CN211975318U - Air compressor applied to gas turbine - Google Patents
Air compressor applied to gas turbine Download PDFInfo
- Publication number
- CN211975318U CN211975318U CN202020347661.2U CN202020347661U CN211975318U CN 211975318 U CN211975318 U CN 211975318U CN 202020347661 U CN202020347661 U CN 202020347661U CN 211975318 U CN211975318 U CN 211975318U
- Authority
- CN
- China
- Prior art keywords
- stage
- iii
- air inlet
- chamber
- side wall
- 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
- Compressor (AREA)
Abstract
An air compressor applied to a gas turbine relates to the technical field of gas turbines. The utility model discloses a solve the problem that current air compressor's volume is great, compression efficiency is low. The utility model discloses an input nozzle stub, I, II th level piston, bent axle, III level piston, output tube connects and motor, and the motor drives the bent axle and rotates, and the bent axle drives I, II th level piston and III level piston respectively through two connecting rods and is straight reciprocating motion, and the air that the input nozzle stub got into passes through output tube joint after the twice compression of I, II th level piston and the third compression of III level piston and discharges. The utility model is used for gas turbine air compression.
Description
Technical Field
The utility model relates to a gas turbine technical field, concretely relates to be applied to gas turbine's air compressor.
Background
The functions of the gas turbine pneumatic control system comprise fuel atomization purging when the gas turbine is started, air release valve control for preventing the gas turbine from surging in the operation process of the gas turbine, and fuel purging of a first oil path and a second oil path when the gas turbine is stopped. To achieve the above function, high pressure compressed air needs to be supplied to the pneumatic control system. However, the existing air compressor has large volume and low air compression efficiency, and is difficult to meet the use requirement of the gas turbine.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve the problem that current air compressor's volume is great, compression efficiency is low, and then propose an air compressor who is applied to gas turbine.
The utility model discloses a solve the technical scheme that above-mentioned technical problem took and be:
an air compressor applied to a gas turbine comprises an input short pipe, an I, II th-stage piston, a crankshaft, a III-stage piston, an output pipe joint and a motor, wherein the motor drives the crankshaft to rotate, the crankshaft drives a I, II th-stage piston and the III-stage piston to do linear reciprocating motion through two connecting rods respectively, and air entering the input short pipe is discharged through the output pipe joint after being compressed twice by the I, II th-stage piston and compressed for the third time by the III-stage piston.
Compared with the prior art, the utility model the beneficial effect who contains is:
the utility model relates to an air compressor that boats and ships trade used belongs to energy power trade, concretely relates to strong tertiary piston double-stroke compressor guarantees to obtain high-pressure compressed air for gas turbine's fuel atomization, sweep and bleed valve control. The utility model provides a be applied to gas turbine's air compressor has compact structure, stable performance, reliable operation, high characteristics of security. The air release valve can ensure fuel atomization when the gas turbine is started, air purging when the gas turbine is stopped, improve surge margin in the operation process and ensure safe operation of the gas turbine.
Drawings
Fig. 1 is a cross-sectional view of the overall structure of the present invention.
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1, and the air compressor applied to the gas turbine in the embodiment includes an input short pipe 1, an I, II th stage piston 4, a crankshaft 9, a III stage piston 11, an output pipe joint 13 and a motor, where the motor drives the crankshaft 9 to rotate, the crankshaft 9 drives the I, II th stage piston 4 and the III stage piston 11 to make linear reciprocating motion through two connecting rods, respectively, and air entering the input short pipe 1 is discharged through the output pipe joint 13 after being compressed twice by the I, II th stage piston 4 and compressed for the third time by the III stage piston 11.
The second embodiment is as follows: the present embodiment is described with reference to fig. 1, and an air compressor applied to a gas turbine according to the present embodiment further includes a first intake valve 2, a first exhaust valve 3, a first bypass pipe 5, a second intake valve 6, a first link 7, a housing 8, a second link 10, a third exhaust valve 12, a third intake valve 14, a second bypass pipe 15, and a second exhaust valve 16,
the crankshaft 9 is arranged in the shell 8, the output shaft of the motor is connected with the crankshaft 9, one end of the first connecting rod 7 and one end of the second connecting rod 10 are respectively fixedly connected with the crankshaft 9,
the other end of the first connecting rod 7 is rotatably connected with an I, II th-stage piston 4, a I, II th-stage cylinder 17 is arranged on the outer side of the I, II th-stage piston 4, a first chamber a is arranged at the top end of the inner side of the I, II th-stage cylinder 17, a first air inlet valve 2 and a first exhaust valve 3 are respectively arranged on the first chamber a, the output end of an input short pipe 1 is connected with the air inlet end of the first air inlet valve 2, the exhaust end of the first air inlet valve 2 is connected with the first chamber a, the air inlet end of the first exhaust valve 3 is connected with the first chamber a, the input end of a first bypass pipe 5 is connected with the exhaust end of the first exhaust valve 3, a second chamber b is arranged in the middle of the I, II th-stage cylinder 17 along the circumferential direction, a second air inlet valve 6 and a second exhaust valve 16 are respectively arranged on the second chamber b, the output end of the first bypass pipe 5 is connected with the air inlet end of the second air inlet valve 6, the inlet end of the second exhaust valve 16 is connected to the second chamber b, the outlet end of the second exhaust valve 16 is connected to the input end of the second bypass pipe 15,
the other end of the second connecting rod 10 is rotatably connected with a stage III piston 11, a stage III cylinder 18 is arranged on the outer side of the stage III piston 11, a third chamber c is arranged in the middle of the stage III cylinder 18 along the circumferential direction, a third air inlet valve 14 and a third exhaust valve 12 are respectively arranged on the third chamber c, the output end of the second bypass pipe 15 is connected with the air inlet end of the third air inlet valve 14, the exhaust end of the third air inlet valve 14 is connected with the third chamber c, the air inlet end of the third exhaust valve 12 is connected with the third chamber c, and the exhaust end of the third exhaust valve 12 is connected with the input end of the output pipe joint 13. Other components and connection modes are the same as those of the first embodiment.
In the embodiment, a strong three-stage piston type double-stroke compressor is adopted, so that high-pressure compressed air is obtained. An output shaft of the motor drives the crankshaft 9 to rotate, and then the I, II th-stage piston 4 is driven by the first connecting rod 7, and the III-stage piston 11 is driven by the second connecting rod 10 to do linear reciprocating motion. When the I, II th stage piston 4 moves downward, decompression occurs in the first chamber a, and air from the atmosphere is drawn into the first chamber a through the input stub 1 and the first intake valve 2. When the I, II th stage piston 4 moves upward, air in the first chamber a is compressed and is expelled to the second chamber b through the first exhaust valve 3, the first bypass pipe 5 and the second intake valve 6 in sequence, and a 'charging' stroke occurs in the chamber, and the air compression process is finished.
When the I, II th stage piston 4 moves downward again, air is compressed in the second chamber b and is expelled into the third chamber c through the second exhaust valve 16, the second bypass tube 15 and the third intake valve 14 in sequence, whereupon the stage III piston 11 moves to the right in that chamber, completing the "charge" stroke and ending the air compression process.
When the stage III piston 11 moves to the left, the volume of the third chamber c decreases and the air is compressed. The compressed air is displaced via a third outlet valve 12 and an outlet connection 13 into the high-pressure air line.
Therefore, three-stage air compression is completed through the two pistons, the structure is compact, the compression efficiency is high, and high-pressure compressed air is guaranteed to be obtained.
The third concrete implementation mode: referring to fig. 1, the I, II-th stage cylinder 17 of the present embodiment is vertically fixed to the upper end of the casing 8, and the III-th stage cylinder 18 is horizontally fixed to one side of the casing 8. Other components and connection modes are the same as those of the second embodiment.
The fourth concrete implementation mode: referring to fig. 1, the I, II th-stage piston 4 is connected to the I, II th-stage cylinder 17 by sliding along the vertical direction, and the III-stage piston 11 is connected to the III-stage cylinder 18 by sliding along the horizontal direction. Other components and connection modes are the same as those of the third embodiment.
The fifth concrete implementation mode: referring to fig. 1, the first chamber a is disposed between the top end of the I, II th-stage piston 4 and the inner side wall of the I, II th-stage cylinder 17, the second chamber b is disposed between the outer circumferential side wall of the I, II th-stage piston 4 and the inner side wall of the I, II th-stage cylinder 17, and the third chamber c is disposed between the outer circumferential side wall of the III-stage piston 11 and the inner side wall of the III-stage cylinder 18. The other compositions and connection modes are the same as those of the second, third or fourth embodiment.
In this embodiment, the first chamber a is disposed between the top end surface of the I, II th stage piston 4, the inner circumferential side wall of the I, II th stage cylinder 17 and the top end surface of the inner side wall of the I, II th stage cylinder 17, the second chamber b is disposed in the middle of the I, II th stage cylinder 17, the inner circumferential side wall of the middle of the I, II th stage cylinder 17 is provided with an annular groove, the second chamber b is disposed between the annular groove and the outer circumferential side wall of the I, II th stage piston 4, the third chamber c is disposed in the middle of the III stage cylinder 18, the inner circumferential side wall of the III stage cylinder 18 is stepped, the inner circumferential side wall of the middle of the III stage cylinder 18 is provided with a flange, the inner diameter of the inner end of the III stage cylinder 18 is smaller than the inner diameter of the outer end, the outer circumferential side wall of the III stage piston 11 is stepped, the outer circumferential side wall of the middle of the III stage piston 11 is provided with a boss, the outer diameter of the inner, the outer circumferential side wall of the inner end of the III-stage piston 11 is matched with the inner circumferential side wall of the inner end of the III-stage cylinder 18, the outer circumferential side wall of the outer end of the III-stage piston 11 is matched with the inner circumferential side wall of the outer end of the III-stage cylinder 18, and the third chamber c is arranged between the end face of the flange, the end face of the boss, the outer circumferential side wall of the inner end of the III-stage piston 11 and the inner circumferential side wall of the outer end of the III-stage cylinder 18.
The sixth specific implementation mode: referring to fig. 1, the I, II th-stage piston 4 of the present embodiment is provided with a first sealing ring set at both ends, the first sealing ring set is disposed between the outer circumferential side wall of the I, II th-stage piston 4 and the inner circumferential side wall of the I, II th-stage cylinder 17, the III-stage piston 11 is provided with a second sealing ring set at both ends, and the second sealing ring set is disposed between the outer circumferential side wall of the III-stage piston 11 and the inner circumferential side wall of the III-stage cylinder 18. The other components and the connection mode are the same as the fifth embodiment mode.
The seventh embodiment: the present embodiment will be described with reference to fig. 1, in which the rotation center of the crankshaft 9 and the center of the housing 8 are eccentrically disposed. Other compositions and connection modes are the same as those of the second, third, fourth or sixth embodiment.
The specific implementation mode is eight: referring to fig. 1, the I, II th-stage piston 4 and the III-stage piston 11 of the present embodiment are both hollow. The other components and the connection mode are the same as those of the seventh embodiment.
The specific implementation method nine: referring to fig. 1, the I, II-th stage cylinder block 17 and the III-th stage cylinder block 18 of the present embodiment are provided with a plurality of heat dissipation fins on the outer sides thereof in the longitudinal direction, and each heat dissipation fin is provided in the circumferential direction. Other compositions and connection modes are the same as those of the second, third, fourth, sixth or eighth embodiment modes.
Although the invention herein has been described with reference to particular embodiments, it is to be understood that these embodiments are merely illustrative of the principles and applications of the present invention. It is therefore to be understood that numerous modifications may be made to the illustrative embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that features described in different dependent claims and herein may be combined in ways different from those described in the original claims. It is also to be understood that features described in connection with individual embodiments may be used in other described embodiments.
Claims (9)
1. An air compressor for a gas turbine, comprising: the air compressor applied to the gas turbine comprises an input short pipe (1), an I, II th-stage piston (4), a crankshaft (9), a III-stage piston (11), an output pipe joint (13) and a motor, wherein the motor drives the crankshaft (9) to rotate, the crankshaft (9) drives the I, II th-stage piston (4) and the III-stage piston (11) to do linear reciprocating motion through two connecting rods respectively, and air entering the input short pipe (1) is discharged through the output pipe joint (13) after being compressed twice by the I, II th-stage piston (4) and compressed for the third time by the III-stage piston (11).
2. The air compressor applied to a gas turbine according to claim 1, wherein: the air compressor applied to the gas turbine further comprises a first air inlet valve (2), a first exhaust valve (3), a first bypass pipe (5), a second air inlet valve (6), a first connecting rod (7), a shell (8), a second connecting rod (10), a third exhaust valve (12), a third air inlet valve (14), a second bypass pipe (15) and a second exhaust valve (16),
the crankshaft (9) is arranged in the shell (8), the output shaft of the motor is connected with the crankshaft (9), one end of the first connecting rod (7) and one end of the second connecting rod (10) are respectively fixedly connected with the crankshaft (9),
the other end of the first connecting rod (7) is rotatably connected with an I, II th-level piston (4), a I, II th-level cylinder body (17) is arranged on the outer side of the I, II th-level piston (4), a first chamber (a) is arranged at the top end of the inner side of the I, II th-level cylinder body (17), a first air inlet valve (2) and a first exhaust valve (3) are respectively arranged on the first chamber (a), the output end of an input short pipe (1) is connected with the air inlet end of the first air inlet valve (2), the exhaust end of the first air inlet valve (2) is connected with the first chamber (a), the air inlet end of the first exhaust valve (3) is connected with the first chamber (a), the input end of a first bypass pipe (5) is connected with the exhaust end of the first exhaust valve (3), a second chamber (b) is arranged in the middle of the I, II th-level cylinder body (17) along the circumferential direction, a second air inlet valve (6) and a second exhaust valve (16) are respectively arranged, the output end of the first bypass pipe (5) is connected with the air inlet end of the second air inlet valve (6), the air outlet end of the second air inlet valve (6) is connected with the second chamber (b), the air inlet end of the second exhaust valve (16) is connected with the second chamber (b), the air outlet end of the second exhaust valve (16) is connected with the input end of the second bypass pipe (15),
the other end of the second connecting rod (10) is rotatably connected with a third-stage piston (11), a third-stage cylinder body (18) is arranged on the outer side of the third-stage piston (11), a third chamber (c) is arranged in the middle of the third-stage cylinder body (18) in the circumferential direction, a third air inlet valve (14) and a third exhaust valve (12) are respectively arranged on the third chamber (c), the output end of a second bypass pipe (15) is connected with the air inlet end of the third air inlet valve (14), the exhaust end of the third air inlet valve (14) is connected with the third chamber (c), the air inlet end of the third exhaust valve (12) is connected with the third chamber (c), and the exhaust end of the third exhaust valve (12) is connected with the input end of an output pipe joint (13).
3. The air compressor applied to a gas turbine according to claim 2, wherein: the I, II th-stage cylinder body (17) is vertically and fixedly connected to the upper end of the shell (8), and the III-stage cylinder body (18) is horizontally and fixedly connected to one side of the shell (8).
4. An air compressor for a gas turbine according to claim 3, wherein: the I, II th-stage piston (4) has its outer circumferential side wall slidably connected to the inner circumferential side wall of the I, II th-stage cylinder (17) in the vertical direction, and the III-stage piston (11) has its outer circumferential side wall slidably connected to the inner circumferential side wall of the III-stage cylinder (18) in the horizontal direction.
5. An air compressor for a gas turbine according to claim 2, 3 or 4, wherein: the first chamber (a) is arranged between the top end of the I, II th-stage piston (4) and the inner side wall of the I, II th-stage cylinder (17), the second chamber (b) is arranged between the outer circumferential side wall of the I, II th-stage piston (4) and the inner side wall of the I, II th-stage cylinder (17), and the third chamber (c) is arranged between the outer circumferential side wall of the III-stage piston (11) and the inner side wall of the III-stage cylinder (18).
6. The air compressor applied to a gas turbine according to claim 5, wherein: the two ends of the I, II th-stage piston (4) are provided with first sealing ring sets, the first sealing ring sets are arranged between the outer circumferential side wall of the I, II th-stage piston (4) and the inner circumferential side wall of the I, II th-stage cylinder body (17), the two ends of the III-stage piston (11) are provided with second sealing ring sets, and the second sealing ring sets are arranged between the outer circumferential side wall of the III-stage piston (11) and the inner circumferential side wall of the III-stage cylinder body (18).
7. An air compressor for a gas turbine according to claim 2, 3, 4 or 6, wherein: the rotation center of the crankshaft (9) and the center of the shell (8) are eccentrically arranged.
8. The air compressor for a gas turbine according to claim 7, wherein: the I, II th-stage piston (4) and the III-stage piston (11) are both hollow structures.
9. An air compressor for a gas turbine according to claim 2, 3, 4, 6 or 8, wherein: the outer sides of the I, II th-stage cylinder body (17) and the III-stage cylinder body (18) are respectively provided with a plurality of radiating fins along the length direction, and each radiating fin is arranged along the circumferential direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020347661.2U CN211975318U (en) | 2020-03-12 | 2020-03-12 | Air compressor applied to gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020347661.2U CN211975318U (en) | 2020-03-12 | 2020-03-12 | Air compressor applied to gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211975318U true CN211975318U (en) | 2020-11-20 |
Family
ID=73394508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020347661.2U Active CN211975318U (en) | 2020-03-12 | 2020-03-12 | Air compressor applied to gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211975318U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113471487A (en) * | 2021-06-30 | 2021-10-01 | 潍柴动力股份有限公司 | Hydrogen fuel cell humidifying system and humidifying method |
-
2020
- 2020-03-12 CN CN202020347661.2U patent/CN211975318U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113471487A (en) * | 2021-06-30 | 2021-10-01 | 潍柴动力股份有限公司 | Hydrogen fuel cell humidifying system and humidifying method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR101390770B1 (en) | Turbocharged downsized compression cylinder for a split-cycle engine | |
| US3204859A (en) | Gas compressor system | |
| KR102285733B1 (en) | Free piston engine | |
| CN102733933B (en) | There is the explosive motor of the emissions processes be placed between two expansion stages | |
| CN109339944B (en) | Miniature free piston generator | |
| CN110219793B (en) | Oil-free piston compressor with two-stage compression | |
| KR20160132023A (en) | Four-cycle internal combustion engine with pre-stage cooled compression | |
| CN211975318U (en) | Air compressor applied to gas turbine | |
| CN113047948B (en) | Free piston generator based on rigid connection | |
| CN111306036A (en) | Air compressor applied to gas turbine | |
| CN113047951B (en) | Free piston generator based on cylinder-separated thermodynamic cycle | |
| CN211692635U (en) | Mechanical supercharged two-stroke compression ignition engine | |
| CN104763525B (en) | Self-priming hydraulic free-piston linear engine | |
| CN210564945U (en) | Novel refrigeration compressor | |
| CN204476553U (en) | Two-stroke pure oxygen motor waste expansion mechanism | |
| CN208310899U (en) | A kind of rotary polygonal piston engine | |
| CN216894561U (en) | Air energy turbocharged engine and equipment comprising same | |
| CN105370385A (en) | Composite supercharging air inlet system of two-stroke engine with horizontally-opposed piston and opposed cylinder | |
| CN112576425A (en) | Water turbine | |
| CN107218119B (en) | Single-supercharger double-cylinder engine | |
| AU2011212150B2 (en) | Two-stage engine exhaust system | |
| WO2008092218A1 (en) | An internal combustion engine with extended stroke | |
| CN211202114U (en) | High-low speed compatible variable turbocharger | |
| CN213298103U (en) | High-efficiency engine | |
| CN216429829U (en) | Hydraulic air compressor and hydraulic air compression system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |