CN106014649B - Gas turbine axial direction draught control system - Google Patents
Gas turbine axial direction draught control system Download PDFInfo
- Publication number
- CN106014649B CN106014649B CN201610549828.1A CN201610549828A CN106014649B CN 106014649 B CN106014649 B CN 106014649B CN 201610549828 A CN201610549828 A CN 201610549828A CN 106014649 B CN106014649 B CN 106014649B
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- segment
- injector
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- pass
- air inlet
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- 238000000605 extraction Methods 0.000 claims abstract description 18
- 238000009792 diffusion process Methods 0.000 claims description 12
- 238000011144 upstream manufacturing Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 abstract description 52
- 230000008859 change Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The present invention provides a kind of gas turbine axial direction draught control system, including compressor, turbine, thrust bearing, thrust-balancing chamber, high pressure pump-line is connected between compressor and turbine, further include lower pressure extraction pipeline, lower pressure extraction pipeline includes first segment and second segment, first segment is connected with compressor, and second segment is connected with thrust-balancing chamber, first segment and second segment by an injector；The high pressure pump-line is equipped with bye-pass, and the bye-pass is connected with injector, and bye-pass is equipped with valve, and thrust bearing is equipped with the temperature detector and load signal collector being electrically connected with the controller, the opening and closing of controller control valve door.The valve openings size on bye-pass is adjusted in the temperature and load signal that the present invention is fed back by thrust bearing, change gases at high pressure enter the flow in injector, so as to adjust the indoor pressure of thrust-balancing chamber, ensure the axial force balance of gas turbine unit.
Description
Technical field
The present invention relates to gas turbine, more particularly to a kind of gas turbine axial direction draught control system
Background technology
Industry gas turbine mainly includes three big component of compressor, combustion chamber and turbine.Air is pressed after entering compressor
Shorten the air of high temperature and pressure into, then supply chamber fuel burning, its high-temperature high-pressure fuel gas produced expands in turbine to be done
Work(.
In the process of running, air-flow can produce responsive to axial force to gas turbine to rotor blade and wheel disc, so as to produce axis
Upward power, and the movement in axial direction occurs for rotor in order to prevent, thrust bearing can bear the axial direction from gas turbine rotor
Power.At present, gas turbine generally separately designs a journal bearing in compressor front end and turbine rear end, and one is designed in compressor
The major and minor thrust bearing of group, the position of the journal bearing installation are equipped with bearing block (a compressorshaft bearing and a turbine spindle
Bearing).Rotor is supported on stator by two journal bearings, and journal bearing is solely subjected to radial load.Major and minor thrust bearing is main
The axial force of rotor is born, main thrust bearings generally bear to be directed toward the axial force in blower outlet direction, and secondary thrust bearing is born
It is directed toward the axial force in compressor inlet direction.
In order to make the axial force that thrust bearing is born be unlikely to excessive, the prior art is taken out generally by from compressor
Gas, the air-flow with certain pressure is introduced directly into thrust-balancing chamber；And usually after the sizing of thrust-balancing chamber design, institute
The axial force that can be provided is substantially stationary, can not carry out the adjusting of active to it in the case of shaft head structure after not changing, and limits
The nargin of whole axial thrust system.When complete machine axial force exceedes the working range that thrust bearing can bear, need to pass through
The indoor pressure of thrust-balancing chamber is adjusted, so that balancing axial thrust.
In view of the above-mentioned problems, need to provide a kind of simple in structure and can accurately control compressed air require and pressure
Adjustable apparatus.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of gas turbine axial direction draught control system, can reliably and
Accurate control gas enters the flow of thrust-balancing chamber, so as to ensure the axial force balance of gas turbine unit, overcomes existing
Technical defect.
In order to solve the above-mentioned technical problem, the present invention adopts the following technical scheme that：A kind of gas turbine axial force adjusts system
System, including compressor and turbine, the compressor front end are equipped with thrust bearing, and the turbine rear end is equipped with thrust-balancing chamber,
High pressure pump-line is connected between the compressor and turbine, further includes lower pressure extraction pipeline, the lower pressure extraction pipeline includes
First segment and second segment, the first segment are connected with compressor, the second segment and thrust-balancing chamber, first segment and the
Two sections are connected by an injector；The high pressure pump-line is equipped with bye-pass, and the bye-pass is connected with the injector,
The bye-pass is equipped with valve, and the thrust bearing is equipped with temperature detector and load signal collector, the temperature inspection
Survey device and load signal collector is electrically connected with a controller, the openings of sizes of the controller control valve door.
Preferably, the injector includes the first air inlet, the second air inlet, exhaust outlet, mixing chamber and diffusion chamber, described
Mixing chamber and diffusion chamber are set along gas flow direction, and first air inlet is connected with the first segment of lower pressure extraction pipeline, institute
The second segment that exhaust outlet is stated with lower pressure extraction pipeline is connected, and second air inlet connects with the bye-pass on high pressure pump-line
Connect.
Further, first air inlet and the second air inlet are located at the side of injector, and the exhaust outlet is located at and draws
The opposite side of emitter, the mixing chamber and diffusion chamber are in the centre position of injector.
Further, second air inlet is equipped with nozzle.
As described above, gas turbine axial direction draught control system of the present invention, has the advantages that：
The present invention sets bye-pass on high pressure pump-line, and the controllable valve of openings of sizes is set on bye-pass
The valve openings size is adjusted in door, the temperature and load signal fed back by thrust bearing, changes high pressure gas
Body enters the flow in injector, so as to adjust the indoor pressure of thrust-balancing chamber, ensures the axial force of gas turbine unit
Balance.
The enforcement body of the present invention is simple, reliable operation, easy to process and installation.
Brief description of the drawings
Fig. 1 is the structure schematic diagram of the present invention.
Fig. 2 is the schematic diagram of injector in the present invention.
In figure：1st, compressor 11, thrust bearing
2nd, turbine 21, thrust-balancing chamber
3rd, high pressure pump-line 31, bye-pass
32nd, valve 33, valve
4th, lower pressure extraction pipeline 41, first segment
42nd, second segment 5, injector
51st, the first air inlet 52, the second air inlet
53rd, exhaust outlet 54, mixing chamber
55th, nozzle 56, diffuser
6th, temperature detector 7, load signal collector
8th, controller
Embodiment
Structure, ratio, size depicted in Figure of description etc., only to coordinate the revealed content of specification, with
Understand for those skilled in the art and read, be not limited to the enforceable qualifications of the present invention, therefore do not have technically
Essential meaning, the modification of any structure, the change of proportionate relationship or the adjustment of size, can be generated not influencing the present invention
Under effect and the purpose that can reach, should all still it fall in the range of disclosed technology contents can be covered.Meanwhile
Cited such as " on ", " under ", "front", "rear", " centre " term, are merely convenient to the clear of narration in this specification, and
It is not used to limit the enforceable scope of the present invention, its relativeness is altered or modified, in the case where changing technology contents without essence, when
Also it is considered as the enforceable category of the present invention.
As depicted in figs. 1 and 2, the present invention is a kind of gas turbine axial direction draught control system, and gas turbine includes compressor 1
With turbine 2,1 front end of compressor is equipped with thrust bearing 11, and 2 rear end of turbine is equipped with thrust-balancing chamber 21, the pressure
High pressure pump-line 3 is connected between mechanism of qi 1 and turbine 2.Further include lower pressure extraction pipeline 4, the lower pressure extraction pipeline 4 includes the
One section 41 and second segment 42, the first segment 41 are connected with compressor 1, and the second segment 42 is connected with thrust-balancing chamber 21,
First segment 41 is connected with second segment 42 by an injector 5.The high pressure pump-line 3 is equipped with bye-pass 31, the branch pipe
Road 31 is connected with the injector 5, and the bye-pass 31 is equipped with valve 32, and the thrust bearing 11 is equipped with temperature detector
6 and load signal collector 7, the temperature detector 6 and load signal collector 7 be electrically connected with a controller 8, the control
The openings of sizes of 8 control valve 32 of device processed.High pressure pump-line 3 and lower pressure extraction pipeline 4 in the present invention are existing structure,
Therefore excessive statement is not done.
The present invention operation principle be：
When gas turbine works, the gas in compressor 1 can pass through high pressure pump-line 3 and lower pressure extraction pipeline 4 respectively
Into turbine 2 and thrust-balancing chamber 21.Wherein, the partial high pressure gas in high pressure pump-line 3 can by bye-pass 31 into
Enter to injector 5, then mixed with by the low-pressure gas of injector 5 in mixing chamber 54, mixed gas pressure changes
Becoming, i.e., mixed gas pressure is higher than the low-pressure gas pressure in lower pressure extraction pipeline 4, and less than in high pressure pump-line 3
High-pressure gas pressure.Controlled into the high-pressure gas flow in injector 5 by valve 32, i.e.,：Temperature detector 6 and load
Signal picker 7 gathers the signal of the feedback of thrust bearing 11 in real time, and the signal is passed to controller 8, and controller 8 controls branch pipe again
Valve 32 on road 31, the opening-closing size of valve 32 can adjust the gas flow and pressure of the ejection of injector 5, thus can be right
Gas pressure in thrust-balancing chamber 21 carries out adjusting that is effective and stablizing, accurate to control thrust-balancing chamber 21 flow into, flow
The tolerance gone out, adjusts pressure size, so as to ensure the axial force balance of gas turbine unit.On the high pressure pump-line 3
Valve 33 is additionally provided with, valve 33 is located at the upstream side of bye-pass 31, i.e. gases at high pressure first pass through valve 33 and enter back into bye-pass
31.Gas pressure and flow velocity of the gases at high pressure in high pressure pump-line 3 can further be controlled by valve 33, more accurately
Control bye-pass 31 in enter injector 5 in high-pressure gas flow and pressure.
In the present embodiment, the injector 5 includes the first air inlet 51, the second air inlet 52, exhaust outlet 53, mixing chamber
54 and diffusion chamber 56, the mixing chamber 54 and diffusion chamber 56 set along gas flow direction, first air inlet 51 and low pressure
The first segment 41 of pump-line 4 connects, and the exhaust outlet 53 is connected with the second segment 42 of lower pressure extraction pipeline 4, described second into
Gas port 52 is connected with the bye-pass 31 on high pressure pump-line 3.Further, 51 and second air inlet 52 of the first air inlet
Positioned at the side of injector 5, the exhaust outlet 53 is located at the opposite side of injector 5, and the mixing chamber 54 and diffusion chamber 56 are drawing
The centre position of emitter 5.First air inlet 51 and the second air inlet 52, which are located at the same side, can allow gases at high pressure and low-pressure gas
It is sufficiently mixed into mixing chamber 54, is then discharged again from exhaust outlet 53 at the same time.
In the present embodiment, the cross section of the diffusion chamber 56 first reduces from mixing chamber 54 to 53 side of exhaust outlet and becomes again
Greatly, i.e., center section is thin, and two end portions are thick, and so setting can ensure that the gas in mixing chamber 54 can be sufficiently mixed, will not
It is too fast by diffusion chamber 56, and can quickly be spread after gas is by the center section of diffusion chamber 56 and flow into second segment
In 42, ensure the flow velocity of gas.
In addition, in order to control the gas flow and pressure from high pressure exhaust pipe 3, the stream of gases at high pressure is improved
Speed, second air inlet 52 are equipped with nozzle 55.The nozzle 55 is towards 53 side of exhaust outlet.High pressure from bye-pass 31
Gas is sprayed by nozzle 55, the gases at high pressure flow velocity increase after nozzle 55, therefore can effectively be driven from lower pressure extraction
The low-pressure gas of pipeline 4.
In conclusion a kind of gas turbine axial direction draught control system of the present invention, can reliably and accurately control gas
Flow, so as to ensure the axial force balance of gas turbine unit.So the present invention effectively overcome it is more of the prior art
Practical problem is so as to have very high utility value and using meaning.
The principle of the present invention and its effect is only illustrated in the above embodiment, not for the limitation present invention.This hair
It is bright to also have many aspects to be improved on the premise of without prejudice to overall thought, all can be for those skilled in the art
Without prejudice under the spirit and scope of the present invention, modifications and changes can be carried out to above-described embodiment.Therefore, technical field such as
Middle tool usually intellectual without departing from disclosed spirit and all equivalent modifications for being completed under technological thought or
Change, should be covered by the claim of the present invention.
Claims (3)
1. a kind of gas turbine axial direction draught control system, including compressor (1) and turbine (2), compressor (1) front end is equipped with
Thrust bearing (11), turbine (2) rear end are equipped with thrust-balancing chamber (21), it is characterised in that：The compressor (1) and thoroughly
High pressure pump-line (3) is connected between flat (2), further includes lower pressure extraction pipeline (4), the lower pressure extraction pipeline (4) includes the
One section (41) and second segment (42), the first segment (41) connect with compressor (1), the second segment (42) and thrust-balancing chamber
Room (21) connects, and first segment (41) is connected with second segment (42) by an injector (5)；Set on the high pressure pump-line (3)
There is bye-pass (31), the bye-pass (31) connects with the injector (5), and the bye-pass (31) is equipped with valve (32),
Valve (33) is additionally provided with the high pressure pump-line (3), valve (33) is located at the upstream side of bye-pass (31)；It is described to push away
Power bearing (11) is equipped with temperature detector (6) and load signal collector (7), the temperature detector (6) and load signal
Collector (7) is electrically connected with a controller (8), the openings of sizes of controller (8) control valve (32)；The injector
(5) the first air inlet (51), the second air inlet (52), exhaust outlet (53), mixing chamber (54) and diffusion chamber (56) are included, it is described mixed
Close chamber (54) and diffusion chamber (56) is set along gas flow direction, first air inlet (51) and lower pressure extraction pipeline (4)
First segment (41) connects, and the exhaust outlet (53) is connected with the second segment (42) of lower pressure extraction pipeline (4), second air inlet
(52) it is connected with the bye-pass (31) on high pressure pump-line (3).
2. gas turbine axial direction draught control system according to claim 1, it is characterised in that：First air inlet (51)
It is located at the side of injector (5) with the second air inlet (52), the exhaust outlet (53) is located at the opposite side of injector (5), described
Mixing chamber (54) and diffusion chamber (56) are in the centre position of injector (5).
3. gas turbine axial direction draught control system according to claim 1, it is characterised in that：Second air inlet (52)
It is equipped with nozzle (55).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610549828.1A CN106014649B (en) | 2016-07-13 | 2016-07-13 | Gas turbine axial direction draught control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610549828.1A CN106014649B (en) | 2016-07-13 | 2016-07-13 | Gas turbine axial direction draught control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106014649A CN106014649A (en) | 2016-10-12 |
| CN106014649B true CN106014649B (en) | 2018-04-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610549828.1A Active CN106014649B (en) | 2016-07-13 | 2016-07-13 | Gas turbine axial direction draught control system |
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| CN (1) | CN106014649B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106593653B (en) * | 2016-12-19 | 2018-07-06 | 新奥能源动力科技（上海）有限公司 | Gas turbine axial direction draught control system, method and apparatus and gas turbine |
| CN110130998B (en) * | 2019-06-28 | 2024-06-07 | 重庆江增船舶重工有限公司 | Self-balancing cooling system and method for turbine compressor |
| CN113819807B (en) * | 2021-09-18 | 2023-03-31 | 贵州黎阳天翔科技有限公司 | Millimeter wave smoke screen generating device |
| CN115355193B (en) * | 2022-10-24 | 2023-03-07 | 中国航发四川燃气涡轮研究院 | Dynamic regulation and control method for axial force of gas compressor under heating and pressurizing conditions |
| CN116220821B (en) * | 2023-02-21 | 2025-08-01 | 中国科学院工程热物理研究所 | Structure for adjusting axial force of turbine disc by utilizing exhaust injection and aeroengine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103016153A (en) * | 2013-01-09 | 2013-04-03 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force adjusting device for rotor of gas turbine |
| CN104265461A (en) * | 2007-10-22 | 2015-01-07 | 通用电气公司 | System For Delivering Air From A Multi-stage Compressor To A Turbine Portion Of A Gas Turbine Engine |
| CN104727950A (en) * | 2015-02-10 | 2015-06-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force control device for combustion gas turbine and control method thereof |
| CN205805736U (en) * | 2016-07-13 | 2016-12-14 | 上海电气燃气轮机有限公司 | A kind of pressure regulating system of gas turbine thrust-balancing chamber |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8434994B2 (en) * | 2009-08-03 | 2013-05-07 | General Electric Company | System and method for modifying rotor thrust |
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2016
- 2016-07-13 CN CN201610549828.1A patent/CN106014649B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104265461A (en) * | 2007-10-22 | 2015-01-07 | 通用电气公司 | System For Delivering Air From A Multi-stage Compressor To A Turbine Portion Of A Gas Turbine Engine |
| CN103016153A (en) * | 2013-01-09 | 2013-04-03 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force adjusting device for rotor of gas turbine |
| CN104727950A (en) * | 2015-02-10 | 2015-06-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial force control device for combustion gas turbine and control method thereof |
| CN205805736U (en) * | 2016-07-13 | 2016-12-14 | 上海电气燃气轮机有限公司 | A kind of pressure regulating system of gas turbine thrust-balancing chamber |
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| Publication number | Publication date |
|---|---|
| CN106014649A (en) | 2016-10-12 |
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