CN210829503U - Air supercharging system for reducing leakage of gas turbine lubricating oil - Google Patents
Air supercharging system for reducing leakage of gas turbine lubricating oil Download PDFInfo
- Publication number
- CN210829503U CN210829503U CN201920751253.0U CN201920751253U CN210829503U CN 210829503 U CN210829503 U CN 210829503U CN 201920751253 U CN201920751253 U CN 201920751253U CN 210829503 U CN210829503 U CN 210829503U
- Authority
- CN
- China
- Prior art keywords
- air
- gas turbine
- lubricating oil
- cavity
- main bearing
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
An air pressurization system for reducing the leakage of lubricating oil of a gas turbine relates to the technical field of gas turbines and aims to solve the problems that the lubricating oil temperature is too high, the lubricating oil is deteriorated and coked, a main bearing cannot be protected and a lubricating system cannot normally work when the lubricating oil of the existing gas turbine is leaked, the oil consumption is large and serious; the air outlet end of the air storage tank is communicated with the air inlet end of the valve group; the gas outlet end of the valve group is communicated with a sealed air cavity gas supply pipe of the gas turbine, the valve group comprises a throttling element and a control element which are connected in series, and the throttling element is a pressure reducing valve; the utility model is used for prevent among the gas turbine that the lubricating oil from leaking.
Description
Technical Field
The utility model relates to a gas turbine technical field especially relates to the antiskid oil leakage technique.
Background
Since the seventies of the twentieth century, the gas turbine has the characteristics of small volume, high power density, quick start, convenient maintenance and the like due to the superior performance of the gas turbine, and is widely applied to the fields of industrial peak shaving power generation, compressed natural gas conveying pipelines, offshore platforms, fuel-steam combined cycle power stations and the like.
No matter the gas turbine is used for mechanical driving or power generation, the gas turbine consists of a gas compressor, a combustion chamber, a turbine and an auxiliary system, and can be regarded as a high-speed power rotating machine, wherein air is continuously compressed in the gas compressor, flows into the combustion chamber for heating, continuously generates gas with certain pressure and temperature, then flows into the turbine for expansion and work, and converts part of heat energy into mechanical energy; any single rotor rotating at high speed is supported by at least 2 main bearings so as to keep the rotor rotating at high speed in a normal working state, and a large amount of heat is generated when the main bearings work and is taken away by adopting a method of lubricating by spraying lubricating oil; reliable operation of the gas turbine is therefore highly dependent on the quality of the lubrication system.
The lubricating system is used for pumping lubricating oil to the working surfaces of the main bearing and the meshing gear by the lubricating oil supply pump, taking away friction heat generated under high-speed rotation and heat transferred by surrounding high-temperature parts to maintain the normal temperature state of the main bearing and the meshing gear, and forming a continuous oil film between a roller path and a roller of the main bearing and between meshed gear surfaces so as to play a role in liquid lubrication; at the same time, there is always a certain amount of oil consumed; the main routes for gas turbine oil consumption are: 1) leakage through the bearing cavity oil seals; 2) heat loss of the oil; 3) loss of oil in the main bearing cavity to atmosphere with an oil plenum. The main research content of the application aims at the lubricating oil leakage caused by the imprecise sealing device;
in 2015, 12, 9, chinese patent invention CN 105143610B entitled "method and system for preventing leakage of lubricating oil in gas turbine" was disclosed, in which, when the gas turbine engine was running, sufficient compressed air was supplied to the oil pan housed by the turbine bearing by using a compressed air source to pressurize the oil chamber; operating the gas turbine engine by supplying compressed air from an external compressed air source if the pressure supplied from the compressed air source on the engine is insufficient in some operating conditions of the gas turbine engine, but controlling the gas turbine engine; however, the patent only proposes a working method of adding an auxiliary compressed air source, and does not disclose the specific structure of the compressed air system.
The lubricating oil sealing device of the existing gas turbine bearing cavity comprises: the gas turbine engine comprises a pressurization bleed air system 20, a lubricating oil seal 3 of a main bearing cavity, an air seal 2 for sealing an air cavity and the like, wherein in order to ensure that the gas turbine reliably operates under the whole operating condition, a two-stage sealing structure is adopted, so that two cavities of a main bearing cavity 7 and a sealed air cavity 5 are formed;
the main bearing cavity 7 is formed by a lubricating oil seal 3, a main bearing cavity wall 6, a main bearing cavity vent pipe 8, a lubricating oil supply pipe 9, a main bearing 10 and a main bearing cavity oil discharge pipe 13;
the main bearing cavity wall 6 is the peripheral wall of the main bearing cavity 7, a plurality of lubricating oil seals 3 are arranged on the main bearing cavity wall 6 for sealing,
the main bearing cavity vent pipe 8 penetrates through the main bearing cavity wall 6, so that the main bearing cavity 7 is communicated with the external space,
two lubricating oil supply pipes 9 penetrate the main bearing cavity wall 6, so that the main bearing cavity 7 is communicated with the external space,
a main bearing 10 is arranged in the main bearing cavity 7,
the main bearing cavity oil discharge pipe 13 is used for discharging dirty oil in the main bearing cavity 7;
the sealed air cavity 5 is formed by an air seal 2, a sealed air cavity wall 4, a sealed air cavity air supply pipe 11, a sealed air cavity oil discharge pipe 12 and an airflow flow path 14;
the sealed air cavity wall 4 is a peripheral wall of the sealed air cavity 5, a plurality of air seals 2 are arranged on the sealed air cavity wall 4 for sealing,
the sealed air cavity air supply pipe 11 penetrates through the sealed air cavity wall 4, so that the sealed air cavity 5 is communicated with the air flow channel 14,
the sealed air cavity oil discharge pipe 12 is used for discharging dirty oil in the sealed air cavity 5;
the pressurized bleed air system 20 is a system for extracting compressed air from a compressor interstage bleed air chamber 21 of a gas turbine and passing the extracted compressed air into the sealed air chamber air supply pipe 11 through an air flow passage 22,
since the pressure of the air provided from the boosted bleed air system 20 varies with the operating conditions of the gas turbine, the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 and the airflow path 14 also varies with the operating conditions; however, when the gas turbine is operated under low working conditions such as starting, slow turning, transition state and shutdown, the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 is lower than a design allowable value, so that the lubricating oil or oil-gas mixture in the main bearing cavity 7 flows to the sealed air cavity 5 along the lubricating oil seal 3 and leaks, and the consumption of the lubricating oil is increased; in severe cases, when the pressure of the high-temperature gas in the gas flow path 14 is higher, the high-temperature gas flows into the main bearing cavity 7 through the air seal 2 and the oil seal, and the oil temperature is too high, and the oil is deteriorated and coked.
The existing pressurized bleed air system 20 for preventing leakage of gas turbine oil therefore has the following problems:
1. when the gas turbine operates under the lower working conditions of starting, slow running, transition state, shutdown and the like, the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 is lower than a design allowable value, so that lubricating oil leakage is caused, the oil consumption is increased, and the phenomena of overhigh temperature, deterioration, coking and the like of the lubricating oil are caused under the severe condition;
2. the leakage of the lubricating oil causes that the main bearing can not be protected and the lubricating system can not work normally.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the problems that the sealing device and the pressure boosting and air entraining system 20 of the existing gas turbine can not ensure the stability of the pressure values in the sealed air cavity 5 and the main bearing cavity 7, which causes the leakage of lubricating oil, leads to large oil consumption and causes the excessive temperature, deterioration and coking of the lubricating oil under severe conditions; and the main bearing can not be protected, and the lubricating system can not work normally.
In order to solve the problems, the technical scheme is as follows:
the air supercharging system for reducing the leakage of the gas turbine lubricating oil comprises an air compressor 19, an air storage tank 18 and a valve group,
the air intake end of the air compressor 19 communicates with the external space,
the air outlet end of the air compressor 19 is communicated with the air inlet end of the air storage tank 18;
the air outlet end of the air storage tank 18 is communicated with the air inlet end of the valve group;
the air outlet end of the valve group is communicated with a sealed air cavity air supply pipe 11 of the gas turbine,
the valve set includes a throttling element and a control element connected in series with each other,
the throttling element is a pressure reducing valve 17;
the application has the following advantages:
1. when the gas turbine runs, the control system sends an instruction of opening a valve group, a newly-added air pressurization system is directly started, compressed air in the air storage tank enters the sealed air cavity 5 after passing through the valve group, the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 is ensured to be within a design allowable value range, lubricating oil leakage in the main bearing cavity 7 can be greatly reduced, and the inflow of high-temperature gas in the airflow flow path 14 can be isolated;
2. the main bearing is effectively protected, the lubricating system can normally work, and the running cost of the system is reduced.
Drawings
FIG. 1 is a block diagram of an air charging system as applied to a gas turbine;
FIG. 2 is a structural view of a conventional oil seal device body for a bearing cavity of a gas turbine;
FIG. 3 is a block diagram of a prior art oil seal body and an enlarged pressurized bleed air system;
FIG. 4 is a block diagram of a gas turbine bearing cavity;
in the figure: 1. a rotating shaft; 2. sealing the air; 3. sealing with lubricating oil; 4. sealing the air cavity wall; 5. sealing the air cavity; 6. the main bearing cavity wall; 7. a main bearing cavity; 8. a main bearing cavity exhaust pipe; 9. a lubricating oil supply pipe; 10. a main bearing; 11. sealing the air cavity air supply pipe; 12. sealing the air cavity oil discharge pipe; 13. an oil discharge pipe of the main bearing cavity; 14. an airflow path; 15. an oil-gas separator; 16. adjusting a valve; 17. a pressure reducing valve; 18. a gas storage tank; 19. an air compressor; 20. a pressurized bleed air system; 21. an interstage bleed air cavity; 22. an air flow passage.
Detailed Description
It should be understood that although exemplary implementations of embodiments of the present invention are described in detail below, the disclosed compositions may be implemented using any other suitable technology, whether currently known or not in existence. Therefore, the present invention should in no way be limited to the exemplary embodiments described below, but may be modified as appropriate within the scope of the appended claims and their equivalents. The present invention will now be described more fully with reference to the accompanying drawings, in which exemplary embodiments of the invention are shown. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the invention to those skilled in the art.
Description of the preferred embodimentthe present embodiment will now be described with reference to fig. 1-4, which provides an air charging system that reduces leakage of gas turbine oil,
comprises an air compressor 19, an air storage tank 18 and a valve group,
the air intake end of the air compressor 19 communicates with the external space,
the air outlet end of the air compressor 19 is communicated with the air inlet end of the air storage tank 18;
the air outlet end of the air storage tank 18 is communicated with the air inlet end of the valve group;
the air outlet end of the valve group is communicated with a sealed air cavity air supply pipe 11 of the gas turbine,
the valve set includes a throttling element and a control element connected in series with each other,
the throttling element is a pressure reducing valve 17;
the pressure in the reservoir 18 is within the norm;
when the pressure of the compressed air in the air storage tank 18 is reduced to a lower pressure limit value, the air compressor 19 automatically supplies air to the air storage tank 18;
when the pressure of the compressed air in the air tank 18 rises to the upper limit value of the pressure, the air compressor 19 is automatically stopped;
the valve group comprises a throttling element and a control element which are connected in series, and the air outlet end of the control element is communicated with the air inlet end of the throttling element;
the control element is a regulating valve 16;
the air outlet end of the air storage tank 18 is communicated with the air inlet end of the regulating valve 16, and the air outlet end of the regulating valve 16 is communicated with the air inlet end of the pressure reducing valve 17;
the air outlet end of the pressure reducing valve 17 is communicated with a sealed air cavity air supply pipe 11 of the gas turbine;
the structural schematic diagram of the air supercharging system applied to the gas turbine is shown in FIG. 1;
the working method comprises the following steps:
the system comprises an air compressor 19, an air storage tank 18, a pressure reducing valve 17 and a regulating valve 16;
when the gas turbine runs, the control system sends out an instruction of opening the regulating valve 16, starts the newly-added air pressurization system,
compressed air in the air storage tank 18 enters the sealed air cavity 5 after passing through the regulating valve 16 and the pressure reducing valve 17, so that the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 is ensured to be within a design allowable value range, and the inflow of high-temperature gas on the air flow path 14 is isolated; the air in the air storage tank 18 is automatically supplemented by an air compressor 19 and is kept within a set pressure value range; when the pressure of the compressed air in the air storage tank 18 is reduced to a lower pressure limit value, the air compressor 19 automatically supplies air; when the pressure of the compressed air in the air tank 18 rises to the upper limit value of the pressure, the air compressor 19 is automatically stopped;
when the gas turbine runs, the newly-added air pressurization system provides compressed air for the sealed air cavity 5, so that the phenomena of overhigh temperature, deterioration, coking and the like of lubricating oil are avoided, the consumption of the lubricating oil of the gas turbine can be reduced, and the running cost of the gas turbine can be saved;
the working process and principle are as follows:
the structural schematic diagram of the lubricating oil sealing device body of the prior gas turbine bearing cavity is shown in FIG. 2; a pressurized bleed air system 20 is provided,
a schematic diagram of a prior art booster bleed air system 20 is shown in figure 3;
the pressurization bleed air system 20 is a system which extracts compressed air from a compressor interstage bleed air cavity 21 of the gas turbine and leads the compressed air into the sealed air cavity air supply pipe 11 through an air flow passage 22;
when the existing gas turbine system operates under low working conditions such as starting, slow running, transition state and shutdown, the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 of the existing device is lower than the design allowable value range, so that lubricating oil or oil-gas mixture in the main bearing cavity 7 leaks to the sealed air cavity 5 along the lubricating oil seal 3, and the consumption of the lubricating oil is increased; in severe cases, when the pressure of the high-temperature gas in the airflow path 14 is higher, the high-temperature gas flows into the main bearing cavity 7 through the air seal 2 and the oil seal 3, which causes the phenomena of excessive oil temperature, deterioration, coking and the like,
and the schematic diagram of the bearing cavity structure is shown in fig. 4, the gas turbine bearing cavity adopts a two-stage sealing structure to form two cavities of a sealed air cavity 5 and a main bearing cavity 7,
the sealed air cavity 5 comprises an air seal 2, a sealed air cavity wall 4, a sealed air cavity air supply pipe 11, a sealed air cavity oil discharge pipe 12 and an air flow passage 14,
the main bearing cavity 7 comprises a lubricating oil seal 3, a main bearing cavity wall 6, a main bearing cavity vent pipe 8, a lubricating oil supply pipe 9, a main bearing 10 and a main bearing cavity oil discharge pipe 13;
the air charging system of the present embodiment with optimized design is schematically shown in figure 1,
the air pressurization system comprises a regulating valve 16, a pressure reducing valve 17, an air storage tank 18 and an air compressor 19, and the connecting structure is as described above; the sealing air cavity 5 of the gas turbine is not extracted from the compressor interstage bleed air cavity 21, but is provided by an air pressurization system,
the pressure within the reservoir 18 is within specification,
when the pressure of the compressed air in the air storage tank 18 is reduced to the lower limit value of the pressure, the air compressor 19 automatically supplies air to the air storage tank 18,
when the pressure of the compressed air in the air tank 18 rises to the upper limit value of the pressure, the air compressor 19 is automatically stopped,
the gas turbine main bearing cavity 7 adopts a lubricating oil seal 3 and an air seal 2, the lubricating oil seal 3 seals and seals air in the air cavity 5, air leaked from the lubricating oil seal 3, evaporation of the lubricating oil and heating of the air by splashed lubricating oil and environment form an oil-gas mixture which enters an oil-gas separator 15 of a ventilation system through a main bearing cavity exhaust pipe 8, and oil-gas separation and ventilation of the gas turbine main bearing cavity 7 are realized;
the air seal 2 separates the high-temperature gas in the airflow flow path 14 and prevents the high-temperature gas in the airflow flow path 14 from entering the main bearing cavity 7;
when the gas turbine runs, the control system sends an instruction of opening the regulating valve 16, a newly-added air pressurization system is directly started, compressed air in the air storage tank 18 enters the sealed air cavity 5 after passing through the regulating valve 16 and the pressure reducing valve 17, the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 is ensured to be within a design allowable value range, lubricating oil leakage in the main bearing cavity 7 can be greatly reduced, and the inflow of high-temperature gas in the airflow flow path 14 can be isolated;
the air in the air storage tank 18 is automatically supplemented by the air compressor 19, and is kept within the set pressure value range,
when the pressure of the compressed air in the air storage tank 18 is reduced to the lower limit value of the pressure, the air compressor 19 automatically supplies air,
when the pressure of the compressed air in the air tank 18 rises to the upper limit value of the pressure, the air compressor 19 is automatically stopped;
the air supercharging system of the embodiment can effectively reduce the leakage of the lubricating oil during the operation of the gas turbine;
therefore, the improved air pressurization system can effectively ensure that the pressure in the air storage tank 18 is in a preset standard pressure value range, so that the pressure difference between the sealed air cavity 5 and the main bearing cavity 7 is ensured to be in an allowable value range, and the phenomenon of lubricating oil leakage generated during the operation of the gas turbine can be effectively reduced;
the arrows in fig. 1 and 2 indicate the flow direction of the oil, the air-fuel mixture and the air.
Therefore, the present invention should in no way be limited to the specific embodiments described hereinabove, but may be modified as appropriate within the scope of the appended claims and their equivalents;
of course, the above description is not intended to limit the present invention, and the present invention is not limited to the above examples, and the changes, modifications, additions or replacements made by those skilled in the art within the scope of the present invention also belong to the protection scope of the present invention.
Claims (2)
1. Reduce air supercharging system that gas turbine lubricating oil leaked, its characterized in that: comprises an air compressor (19), an air storage tank (18) and a valve group,
the air inlet end of the air compressor (19) is communicated with the external space,
the air outlet end of the air compressor (19) is communicated with the air inlet end of the air storage tank (18);
the air outlet end of the air storage tank (18) is communicated with the air inlet end of the valve group;
the air outlet end of the valve group is communicated with a sealed air cavity air supply pipe (11) of the gas turbine,
the valve set includes a throttling element and a control element connected in series with each other,
the throttling element is a pressure reducing valve (17);
the control element is a regulating valve (16).
2. The air supercharging system for reducing leakage of gas turbine oil according to claim 1, wherein: the air outlet end of the air storage tank (18) is communicated with the air inlet end of the regulating valve (16),
the air outlet end of the pressure reducing valve (17) is communicated with a sealed air cavity air supply pipe (11) of the gas turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920751253.0U CN210829503U (en) | 2019-05-23 | 2019-05-23 | Air supercharging system for reducing leakage of gas turbine lubricating oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920751253.0U CN210829503U (en) | 2019-05-23 | 2019-05-23 | Air supercharging system for reducing leakage of gas turbine lubricating oil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210829503U true CN210829503U (en) | 2020-06-23 |
Family
ID=71269816
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920751253.0U Active CN210829503U (en) | 2019-05-23 | 2019-05-23 | Air supercharging system for reducing leakage of gas turbine lubricating oil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210829503U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109989830A (en) * | 2019-05-23 | 2019-07-09 | 中国船舶重工集团公司第七0三研究所 | Reduce the supercharging air system of turbine oil leakage |
| CN112228223A (en) * | 2020-10-14 | 2021-01-15 | 上海尚实能源科技有限公司 | High-power gas turbine engine |
-
2019
- 2019-05-23 CN CN201920751253.0U patent/CN210829503U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109989830A (en) * | 2019-05-23 | 2019-07-09 | 中国船舶重工集团公司第七0三研究所 | Reduce the supercharging air system of turbine oil leakage |
| CN112228223A (en) * | 2020-10-14 | 2021-01-15 | 上海尚实能源科技有限公司 | High-power gas turbine engine |
| CN112228223B (en) * | 2020-10-14 | 2021-04-13 | 上海尚实能源科技有限公司 | High-power gas turbine engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN209800100U (en) | sealing system for reducing oil leakage | |
| RU2661123C2 (en) | Methods and systems for preventing lubricating oil leakage in gas turbines | |
| US7836675B2 (en) | Supercore sump vent pressure control | |
| US20190234558A1 (en) | Leak-proof lubrication system for a power device | |
| CN103140651A (en) | System for pressurising the bearing chambers of turbine engines machines using air taken from the intake duct | |
| CN210829503U (en) | Air supercharging system for reducing leakage of gas turbine lubricating oil | |
| CN111911415B (en) | Nuclear power plant is with emergent moisturizing diesel engine pump package of primary circuit and system | |
| CN110056431A (en) | Reduce the sealing system of lubrication leakage | |
| CN107869364B (en) | Turbocharger bearing body assembly | |
| US11965510B2 (en) | Compressor body and compressor to supply liquid into working chambers and whose downstream portion reaches a suction bearing chamber | |
| CN201568738U (en) | Expander seal gas recycle device | |
| CN104093941B (en) | Self adaption ejector system | |
| CN108019243A (en) | A kind of integral bearing A seating turbine | |
| CN104989531A (en) | Ventilation system for bearing cavities | |
| US8539936B2 (en) | Supercharger rotor shaft seal pressure equalization | |
| CN203175624U (en) | Novel airtight type oil baffle | |
| CN109989830A (en) | Reduce the supercharging air system of turbine oil leakage | |
| CN115507034B (en) | Lubricating oil circulation system of oil injection screw compressor | |
| US9097180B2 (en) | Apparatus and method for reducing oil mist ingestion in a heavy duty gas turbine engine | |
| CN217300909U (en) | Air seal type screw compressor | |
| RU90505U1 (en) | GAS BOILER INSTALLATION OF A GAS COMPRESSOR STATION OF A MAIN GAS PIPELINE | |
| CN2208627Y (en) | Air film floating ring shaft seal for gas compressor | |
| CN208578591U (en) | A kind of gland seal system improving starting efficiency | |
| CN104819050A (en) | Turbo intelligent protector and protection method | |
| CN204591468U (en) | A kind of turbosupercharger intellective protector |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |