CN106014649A - Axial force adjusting system for gas turbine - Google Patents
Axial force adjusting system for gas turbine Download PDFInfo
- Publication number
- CN106014649A CN106014649A CN201610549828.1A CN201610549828A CN106014649A CN 106014649 A CN106014649 A CN 106014649A CN 201610549828 A CN201610549828 A CN 201610549828A CN 106014649 A CN106014649 A CN 106014649A
- Authority
- CN
- China
- Prior art keywords
- air inlet
- injector
- gas turbine
- turbine
- thrust
- 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.)
- Granted
Links
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 invention provides an axial force adjusting system for a gas turbine. The axial force adjusting system comprises a gas compressor, a turbine, a thrust bearing and a thrust balance cavity. A high-pressure gas extraction pipeline is connected between the gas compressor and the turbine. The axial force adjusting system further comprises a low-pressure gas extraction pipeline which comprises a first section and a second section, wherein the first section communicates with the gas compressor, the second section communicates with the thrust balance cavity, and the first section communicates with the second section through an ejector. A branch pipeline is arranged on the high-pressure gas extraction pipeline and communicates with the ejector. A valve is arranged on the branch pipeline. The thrust bearing is provided with a signal detector and a load signal collector which are electrically connected with a controller. The controller controls the valve to be opened and closed. By means of the axial force adjusting system for the gas turbine, the opening degree of the valve on the branch pipeline is adjusted according to temperature and the load signals which are fed back by the thrust bearing, the flow of high-pressure gas entering the ejector is changed, and therefore the pressure in the thrust balance cavity is adjusted, and it is ensured that the axial force of a gas turbine unit is balanced.
Description
Technical field
The present invention relates to gas turbine, particularly relate to a kind of axial draught control system of gas turbine
Background technology
Industry gas turbine mainly includes compressor, combustor and the big parts of turbine three.Air is pressed after entering compressor
Shortening the air of High Temperature High Pressure, the then burning of supply chamber fuel into, its high-temperature high-pressure fuel gas produced expands in turbine and does
Merit.
Gas turbine is in running, and air-flow can produce responsive to axial force to rotor blade and wheel disc, thus produces axle
Power upwards, and that the movement on axially, thrust bearing can bear from gas turbine rotor is axial in order to prevent rotor from occurring
Power.At present, gas turbine typically separately designs a journal bearing in compressor front end and turbine rear end, designs one at compressor
Organizing major and minor thrust bearing, the position that described journal bearing is installed is provided 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 force.Major and minor thrust bearing is main
Bearing the axial force of rotor, main thrust bearings typically bears the axial force pointing to blower outlet direction, and secondary thrust bearing bears
Point to the axial force in compressor inlet direction.
Axial force in order to make thrust bearing be born is unlikely to excessive, and prior art is taken out generally by from compressor
Gas, is introduced directly into the air-flow with certain pressure in thrust-balancing chamber；And after generally thrust-balancing chamber design is shaped, institute
The axial force being provided that is substantially stationary, it is impossible in the case of shaft head structure, it is carried out regulation actively 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
Pressure in thrust-balancing chamber is adjusted, thus balancing axial thrust.
For the problems referred to above, it is desirable to provide a kind of simple in construction and can accurately control compressed air require and pressure
Adjustable apparatus.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of axial draught control system of gas turbine, it is possible to reliable and
Accurately control gas and enter the flow of thrust-balancing chamber, thus ensure the axial force balance of gas turbine unit, overcome existing
Technical defect.
In order to solve above-mentioned technical problem, the present invention adopts the following technical scheme that a kind of gas turbine axial force regulation is
System, including compressor and turbine, described compressor front end is provided with thrust bearing, and described turbine rear end is provided with thrust-balancing chamber,
It is connected with high pressure pump-line between described compressor and turbine, also includes that lower pressure extraction pipeline, described lower pressure extraction pipeline include
First paragraph and second segment, described first paragraph connects with compressor, described second segment and thrust-balancing chamber, first paragraph and the
Two-stage nitration is connected by an injector；Described high pressure pump-line is provided with bye-pass, and described bye-pass connects with described injector,
Described bye-pass is provided with valve, and described thrust bearing is provided with temperature detector and load signal harvester, and described temperature is examined
Surveying device and load signal harvester all electrically connects with a controller, described controller controls the openings of sizes of valve.
Preferably, described injector includes the first air inlet, the second air inlet, air vent, hybrid chamber and diffusion chamber, described
Hybrid chamber and diffusion chamber are arranged along gas flow direction, and described first air inlet is connected with the first paragraph of lower pressure extraction pipeline, institute
Stating air vent to be connected with the second segment of lower pressure extraction pipeline, described second air inlet is with the bye-pass on high pressure pump-line even
Connect.
Further, described first air inlet and the second air inlet are positioned at the side of injector, and described air vent is positioned at and draws
The opposite side of emitter, described hybrid chamber and diffusion chamber are in the centre position of injector.
Further, described second air inlet is provided with nozzle.
As it has been described above, the axial draught control system of gas turbine of the present invention, have the advantages that
The present invention arranges bye-pass on high pressure pump-line, and arranges the valve that openings of sizes is controlled on bye-pass
Door, described valve openings size is adjusted by the temperature and the load signal that are fed back by thrust bearing, changes high pressure gas
Body enters into the flow in injector, thus regulates the pressure in thrust-balancing chamber, it is ensured that the axial force of gas turbine unit
Balance.
The enforcement body of the present invention is simple, reliable operation, it is simple to process and install.
Accompanying drawing explanation
Fig. 1 is the structural representation sketch of the present invention.
Fig. 2 is the schematic diagram of injector in the present invention.
In figure: 1, compressor 11, thrust bearing
2, turbine 21, thrust-balancing chamber
3, high pressure pump-line 31, bye-pass
32, valve 33, valve
4, lower pressure extraction pipeline 41, first paragraph
42, second segment 5, injector
51, first air inlet the 52, second air inlet
53, air vent 54, hybrid chamber
55, nozzle 56, bubbler
6, temperature detector 7, load signal harvester
8, controller
Detailed description of the invention
Structure depicted in Figure of description, ratio, size etc., the most only in order to coordinate the content disclosed in description, with
Understand for those skilled in the art and read, being 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, do not affecting what the present invention can be generated by
Under effect and the purpose that can reach, all should still fall in the range of disclosed technology contents can be contained.Meanwhile,
In this specification cited as " on ", D score, "front", "rear", the term such as " middle ", be merely convenient to the clear of narration, and
It is not used to limit the enforceable scope of the present invention, being altered or modified of its relativeness, is changing under technology contents without essence, when
Also the enforceable category of the present invention it is considered as.
As depicted in figs. 1 and 2, the present invention is a kind of axial draught control system of gas turbine, and gas turbine includes compressor 1
With turbine 2, described compressor 1 front end is provided with thrust bearing 11, and described turbine 2 rear end is provided with thrust-balancing chamber 21, described pressure
High pressure pump-line 3 it is connected with between mechanism of qi 1 and turbine 2.Also include that lower pressure extraction pipeline 4, described lower pressure extraction pipeline 4 include
One section 41 and second segment 42, described first paragraph 41 connects with compressor 1, and described second segment 42 connects with thrust-balancing chamber 21,
First paragraph 41 is connected by an injector 5 with second segment 42.Described high pressure pump-line 3 is provided with bye-pass 31, described arm
Road 31 connects with described injector 5, and described bye-pass 31 is provided with valve 32, and described thrust bearing 11 is provided with temperature detector
6 and load signal harvester 7, described temperature detector 6 and load signal harvester 7 all electrically connect with a controller 8, described control
Device 8 processed controls the openings of sizes of valve 32.High pressure pump-line 3 and lower pressure extraction pipeline 4 in the present invention are existing structure,
The most do not do too much statement.
The operation principle of the present invention is:
During gas turbine work, the gas in compressor 1 can pass through high pressure pump-line 3 and lower pressure extraction pipeline 4 respectively
Enter turbine 2 and thrust-balancing chamber 21.Wherein, the partial high pressure gas in high pressure pump-line 3 can be entered by bye-pass 31
Entering to injector 5, then mix at hybrid chamber 54 with the low-pressure gas through injector 5, mixed gas pressure changes
Becoming, the most mixed gas pressure is higher than the low-pressure gas pressure in lower pressure extraction pipeline 4, and is less than in high pressure pump-line 3
High-pressure gas pressure.The high-pressure gas flow entered in injector 5 is controlled by valve 32, it may be assumed that temperature detector 6 and load
The signal of signal picker 7 Real-time Collection thrust bearing 11 feedback, the incoming controller of described signal 8, controller 8 controls arm again
Valve 32 on road 31, the opening-closing size of valve 32 can regulate gas flow and the pressure of injector 5 ejection, thus can be right
Gas pressure in thrust-balancing chamber 21 carries out effective and stable regulation, accurately controls thrust-balancing chamber 21 and flows into, flows
The tolerance gone out, regulates pressure size, thus ensures the axial force balance of gas turbine unit.On described high pressure pump-line 3
Being additionally provided with valve 33, valve 33 is positioned at the upstream side of bye-pass 31, i.e. gases at high pressure and first passes through valve 33 and enter back into bye-pass
31.Gases at high pressure gas pressure in high pressure pump-line 3 and flow velocity can be controlled further, more accurately by valve 33
Control bye-pass 31 enters the high-pressure gas flow in injector 5 and pressure.
In the present embodiment, described injector 5 includes first air inlet the 51, second air inlet 52, air vent 53, hybrid chamber
54 and diffusion chamber 56, described hybrid chamber 54 and diffusion chamber 56 along gas flow direction arrange, described first air inlet 51 and low pressure
The first paragraph 41 of pump-line 4 connects, and described air vent 53 is connected with the second segment 42 of lower pressure extraction pipeline 4, and described second enters
QI KOU 52 is connected with the bye-pass 31 on high pressure pump-line 3.Further, described first air inlet 51 and the second air inlet 52
Being positioned at the side of injector 5, described air vent 53 is positioned at the opposite side of injector 5, and described hybrid chamber 54 and diffusion chamber 56 are drawing
The centre position of emitter 5.First air inlet 51 and the second air inlet 52 are positioned at the same side can allow gases at high pressure and low-pressure gas
Simultaneously enter hybrid chamber 54 to be sufficiently mixed, discharge from air vent 53 the most again.
In the present embodiment, the cross section of described diffusion chamber 56 first reduces to air vent 53 side from hybrid chamber 54 and becomes
Greatly, i.e. mid portion is thin, and two end portions is thick, so arranges and can ensure that the gas in hybrid chamber 54 can be sufficiently mixed, will not
Too fast by diffusion chamber 56, and can quickly spread and flow into second segment after gas is by the mid portion of diffusion chamber 56
In 42, it is ensured that the flow velocity of gas.
In addition, in order to control the gas flow from high pressure exhaust pipe 3 and pressure, improve the stream of gases at high pressure
Speed, described second air inlet 52 is provided with nozzle 55.Described nozzle 55 is towards air vent 53 side.High pressure from bye-pass 31
Gas is sprayed by nozzle 55, and the gases at high pressure flow velocity after nozzle 55 increases, therefore, it is possible to effectively drive from lower pressure extraction
The low-pressure gas of pipeline 4.
In sum, the axial draught control system of one gas turbine of the present invention, it is possible to can reliably and accurately control gas
Flow, thus ensure the axial force balance of gas turbine unit.So, the present invention effectively overcomes more of the prior art
Practical problem thus have the highest value and use meaning.
The principle of the above-mentioned embodiment only illustrative present invention and effect thereof, not for limiting the present invention.This
Bright also have many aspects can improve on the premise of overall thought, all can be for those skilled in the art
Under the spirit and the scope of the present invention, above-described embodiment can be modified or change.Therefore, art such as
All equivalences that middle tool usually intellectual is completed under without departing from disclosed spirit and technological thought modify or
Change, must be contained by the claim of the present invention.
Claims (4)
1. the axial draught control system of gas turbine, including compressor (1) and turbine (2), described compressor (1) front end is provided with
Thrust bearing (11), described turbine (2) rear end is provided with thrust-balancing chamber (21), it is characterised in that: described compressor (1) and thoroughly
It is connected with high pressure pump-line (3) between flat (2), also includes that lower pressure extraction pipeline (4), described lower pressure extraction pipeline (4) include the
One section (41) and second segment (42), described first paragraph (41) connects with compressor (1), described second segment (42) and thrust-balancing chamber
Room (2) connects, and first paragraph (41) is connected by an injector (5) with second segment (42)；Described high pressure pump-line (3) is provided with
Bye-pass (31), described bye-pass (31) connects with described injector (5), and described bye-pass (31) is provided with valve (32), institute
State thrust bearing (11) and be provided with temperature detector (6) and load signal harvester (7), described temperature detector (6) and load
Signal picker (7) all electrically connects with a controller (8), and described controller (8) controls the openings of sizes of valve (32).
The axial draught control system of gas turbine the most according to claim 1, it is characterised in that: described injector (5) includes
First air inlet (51), the second air inlet (52), air vent (53), hybrid chamber (54) and diffusion chamber (56), described hybrid chamber
(54) arrange along gas flow direction with diffusion chamber (56), described first air inlet (51) and the first of lower pressure extraction pipeline (4)
Section (41) connects, and described air vent (53) is connected with the second segment (42) of lower pressure extraction pipeline (4), described second air inlet (52)
It is connected with the bye-pass (31) on high pressure pump-line (3).
The axial draught control system of gas turbine the most according to claim 2, it is characterised in that: described first air inlet (51)
With the side that the second air inlet (52) is positioned at injector (5), described air vent (53) is positioned at the opposite side of injector (5), described
Hybrid chamber (54) and diffusion chamber (56) are in the centre position of injector (5).
The axial draught control system of gas turbine the most according to claim 2, it is characterised in that: described second air inlet (52)
It is provided 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 true CN106014649A (en) | 2016-10-12 |
| CN106014649B CN106014649B (en) | 2018-04-17 |
Family
ID=57117631
Family Applications (1)
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106014649B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106593653A (en) * | 2016-12-19 | 2017-04-26 | 上海泛智能源装备有限公司 | Combustion gas turbine axial force adjusting system, method and device and combustion gas turbine |
| CN110130998A (en) * | 2019-06-28 | 2019-08-16 | 重庆江增船舶重工有限公司 | A kind of the self-balancing cooling system and method for turbocompressor |
| CN113819807A (en) * | 2021-09-18 | 2021-12-21 | 贵州黎阳天翔科技有限公司 | Millimeter wave smoke screen generating device |
| CN115355193A (en) * | 2022-10-24 | 2022-11-18 | 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110027064A1 (en) * | 2009-08-03 | 2011-02-03 | General Electric Company | System and method for modifying rotor thrust |
| 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 |
-
2016
- 2016-07-13 CN CN201610549828.1A patent/CN106014649B/en active Active
Patent Citations (5)
| 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 |
| US20110027064A1 (en) * | 2009-08-03 | 2011-02-03 | General Electric Company | System and method for modifying rotor thrust |
| 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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106593653A (en) * | 2016-12-19 | 2017-04-26 | 上海泛智能源装备有限公司 | Combustion gas turbine axial force adjusting system, method and device and combustion gas turbine |
| CN110130998A (en) * | 2019-06-28 | 2019-08-16 | 重庆江增船舶重工有限公司 | A kind of the self-balancing cooling system and method for turbocompressor |
| CN113819807A (en) * | 2021-09-18 | 2021-12-21 | 贵州黎阳天翔科技有限公司 | Millimeter wave smoke screen generating device |
| CN115355193A (en) * | 2022-10-24 | 2022-11-18 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106014649B (en) | 2018-04-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106014649A (en) | Axial force adjusting system for gas turbine | |
| US20190186381A1 (en) | Intergrated environmental control system manifold | |
| KR101619758B1 (en) | Gas turbine power plant with exhaust gas recirculation | |
| CA2535094C (en) | Methods and apparatus for operating gas turbine engines | |
| CN1590709A (en) | Turbine airfoil cooling flow particle separator | |
| CN103917760A (en) | Adjustable compressor Trim | |
| CN107218156B (en) | Hybrid rocket engine pintle formula becomes larynx diameter Effuser device | |
| CN205805736U (en) | A kind of pressure regulating system of gas turbine thrust-balancing chamber | |
| CN109681907B (en) | Variable-load air-coal matching control device and method for coal-fired power plant boiler | |
| US20110265486A1 (en) | Combustion system with variable pressure differential for additional turndown capability of a gas turine engine | |
| CN105715585B (en) | Variable-geometry exit guide blade | |
| EP3219956A2 (en) | Turbine engine ejector throat control | |
| CN110318874A (en) | The control whirlpool flow path system of centrifugal compressor back chamber in a kind of gas turbine | |
| CN103175199B (en) | Low-load burner capable of achieving boiler flue heat recycling for boiler | |
| CN106014643B (en) | Gas turbine axial direction apparatus for adjusting force | |
| FR2462564A1 (en) | INSTALLATION FOR CONTROLLING ADJUSTABLE PUSH TUTERS OF DOUBLE FLOW TURBOREACTORS | |
| CN109458229A (en) | A kind of turbine disk chamber seal structure of band bypass bleed | |
| KR101619753B1 (en) | Axial compressor for fluid-flow machines | |
| EP3037352A1 (en) | System and method with inlet particle separator | |
| JP2015509564A (en) | Method for driving gas turbine power plant including exhaust gas circulation system, and gas turbine power plant | |
| CN105484901B (en) | A kind of metal dust high pressure supply system controlled based on pressure difference | |
| CN209876975U (en) | Load-variable air-coal matching control device for boiler of coal-fired power plant | |
| CN111579246A (en) | Supercharger test bench combustion chamber air inflow proportion adjusting device and method | |
| EP2667093A1 (en) | Method and device for controlling operation of oxygen combustion boiler | |
| CN205805735U (en) | A kind of gas turbine axial force adjustment structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |