for bearing lubricating oil seal, and the operation of a unit is seriously influenced. But the existing scheme can not achieve a good cooling effect, and still causes the phenomenon of the glue formation of the lubricating oil, thereby influencing the operation of the unit.
An existing gas turbine oil-gas cooling and lubricating system is shown in fig. 1 and comprises a gas turbine, an air filter, a front bearing, a rear bearing, an oil pump, an oil tank and a gear box; the gas turbine air compressor machine in link to each other with air cleaner, be connected with front bearing and rear bearing on the air compressor machine among the gas turbine, air cleaner links to each other with the rear bearing, front bearing and rear bearing all link to each other with the oil tank, the oil tank links to each other with the oil pump, the oil pump links to each other with gear box, front bearing and rear bearing respectively, the gear box links to each other with the oil tank. The gas turbine comprises a gas compressor, a combustion chamber and a turbine; the air compressor is connected with the turbine, the air compressor is respectively connected with the air filter and the combustion chamber, and the combustion chamber is connected with the turbine. The device still includes oil gas device, oil gas device be equipped with lubrication hole and air hole, air cleaner link to each other with the rear bearing through oil gas device's air hole, oil pump and oil tank all link to each other with the rear bearing through oil gas device's lubrication hole. Lubricating oil and air enter the oil-gas device through a pipeline, and the oil-gas device is provided with a lubricating hole and an air hole which act on the bearing together. The system adopts lubricating oil and partial sealing cooling gas in the gas compressor, and the sealing cooling gas mainly acts on the rear bearing, because the rear bearing is close to one end of the turbine and one end of the gas compressor, the temperature is high, and the temperature of the position of the front bearing is low, and the front bearing is cooled by the lubricating oil.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide a gas turbine compressor high temperature exhaust's cooling device, can cool off the high temperature high-pressure gas of drawing forth from the compressor exhaust end more high-efficiently, simple structure is reliable, the maintenance of being convenient for.
In order to solve the technical problem, the cooling device for high-temperature exhaust of the gas turbine compressor provided by the utility model comprises a cooling pipeline 1 and a pipeline body fixing device 3;
the main body of the cooling pipeline 1 is wound at least two circles, the outer diameter of each circle of cooling pipeline 1 is similar to the inner wall of the air inlet duct 2 of the air compressor and is 80% -99% of the inner diameter of the air inlet duct 2;
the main body of the cooling pipeline 1 is arranged inside the air inlet duct 2, and the air inlet end and the air outlet end of the cooling pipeline respectively penetrate out of the air inlet duct 2 of the compressor;
each circle of the cooling pipeline 1 is detachably fixed on the side wall of the air inlet duct 2 through at least 2 pipeline body fixing devices 3;
and the air inlet end of the cooling pipeline 1 is connected with the exhaust of the compressor.
Preferably, the gas discharged from the gas outlet end of the cooling pipeline 1 is used for sealing bearing lubricating oil.
Preferably, the gas discharged from the gas outlet end of the cooling pipeline 1 is used for valve driving.
Preferably, the gas discharged from the gas outlet end of the cooling pipeline 1 is used for back blowing of the gas inlet filter.
Preferably, the cooling pipeline 1 penetrates out of the air inlet duct 2 of the compressor and is detachably fixed on the side wall of the air inlet duct 2 of the compressor through a pipeline head fixing device 4.
Preferably, the radial section of the air inlet duct 2 of the compressor is rectangular, oval or circular.
Preferably, the pipe body fixing device 3 comprises a pipe clamp 5, a bolt 6 and a nut 7;
the pipe clamp 5 is used for supporting the cooling pipeline 1;
the bolt 6 penetrates through the side wall of the air inlet duct 2;
the nut 7 cooperates with the bolt 6 to clamp the pipe clamp 5 on the side wall of the air inlet duct 2.
Preferably, the bearing seal structure of the gas turbine is provided with a bearing lubricating oil cavity 100;
the gap between the centrifugal impeller 310 of the gas turbine and the turbine stator 320 of the gas turbine forms a clearance channel 300;
a high-pressure cavity 200 is arranged between the bearing lubricating oil cavity 100 and the clearance channel 300;
the air outlet end of the cooling pipeline 1 is communicated with the high-pressure cavity 200.
The utility model discloses a gas turbine compressor high temperature exhaust's cooling device through set up surrounding type's the cooling tube that dismantles 1 in compressor air inlet duct 2, utilizes the inlet air of gas turbine compressor, cools off the high temperature high-pressure gas of drawing forth from the compressor exhaust end more high-efficiently, makes this high temperature high-pressure gas obtain effective cooling and obtain low temperature high-pressure gas. The cooling device for high-temperature exhaust of the gas turbine compressor is simple and reliable in structure and convenient to maintain, low-temperature high-pressure gas generated by the cooling device can be used for sealing bearing lubricating oil in the operation process of the gas turbine so as to avoid the caking of the lubricating oil, and can also be used for valve driving or back flushing of an air inlet filter so as to reduce energy consumption.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings required for the present invention are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic diagram of a prior art gas turbine oil and gas cooling and lubricating system;
FIG. 2 is a schematic structural diagram of an embodiment of a cooling device for high-temperature exhaust of a gas turbine compressor according to the present invention;
FIG. 3 is a schematic structural view of a pipe fixing device according to an embodiment of the cooling device for high-temperature exhaust of a gas turbine compressor of the present invention;
FIG. 4 is a schematic structural view of an embodiment of a bearing seal structure of a gas turbine.
The reference numbers in the figures illustrate:
1 cooling the pipeline; 2, an air inlet duct; 3, a pipeline body fixing device; 4, a pipeline head fixing device; 5, pipe clamp; 6, bolts; 7, a nut; 100 bearing lubricating oil cavities; 140 bearings; 310 a centrifugal impeller of a gas turbine; 320 turbine stator of a gas turbine; 300 gap channels; 200 high pressure chamber.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments, but not all embodiments, of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
Example one
As shown in fig. 2, the cooling device for high-temperature exhaust of the gas turbine compressor comprises a cooling pipeline 1 and a pipeline body fixing device 3;
the main body of the cooling pipeline 1 is wound at least two circles, the outer diameter of each circle of cooling pipeline 1 is similar to the inner wall of the air inlet duct 2 of the air compressor and is 80% -99% of the inner diameter of the air inlet duct 2;
the main body of the cooling pipeline 1 is arranged inside the air inlet duct 2, and the air inlet end and the air outlet end of the cooling pipeline respectively penetrate out of the air inlet duct 2 of the compressor;
each circle of the cooling pipeline 1 is detachably fixed on the side wall of the air inlet duct 2 through at least 2 pipeline body fixing devices 3;
and the air inlet end of the cooling pipeline 1 is connected with the exhaust of the compressor.
Preferably, the gas discharged from the gas outlet end of the cooling pipeline 1 can be used for bearing lubricating oil sealing, valve driving or gas inlet filter back flushing.
Preferably, the cooling pipeline 1 penetrates out of the air inlet duct 2 of the compressor and is detachably fixed to the side wall of the air inlet duct 2 of the compressor through the pipeline head fixing device 4, so that the cooling pipeline is convenient to detach and maintain.
Preferably, the radial section of the air inlet duct 2 of the compressor is rectangular, oval or circular.
In the cooling device for high-temperature exhaust of the gas turbine compressor in the first embodiment, the cooling pipeline 1 is arranged inside the air inlet duct 2 of the compressor, and gas in the cooling pipeline 1 is cooled by inlet air of the compressor; the cooling pipeline 1 is close to the inner side of the air inlet duct 2 of the air compressor, at least two circles of cooling pipeline are wound along the axial direction of the air inlet duct 2 of the air compressor at the front and back, a multilayer structure is formed along the axial direction of the air inlet duct 2 of the air compressor, and the cooling pipeline is supported and fixed on the side wall of the air inlet duct 2 of the air compressor through the pipeline fixing device 3, so that the cooling area is increased, and the resistance brought to air inlet of the air compressor is reduced.
According to the cooling device for high-temperature exhaust of the gas turbine compressor, the surrounding detachable cooling pipeline 1 is arranged in the air inlet duct 2 of the compressor, and high-temperature and high-pressure gas led out from the exhaust end of the compressor is cooled more efficiently by utilizing the inlet air of the gas turbine compressor, so that the high-temperature and high-pressure gas is effectively cooled to obtain low-temperature and high-pressure gas. The cooling device for high-temperature exhaust of the gas turbine compressor is simple and reliable in structure and convenient to maintain, low-temperature high-pressure gas generated by the cooling device can be used for sealing bearing lubricating oil in the operation process of the gas turbine so as to avoid the caking of the lubricating oil, and can also be used for valve driving or back flushing of an air inlet filter so as to reduce energy consumption.
Example two
According to the cooling device for high-temperature exhaust gas of the gas turbine compressor in the first embodiment, as shown in fig. 3, the pipeline body fixing device 3 comprises a pipe clamp 5, a bolt 6 and a nut 7;
the pipe clamp 5 is used for supporting the cooling pipeline 1;
the bolt 6 penetrates through the side wall of the air inlet duct 2;
the nut 7 cooperates with the bolt 6 to clamp the pipe clamp 5 on the side wall of the air inlet duct 2.
EXAMPLE III
According to the cooling device for high-temperature exhaust of the compressor of the gas turbine in the first embodiment, as shown in fig. 4, a bearing 140 sealing structure of the gas turbine is provided with a bearing lubricating oil cavity 100;
the gap between the centrifugal impeller 310 of the gas turbine and the turbine stator 320 of the gas turbine forms a clearance channel 300;
a high-pressure cavity 200 is arranged between the bearing lubricating oil cavity 100 and the clearance channel 300;
the air outlet end of the cooling pipeline 1 is communicated with the high-pressure cavity 200.
In the cooling device for high-temperature exhaust of the gas turbine compressor in the third embodiment, the low-temperature high-pressure gas discharged from the gas outlet end of the cooling pipeline 1 enters the high-pressure cavity 200, so that the pressure in the high-pressure cavity 200 is greater than the pressure in the lubricating oil cavity 100, oil mist in the bearing lubricating oil cavity 100 cannot enter the high-pressure cavity 200, the gas turbine is ensured not to be polluted by the oil mist in the bearing lubricating oil cavity 100 in the working process, and the lubricating oil in the lubricating oil cavity 100 is effectively cooled.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A cooling device for high-temperature exhaust of a gas turbine compressor is characterized by comprising a cooling pipeline (1) and a pipeline body fixing device (3);
the main body of the cooling pipeline (1) winds at least two circles, the outer diameter of each circle of cooling pipeline (1) is similar to the inner wall of the air inlet duct (2) of the air compressor and is 80% -99% of the inner diameter of the air inlet duct (2);
the cooling pipeline (1) is provided with a main body inside the air inlet duct (2), and an air inlet end and an air outlet end of the cooling pipeline respectively penetrate out of the air inlet duct (2) of the air compressor;
each circle of the cooling pipeline (1) is detachably fixed to the side wall of the air inlet duct (2) through at least 2 pipeline body fixing devices (3);
and the air inlet end of the cooling pipeline (1) is connected with the exhaust of the compressor.
2. The cooling device for high-temperature exhaust gas of a compressor of a gas turbine according to claim 1,
and gas discharged from the gas outlet end of the cooling pipeline (1) is used for sealing bearing lubricating oil.
3. The cooling device for high-temperature exhaust gas of a compressor of a gas turbine according to claim 1,
and gas discharged from the gas outlet end of the cooling pipeline (1) is used for driving a valve.
4. The cooling device for high-temperature exhaust gas of a compressor of a gas turbine according to claim 1,
and gas discharged from the gas outlet end of the cooling pipeline (1) is used for back flushing of the gas inlet filter.
5. The cooling device for high-temperature exhaust gas of a compressor of a gas turbine according to claim 1,
the cooling pipeline (1) penetrates out of the air inlet duct (2) of the air compressor and is detachably fixed to the side wall of the air inlet duct (2) of the air compressor through a duct head fixing device (4).
6. The cooling device for high-temperature exhaust gas of a compressor of a gas turbine according to claim 1,
the radial section of an air inlet duct (2) of the air compressor is rectangular, oval or circular.
7. The cooling device for high-temperature exhaust gas of a compressor of a gas turbine according to claim 1,
the pipeline body fixing device (3) comprises a pipe clamp (5), a bolt (6) and a nut (7);
the pipe clamp (5) is used for supporting the cooling pipeline (1);
the bolt (6) penetrates through the side wall of the air inlet duct (2);
the nut (7) is matched with the bolt (6) to clamp the pipe clamp (5) on the side wall of the air inlet duct (2).
8. The cooling device for high-temperature exhaust gas of a compressor of a gas turbine according to claim 1,
the bearing sealing structure of the gas turbine is provided with a bearing lubricating oil cavity (100);
a gap between a centrifugal impeller (310) of the gas turbine and a turbine stator (320) of the gas turbine forms a clearance channel (300);
a high-pressure cavity (200) is arranged between the bearing lubricating oil cavity (100) and the clearance channel (300);
the air outlet end of the cooling pipeline (1) is communicated with the high-pressure cavity (200).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022982877.9U CN214145679U (en) | 2020-12-14 | 2020-12-14 | Cooling device for high-temperature exhaust of gas turbine compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022982877.9U CN214145679U (en) | 2020-12-14 | 2020-12-14 | Cooling device for high-temperature exhaust of gas turbine compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214145679U true CN214145679U (en) | 2021-09-07 |
Family
ID=77586133
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022982877.9U Active CN214145679U (en) | 2020-12-14 | 2020-12-14 | Cooling device for high-temperature exhaust of gas turbine compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214145679U (en) |
-
2020
- 2020-12-14 CN CN202022982877.9U patent/CN214145679U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102068390B1 (en) | Supercharger and method for cooling electric motor | |
| CN103140651B (en) | System for pressurising the bearing chambers of turbine engines machines using air taken from the intake duct | |
| EA015281B1 (en) | Gas turbine plant | |
| CN102007273A (en) | A rotary piston internal combustion engine cooling arrangement | |
| CN112473189B (en) | Aircraft engine and centrifugal axis oil-gas separation device and method thereof | |
| CN209800100U (en) | sealing system for reducing oil leakage | |
| JP2017008937A (en) | Gas turbine engine | |
| CN112065586B (en) | Engine circulating lubrication oil way structure and engine rotating device | |
| CN214145679U (en) | Cooling device for high-temperature exhaust of gas turbine compressor | |
| CN210829503U (en) | Air supercharging system for reducing leakage of gas turbine lubricating oil | |
| RU177740U1 (en) | GAS-TURBINE ENGINE SUPPORT ASSEMBLY | |
| CN201650444U (en) | Turbocharger | |
| US10641174B2 (en) | Rotor shaft cooling | |
| CN108019243A (en) | A kind of integral bearing A seating turbine | |
| CN114458451B (en) | Multiphase flow bearing cooling device of micro turbojet engine | |
| CN216477580U (en) | Gas turbine's bearing frame assembly and two oil jet lubricating arrangement thereof | |
| CN205936713U (en) | Turbocharger bearing casing | |
| RU2448294C1 (en) | Reduction gear unit with shaft sealing system | |
| CN111396197A (en) | Air separator of gas turbine | |
| CN204458018U (en) | A kind of vehicle turbocharger | |
| CN212003353U (en) | Air separator of gas turbine | |
| CN111963484A (en) | High-integration-level diffuser structure for small turbine engine | |
| CN207297103U (en) | The circulating oil system of organic Rankine bottoming cycle twin-screw expander | |
| CN2929194Y (en) | Small turbocharger with mixed flow turbine and water cooling bearing | |
| CN219366170U (en) | Lubricating oil system of gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |