CN216050703U - Compressed air system for gas turbine test bed - Google Patents
Compressed air system for gas turbine test bed Download PDFInfo
- Publication number
- CN216050703U CN216050703U CN202121909629.XU CN202121909629U CN216050703U CN 216050703 U CN216050703 U CN 216050703U CN 202121909629 U CN202121909629 U CN 202121909629U CN 216050703 U CN216050703 U CN 216050703U
- Authority
- CN
- China
- Prior art keywords
- branch pipe
- pipeline
- valve
- air
- gas turbine
- 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
- Testing Of Engines (AREA)
Abstract
The utility model relates to the technical field of gas turbines, in particular to a compressed air system for a gas turbine test bed, wherein a main valve is arranged on a pipeline of a main pipe, an air outlet of a compressed air tank is communicated with an air inlet of the main pipe, the air outlet of the main pipe is divided into four paths which are respectively communicated with air inlets of a first branch pipe, a second branch pipe, a third branch pipe and a standby branch pipe, the air outlet of the first branch pipe is communicated with an air interface of a salt spray device of the gas turbine, a first stop valve and a first pressure reducing valve are arranged on the pipeline of the first branch pipe, the air outlet of the second branch pipe is communicated with an air interface of a ventilation baffle of the gas turbine, a second stop valve and a second pressure reducing valve are arranged on the pipeline of the second branch pipe, the air outlet of the third branch pipe is communicated with an air interface of a deflation valve of the gas turbine, a third stop valve and a third stop valve are arranged on the pipeline of the third branch pipe, and a fourth stop valve and a fourth pressure reducing valve are arranged on the pipeline of the standby pressure reducing valve, the application has reasonable design and easy operation, and can meet the requirement of the gas turbine on compressed air.
Description
Technical Field
The utility model relates to the technical field of gas turbines, in particular to a compressed air system for a gas turbine test bed.
Background
When the gas turbine is started, the fuel combustion needs compressed air to provide atomization; after the start is successful, compressed air is needed to control the opening of the anti-surge air release valve; in the test process, a salt spray system which takes compressed air as an injection power source to simulate the marine environment needs to be added. This requires the deployment of a complete compressed air system.
SUMMERY OF THE UTILITY MODEL
The applicant aims at the defects in the prior art and provides a compressed air system for a gas turbine test bed, which is reasonable in design and easy to operate and can meet the requirement of a gas turbine on compressed air.
The technical scheme adopted by the utility model is as follows: a compressed air system for a gas turbine test bed comprises a compressed air tank, a header pipe, a main valve, a first branch pipe, a second branch pipe, a third branch pipe and a standby branch pipe, wherein the main valve is arranged on a pipeline of the header pipe, an air outlet of the compressed air tank is communicated with an air inlet of the header pipe, the air outlet of the header pipe is divided into four paths which are respectively communicated with air inlets of the first branch pipe, the second branch pipe, the third branch pipe and the standby branch pipe, an air outlet of the first branch pipe is communicated with an air interface of a salt spray device of the gas turbine, a first stop valve and a first pressure reducing valve are arranged on the pipeline of the first branch pipe, an air outlet of the second branch pipe is communicated with an air interface of a ventilation baffle of the gas turbine, a second stop valve and a second pressure reducing valve are arranged on the pipeline of the second branch pipe, an air outlet of the third branch pipe is communicated with an air interface of a deflation valve of the gas turbine, and a third stop valve and a third pressure reducing valve are arranged on the pipeline of the third branch pipe, and a fourth stop valve and a fourth pressure reducing valve are arranged on the pipeline of the standby branch pipe.
As a further improvement of the above technical solution:
the pipeline of the first branch pipe is provided with a first reducing joint, and the first reducing joint, the first stop valve and the first pressure reducing valve are sequentially arranged along the direction from the air inlet to the air outlet of the first branch pipe.
And a second reducing joint is arranged on a pipeline of the second branch pipe, and the second reducing joint, the second stop valve and the second pressure reducing valve are sequentially arranged along the direction from the air inlet to the air outlet of the second branch pipe.
And a third different-diameter joint, a third stop valve and a third pressure reducing valve are sequentially arranged along the direction from the air inlet to the air outlet of the third branch pipe.
And a fourth reducing joint is arranged on a pipeline of the standby branch pipe, and the fourth reducing joint, the fourth stop valve and the fourth reducing valve are sequentially arranged along the direction from the air inlet to the air outlet of the standby branch pipe.
The pipeline of the main pipe between the main valve and the main pipe gas outlet is provided with a total pressure transmitter, the pipeline of the first branch pipe between the first pressure reducing valve and the first branch pipe gas outlet is provided with a first pressure transmitter, the pipeline of the second branch pipe between the second pressure reducing valve and the second branch pipe gas outlet is provided with a second pressure transmitter, the pipeline of the third branch pipe between the third pressure reducing valve and the third branch pipe gas outlet is provided with a third pressure transmitter, and the pipeline of the standby branch pipe between the fourth pressure reducing valve and the standby branch pipe gas outlet is provided with a fourth pressure transmitter.
The utility model has the following beneficial effects: the used compressed air system of this application has realized gas turbine to compressed air's demand, and this system control function is comprehensive, reasonable in design, easy operation, has satisfied gas turbine to the compressed air's of the different atmospheric pressure of stranded demand. This application can be to each pipeline pressure real-time measurement, the operator real-time supervision of being convenient for, and gas turbine during operation, when pressure is not conform to the requirement, but in time discovery and processing maintain gas turbine's steady operation.
Drawings
FIG. 1 is a flow chart of an embodiment of the present invention.
Wherein: 11. a compressed air tank; 12. a header pipe; 13. a main valve; 14. a total pressure transmitter; 21. a first branch pipe; 22. a first shut-off valve; 23. a first pressure reducing valve; 24. a first reducing joint; 25. a first pressure transmitter; 31. a second branch pipe; 32. a second stop valve; 33. a second pressure reducing valve; 34. a second reducing joint; 35. a second pressure transmitter; 41. a third branch pipe; 42. a third stop valve; 43. a third pressure reducing valve; 44. a third differential joint; 45. a third pressure transmitter; 51. a standby branch pipe; 52. a fourth stop valve; 53. a fourth pressure reducing valve; 54. a fourth reducing joint; 55. and a fourth pressure transmitter.
Detailed Description
The following describes embodiments of the present invention with reference to the drawings.
As shown in fig. 1, the compressed air system for a gas turbine test bed of the present embodiment includes a compressed air tank 11, a main pipe 12, a main valve 13, a first branch pipe 21, a second branch pipe 31, a third branch pipe 41 and a spare branch pipe 51, the main valve 13 is disposed on a pipeline of the main pipe 12, an air outlet of the compressed air tank 11 is communicated with an air inlet of the main pipe 12, an air outlet of the main pipe 12 is divided into four paths to be respectively communicated with air inlets of the first branch pipe 21, the second branch pipe 31, the third branch pipe 41 and the spare branch pipe 51, an air outlet of the first branch pipe 21 is communicated with an air inlet of a salt spray device of the gas turbine, a first stop valve 22 and a first pressure reducing valve 23 are disposed on a pipeline of the first branch pipe 21, an air outlet of the second branch pipe 31 is communicated with an air inlet of a ventilation damper of the gas turbine, a second stop valve 32 and a second pressure reducing valve 33 are disposed on a pipeline of the second branch pipe 31, an air outlet of the third branch pipe 41 is communicated with an air inlet of a gas release valve of the gas turbine, a third stop valve 42 and a third pressure reducing valve 43 are provided in the pipe of the third branch pipe 41, and a fourth stop valve 52 and a fourth pressure reducing valve 53 are provided in the pipe of the backup branch pipe 51.
The pipeline of the first branch pipe 21 is provided with a first reducing joint 24, and the first reducing joint 24, a first stop valve 22 and a first pressure reducing valve 23 are sequentially arranged along the direction from the air inlet to the air outlet of the first branch pipe 21.
A second reducing joint 34 is arranged on the pipeline of the second branch pipe 31, and the second reducing joint 34, the second stop valve 32 and the second pressure reducing valve 33 are sequentially arranged along the direction from the air inlet to the air outlet of the second branch pipe 31.
A third differential joint 44 is provided on the piping of the third branch pipe 41, and the third differential joint 44, the third stop valve 42 and the third pressure reducing valve 43 are arranged in this order along the gas inlet to gas outlet direction of the third branch pipe 41.
A fourth reducing joint 54 is arranged on the pipeline of the spare branch pipe 51, and the fourth reducing joint 54, the fourth stop valve 52 and the fourth reducing valve 53 are sequentially arranged along the direction from the air inlet to the air outlet of the spare branch pipe 51.
A total pressure transmitter 14 is arranged on a pipeline of the main pipe 12 between the main valve 13 and an air outlet of the main pipe 12, a first pressure transmitter 25 is arranged on a pipeline of the first branch pipe 21 between the first pressure reducing valve 23 and an air outlet of the first branch pipe 21, a second pressure transmitter 35 is arranged on a pipeline of the second branch pipe 31 between the second pressure reducing valve 33 and an air outlet of the second branch pipe 31, a third pressure transmitter 45 is arranged on a pipeline of the third branch pipe 41 between the third pressure reducing valve 43 and an air outlet of the third branch pipe 41, and a fourth pressure transmitter 55 is arranged on a pipeline of the standby branch pipe 51 between the fourth pressure reducing valve 53 and an air outlet of the standby branch pipe 51.
In actual operation, the following compressed air preparation is performed before the gas turbine is started.
Step 1: when the main valve 13 is opened, the compressed air in the compressed air tank 11 enters the main pipe 12, and the pressure measurement value of the main pipe 12 is transmitted to the gas turbine control system by the total pressure transmitter 14, so that the operator can observe the pressure measurement value conveniently;
step 2: opening a first stop valve 22, allowing compressed air in the main pipe 12 to enter a first branch pipe 21, adjusting a first pressure reducing valve 23 to adjust the air for the salt spray device at a specific pressure required by the gas turbine, and transmitting a measured value of the atomized air pressure to a gas turbine control system by a first pressure transmitter 25 for an operator to observe;
and step 3: the second stop valve 32 is opened, the compressed air in the main pipe 12 enters the second branch pipe 31, the ventilation baffle air with specific pressure required by the gas turbine is adjusted by adjusting the second reducing valve 33, and the second pressure transmitter 35 transmits the measured value of the ventilation baffle air pressure to the gas turbine control system, so that an operator can observe the measured value in real time conveniently;
and 4, step 4: the third stop valve 42 is opened, the compressed air in the main pipe 12 enters the third branch pipe 41, the air for the bleed valve at a specific pressure required by the gas turbine is adjusted by adjusting the third pressure reducing valve 43, and the third pressure transmitter 45 transmits the measured value of the air pressure for the bleed valve to the gas turbine control system, so that the operator can observe the measured value in real time.
In addition, the backup branch 51 serves as a backup line for salt spray device air, vent damper air, purge valve air, or other equipment air. When other branch pipes are damaged, the normal operation of the system can be ensured.
The used compressed air system of this application has realized gas turbine to compressed air's demand, and this system control function is comprehensive, reasonable in design, easy operation, has satisfied gas turbine to the compressed air's of the different atmospheric pressure of stranded demand. This application can be to each pipeline pressure real-time measurement, the operator real-time supervision of being convenient for, and gas turbine during operation, when pressure is not conform to the requirement, but in time discovery and processing maintain gas turbine's steady operation.
The above description is intended to illustrate the present invention and not to limit the present invention, which is defined by the scope of the claims, and may be modified in any manner within the scope of the present invention.
Claims (6)
1. The utility model provides a compressed air system for gas turbine test bench which characterized in that: comprises a compressed air tank (11), a main pipe (12), a main valve (13), a first branch pipe (21), a second branch pipe (31), a third branch pipe (41) and a standby branch pipe (51), wherein the main valve (13) is arranged on a pipeline of the main pipe (12), an air outlet of the compressed air tank (11) is communicated with an air inlet of the main pipe (12), an air outlet of the main pipe (12) is divided into four paths to be respectively communicated with air inlets of the first branch pipe (21), the second branch pipe (31), the third branch pipe (41) and the standby branch pipe (51), an air outlet of the first branch pipe (21) is communicated with an air interface of a salt spray device of a gas turbine, a first stop valve (22) and a first reducing valve (23) are arranged on a pipeline of the first branch pipe (21), an air outlet of the second branch pipe (31) is communicated with an air interface of a ventilation baffle of the gas turbine, a second stop valve (32) and a second reducing valve (33) are arranged on a pipeline of the second branch pipe (31), the air outlet of the third branch pipe (41) is communicated with an air interface for an air release valve of the gas turbine, a third stop valve (42) and a third pressure reducing valve (43) are arranged on the pipeline of the third branch pipe (41), and a fourth stop valve (52) and a fourth pressure reducing valve (53) are arranged on the pipeline of the standby branch pipe (51).
2. The compressed air system for a gas turbine test stand of claim 1, wherein: a first reducing joint (24) is arranged on a pipeline of the first branch pipe (21), and the first reducing joint (24), the first stop valve (22) and the first pressure reducing valve (23) are sequentially arranged along the direction from the air inlet to the air outlet of the first branch pipe (21).
3. The compressed air system for a gas turbine test stand according to claim 2, wherein: a second reducing joint (34) is arranged on a pipeline of the second branch pipe (31), and the second reducing joint (34), the second stop valve (32) and the second pressure reducing valve (33) are sequentially arranged along the direction from the air inlet to the air outlet of the second branch pipe (31).
4. The compressed air system for a gas turbine test stand of claim 3, wherein: and a third different-diameter joint (44) is arranged on the pipeline of the third branch pipe (41), and the third different-diameter joint (44), the third stop valve (42) and the third pressure reducing valve (43) are sequentially arranged along the direction from the air inlet to the air outlet of the third branch pipe (41).
5. The compressed air system for a gas turbine test stand according to claim 4, wherein: a fourth reducing joint (54) is arranged on a pipeline of the standby branch pipe (51), and the fourth reducing joint (54), a fourth stop valve (52) and a fourth reducing valve (53) are sequentially arranged along the direction from the air inlet to the air outlet of the standby branch pipe (51).
6. The compressed air system for a gas turbine test stand of claim 5, wherein: the pipeline of the main pipe (12) between the main valve (13) and the air outlet of the main pipe (12) is provided with a total pressure transmitter (14), the pipeline of the first branch pipe (21) between the first pressure reducing valve (23) and the air outlet of the first branch pipe (21) is provided with a first pressure transmitter (25), the pipeline of the second branch pipe (31) between the second pressure reducing valve (33) and the air outlet of the second branch pipe (31) is provided with a second pressure transmitter (35), the pipeline of the third branch pipe (41) between the third pressure reducing valve (43) and the air outlet of the third branch pipe (41) is provided with a third pressure transmitter (45), and the pipeline of the standby branch pipe (51) between the fourth pressure reducing valve (53) and the air outlet of the standby branch pipe (51) is provided with a fourth pressure transmitter (55).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121909629.XU CN216050703U (en) | 2021-08-13 | 2021-08-13 | Compressed air system for gas turbine test bed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121909629.XU CN216050703U (en) | 2021-08-13 | 2021-08-13 | Compressed air system for gas turbine test bed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216050703U true CN216050703U (en) | 2022-03-15 |
Family
ID=80558759
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121909629.XU Active CN216050703U (en) | 2021-08-13 | 2021-08-13 | Compressed air system for gas turbine test bed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216050703U (en) |
-
2021
- 2021-08-13 CN CN202121909629.XU patent/CN216050703U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111006840B (en) | Hypersonic wind tunnel vacuum pressure air inlet pressure regulating method | |
| CN201348557Y (en) | Air leakage rate field test apparatus for air conditioner | |
| CN102052143B (en) | Single cylinder diesel pressurization system simulator | |
| CN203758745U (en) | Engine plateau test simulation device employing intake-exhaust bypassing | |
| CN209606081U (en) | A kind of A320 aircraft engine HP Bleed Valve test device | |
| CN216050703U (en) | Compressed air system for gas turbine test bed | |
| CN111595574A (en) | Efficient pressure regulating box test board and test method thereof | |
| CN203321700U (en) | Fuel gas feeding device of gas engine | |
| CN209655043U (en) | A kind of low-pressure fuel gas pipeline minute leakage on-line monitoring system | |
| CN111076923A (en) | Continuous flow calibration system and method for high-temperature gas regulator | |
| CN109708004A (en) | A kind of low-pressure fuel gas pipeline minor leakage on-line monitoring system and method | |
| CN202582899U (en) | Crankcase ventilation system of diesel engine experimental station | |
| CN109459277B (en) | Constant-speed control box applied to portable coal dust sampling device and application method of constant-speed control box | |
| CN112780417B (en) | Gas turbine starting optimization control system and method applying nitrogen isolation | |
| CN105043780B (en) | A kind of discharged nitrous oxides measuring method of many booster diesel engines | |
| CN210511034U (en) | CNG gas storage well CNG recovery system | |
| CN204459773U (en) | Cutting gas air feeder | |
| CN103292878A (en) | Calibrating device for high-pressure natural gas flow meter | |
| CN209622483U (en) | Gas pressure regulator, governor debugging system | |
| CN219224149U (en) | Hydrogen injector performance test system | |
| CN112113737A (en) | Air supply and exhaust system capable of accurately controlling equipment pressure under interference condition | |
| CN201215252Y (en) | Stalk gas supply device | |
| CN216922454U (en) | Pressure simulation manual regulating device for parallel operation of multiple air compressors | |
| CN219416671U (en) | Device for durability test of cabin pressure regulating valve | |
| CN215862899U (en) | A diffuse pipe system for multistage gas pressure regulating system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |