CN106014643B - Gas turbine axial direction apparatus for adjusting force - Google Patents
Gas turbine axial direction apparatus for adjusting force Download PDFInfo
- Publication number
- CN106014643B CN106014643B CN201610550696.4A CN201610550696A CN106014643B CN 106014643 B CN106014643 B CN 106014643B CN 201610550696 A CN201610550696 A CN 201610550696A CN 106014643 B CN106014643 B CN 106014643B
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- CN
- China
- Prior art keywords
- adjustable plate
- packing ring
- thrust
- gas turbine
- throttle orifice
- 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.)
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Links
- 238000012856 packing Methods 0.000 claims abstract description 32
- 230000007246 mechanism Effects 0.000 claims abstract description 9
- 238000007789 sealing Methods 0.000 claims description 11
- 244000126211 Hericium coralloides Species 0.000 claims description 7
- 210000004907 gland Anatomy 0.000 claims description 7
- 239000007789 gas Substances 0.000 description 18
- 230000008859 change Effects 0.000 description 5
- 238000010276 construction Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000001914 calming effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000010355 oscillation 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
-
- 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
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention provides a kind of gas turbine axial apparatus for adjusting force, including turbine bearing block, spindle nose is provided with turbine bearing block, bleed chamber is provided with the turbine bearing block, the inwall of turbine bearing block protrudes to form auxiliary section to inner side, packing ring is provided between the auxiliary section and the spindle nose, the both sides of packing ring are thrust-balancing chamber and bearing bore respectively, the bleed chamber and the thrust-balancing chamber, throttle orifice is provided with the packing ring, the throttle orifice connects the thrust-balancing chamber with bearing bore；Also include a mobilizable adjustable plate, the adjustable plate can be covered on the throttle orifice of the packing ring, and the position of the adjustable plate passes through driving mechanisms control.The present invention is adjusted by compressor side thrust bearing is fed back on gas turbine temperature and load signal to described regulation Board position, changes area of the air-flow by throttle orifice, so as to adjust the pressure in thrust-balancing chamber.
Description
Technical field
The present invention relates to gas turbine, more particularly to a kind of axial apparatus for adjusting force of gas turbine.
Background technology
Industry gas turbine mainly includes compressor, combustion chamber and the big part of turbine three.Air is pressed after entering compressor
Shorten the air of HTHP 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 axle
Upward power, and in order to prevent rotor from occurring the movement on axial direction, thrust bearing can bear the axial direction from gas turbine rotor
Power.At present, gas turbine typically 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 that the 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 load.Major and minor thrust bearing is main
The axial force of rotor is born, main thrust bearings are typically born to point to the axial force in blower outlet direction, and secondary thrust bearing is born
Point to the axial force in compressor inlet direction.
In order that the axial force that thrust bearing is born is unlikely to excessive, prior art is taken out generally by from compressor
Gas, the air-flow with certain pressure is introduced directly into thrust-balancing chamber；And generally after the sizing of thrust-balancing chamber design, institute
The axial force that can be provided is substantially stationary, it is impossible to carry out the regulation 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, it need to pass through
Pressure in thrust-balancing chamber is adjusted, so that balancing axial thrust.
In view of the above-mentioned problems, needing a kind of simple in construction, sealing property of offer reliable and can accurately control compressed air
The adjustable apparatus of flow and pressure.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of simple in construction, dependable performance and can accurately control compression
The axial apparatus for adjusting force of the gas turbine of air mass flow and pressure.
In order to solve the above-mentioned technical problem, the present invention is adopted the following technical scheme that：A kind of gas turbine axial force regulation dress
Put, including turbine bearing block, spindle nose is provided with turbine bearing block, journal bearing is provided between turbine bearing block and spindle nose, it is described
Bleed chamber is provided with turbine bearing block, the inwall of turbine bearing block protrudes to form auxiliary section to inner side, the auxiliary section with it is described
Packing ring is provided between spindle nose, the both sides of the packing ring are thrust-balancing chamber and the bearing for placing journal bearing respectively
Throttle orifice is provided with chamber, the bleed chamber and the thrust-balancing chamber, the packing ring, the throttle orifice is pushed away described
Balance chamber is connected with bearing bore；Also include a mobilizable adjustable plate, the adjustable plate can be covered in the packing ring
Throttle orifice on, the position of the adjustable plate passes through driving mechanisms control.
Preferably, stopper slot is provided with the end face of the packing ring, throttle orifice passes through stopper slot, and the adjustable plate is located at institute
State in stopper slot, the drive mechanism includes being connected with drive rod in motor, the rotating shaft of motor, and the end of the drive rod is provided with tooth
Wheel, the adjustable plate is provided with rack, and the gear is meshed with the rack.
Further, elongated slot is provided with the adjustable plate, the rack is arranged in elongated slot along elongated slot length direction.
Further, the inwall of the stopper slot is provided with spacing preiection, is limited in adjustable plate by spacing preiection spacing
In groove.
Preferably, comb tooth sealing gland is provided between the packing ring and spindle nose.
Preferably, brush seal is provided between the packing ring and spindle nose.
Preferably, the throttle orifice is circular arc perpendicular to the section of spindle nose axis.
As described above, the axial apparatus for adjusting force of gas turbine of the present invention, has the advantages that：
The present invention is provided with packing ring, and opens up throttle orifice, in addition to a moveable adjustable plate on packing ring, leads to
Cross temperature that thrust bearing fed back and load signal is adjusted to described regulation Board position, change air-flow and pass through throttle orifice
Area, so as to adjust the pressure in thrust-balancing chamber, it is ensured that the axial force balance of gas turbine unit.
The pressure in thrust-balancing chamber can in real time be adjusted by the present invention.In addition, also being installed in the present invention
There are comb tooth sealing gland and brush seal, so as to effectively overcome the shortcoming that the sealing property brought of unit vibrations is unstable.Packing ring
For cyclic structure, its form is simple, lightweight, material saving and is easy to process and installs.
Brief description of the drawings
Fig. 1 is structure chart of the invention.
Fig. 2 is enlarged drawing at A in Fig. 1.
Fig. 3 is B direction views in Fig. 2.
In figure：1st, turbine bearing block 10, bearing 11, bleed chamber
12nd, auxiliary section 2, spindle nose 3, packing ring
31st, throttle orifice 32, stopper slot 33, spacing preiection
41st, thrust-balancing chamber 42, bearing bore 5, adjustable plate
51st, rack 52, elongated slot 6, drive mechanism
61st, motor 62, drive rod 63, gear
71st, comb tooth sealing gland 72, brush seal
Embodiment
Structure, ratio, size depicted in Figure of description etc., only to coordinate the content disclosed in specification, with
Understand and read for those skilled in the art, be not limited to enforceable qualifications of the 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 influenceing the present invention
Under effect and the purpose that can reach, all should 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 enforceable scope of the invention, being altered or modified for its relativeness is changed under technology contents without essence, when
Also it is considered as enforceable category of the invention.
The present invention is a kind of axial apparatus for adjusting force of gas turbine, and as shown in Figure 1-Figure 3, it includes turbine bearing block 1, thoroughly
Spindle nose 2 is provided with plane bearing seat 1, is provided with journal bearing 10, the turbine bearing block 1 and opens between turbine bearing block 1 and spindle nose 2
Have bleed chamber 11, the inwall of turbine bearing block 1 protrudes to form auxiliary section 12 to inner side, the auxiliary section 12 and the spindle nose 2 it
Between be provided with packing ring 3, the packing ring 3 by bolt be arranged on turbine bearing block 1 on.The both sides of the packing ring 3 are respectively
Thrust-balancing chamber 41 and the bearing bore 42 for placing journal bearing 10, the bleed chamber 11 and the thrust-balancing chamber 41
Throttle orifice 31 is provided with connection, the packing ring 3, the throttle orifice 31 connects the thrust-balancing chamber 41 and bearing bore 42
It is logical.Also include a mobilizable adjustable plate 5, the adjustable plate 5 can be covered on the throttle orifice 31 of the packing ring 3, described
The position of adjustable plate 5 is controlled by drive mechanism 6.
Drive mechanism 6 in the present invention can have diversified forms, and for example it includes an oil cylinder, the piston rod and tune of oil cylinder
Section plate 5 is connected, and piston rod is moved together when flexible with adjustable plate 5, so as to adjust covering of the adjustable plate 5 to throttle orifice 31
Area, that is, adjust flow of the compressed air by throttle orifice 31.It is preferred in the present embodiment, it is as shown in Figures 2 and 3, described
Stopper slot 32 is provided with the end face of packing ring 3, throttle orifice 31 passes through stopper slot 32, and the adjustable plate 5 is located at the stopper slot 32
In；The drive mechanism 6 includes being connected with drive rod 62 in motor 61, the rotating shaft of motor 61, and the end of the drive rod 62 is provided with
Gear 63, the motor 61 is controlled by the controller (not shown) in gas turbine.The adjustable plate 5 is provided with rack
51, elongated slot 52 is also provided with adjustable plate 5, and the rack 51 is arranged in elongated slot 52 along the length direction of elongated slot 52, the gear 63
It is meshed with the rack 51.During work：When motor 61 works, it is rotated with gear 63, and the driving adjustable plate 5 of gear 63 exists
Moved in stopper slot 32.The rotation direction of gear 63 can allow adjustable plate 5 to be moved to different directions when different, so as to adjust throttling
Compressed air in the openings of sizes in hole 31, control thrust-balancing chamber 41 enters the flow of bearing bore 42, so as to ensure combustion gas
The axial force balance of turbine unit.For the rotating speed of more preferable controlled motor 61, it is connected between the motor 61 and drive rod 62
Decelerator, by decelerator can effective controlled motor 61 rotating speed.Motor 61 in the present embodiment is in thrust-balancing chamber 41 1
Side, it is arranged on the packing ring 3.
Because the packing ring 3, the section of spindle nose 2 are circle, therefore in the present embodiment, as shown in figure 3, perpendicular to
On the direction of the axis of spindle nose 2, the section of the throttle orifice 31 is that circular arc, the stopper slot 32 are circular arc, the adjustable plate 5
For circular arc, by this structure adjustable plate 5 can be allowed reliablely and stablely to move, effectively the openings of sizes of control throttle orifice 31.
In addition, the width of throttle orifice 31 in the present embodiment is smaller, so that the chamber (He of thrust-balancing chamber 41 before and after throttle orifice 31
Bearing bore 42) pressure there is pressure differential；When introducing the compressed air for generator terminal of calming the anger by bleed chamber 11, compressed air, which enters, to be pushed away
Balance chamber 41 simultaneously acts on chamber wall generation axial thrust.
With reference to Fig. 2 and Fig. 3, air-tightness is ensured in order to ensure that adjustable plate 5 can be covered in continuously effective on throttle orifice 31
Well, the inwall of the stopper slot 32 is provided with spacing preiection 33, and adjustable plate 5 is limited in into stopper slot 32 by spacing preiection 33
In so that adjustable plate 5 and then it can move in a circumferential direction.
As shown in Fig. 2 comb tooth sealing gland 71 is provided between the packing ring 3 and spindle nose 2, between the packing ring 3 and spindle nose 2
Provided with brush seal 72.Overall sealing is ensured by comb tooth sealing gland 71 and brush seal 72.That is, packing ring 3
Comb tooth sealing gland 71 and the structure of brush seal 72 are provided between the outer wall of inwall and spindle nose 2.Brush seal 72 can effectively reduce due to
The pressure oscillation of thrust-balancing chamber 41 that gas turbine rotor vibration and abrasion etc. are brought.
With reference to such as Fig. 1-Fig. 3, when gas turbine complete machine axial force changes by the present invention to thrust-balancing chamber
Pressure in 41 is adjusted, and concrete operating principle is：
Thrust bearing (not shown) is provided with compressor side, the controller of controlled motor 61 is receiving thrust bearing
Temperature and load signal after instruction is sent to motor 61 so that gear 63 is rotated, gear 63 rotates driving rack 51 and entered
And change the position of adjustable plate 5, change the area coverage to throttle orifice 31 when adjustable plate 5 is moved, so as to control by throttle orifice
31 throughput, can thus carry out effective and stable regulation, accurately to the compressed air pressure in thrust-balancing chamber 41
The air supply that control thrust-balancing chamber 41 is flowed into, flowed out, adjusts pressure size, so as to ensure the axle of gas turbine unit
To dynamic balance.
In summary, the axial apparatus for adjusting force of gas turbine of the present invention, simple in construction, sealing property is reliable and can be accurate
Control compressed air require.So, the present invention effectively overcomes some practical problems of the prior art to have very high profit
With being worth and use meaning.
The principle and its effect of the above-mentioned embodiment only illustrative present invention, 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, art 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 (7)
1. it is provided with spindle nose in a kind of axial apparatus for adjusting force of gas turbine, including turbine bearing block (1), turbine bearing block (1)
(2), it is provided between turbine bearing block (1) and spindle nose (2) on journal bearing (10), the turbine bearing block (1) and is provided with bleed chamber
(11), it is characterised in that：The inwall of turbine bearing block (1) protrudes to form auxiliary section (12) to inner side, the auxiliary section (12) with
Packing ring (3) is provided between the spindle nose (2), the both sides of the packing ring (3) are thrust-balancing chamber (41) respectively and are used for
The bearing bore (42) of journal bearing (10) is placed, the bleed chamber (11) connects with the thrust-balancing chamber (41), the axle
Throttle orifice (31) is provided with seal ring (3), the throttle orifice (31) connects the thrust-balancing chamber (41) with bearing bore (42)；
Also include a mobilizable adjustable plate (5), the adjustable plate (5) can be covered on the throttle orifice of the packing ring (3) (31),
The position of the adjustable plate (5) is controlled by drive mechanism (6).
2. the axial apparatus for adjusting force of gas turbine according to claim 1, it is characterised in that：The end of the packing ring (3)
Stopper slot (32) is provided with face, throttle orifice (31) passes through stopper slot (32), and the adjustable plate (5) is located at the stopper slot (32)
In, the drive mechanism (6) includes being connected with drive rod (62), the drive rod (62) in motor (61), the rotating shaft of motor (61)
End be provided with gear (63), the adjustable plate (5) is provided with rack (51), and the gear (63) mutually nibbles with the rack (51)
Close.
3. the axial apparatus for adjusting force of gas turbine according to claim 2, it is characterised in that：Opened on the adjustable plate (5)
There is elongated slot (52), the rack (51) is arranged in elongated slot (52) along elongated slot (52) length direction.
4. the axial apparatus for adjusting force of gas turbine according to claim 2, it is characterised in that：The stopper slot (32) it is interior
Wall is provided with spacing preiection (33), and adjustable plate (5) is limited in stopper slot (32) by spacing preiection (33).
5. the axial apparatus for adjusting force of gas turbine according to claim 1, it is characterised in that：The packing ring (3) and axle
Comb tooth sealing gland (71) is provided between head (2).
6. the axial apparatus for adjusting force of gas turbine according to claim 1, it is characterised in that：The packing ring (3) and axle
Brush seal (72) is provided between head (2).
7. the axial apparatus for adjusting force of gas turbine according to claim 1, it is characterised in that：The throttle orifice (31) is vertical
In the section of spindle nose (2) axis be circular arc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550696.4A CN106014643B (en) | 2016-07-13 | 2016-07-13 | Gas turbine axial direction apparatus for adjusting force |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550696.4A CN106014643B (en) | 2016-07-13 | 2016-07-13 | Gas turbine axial direction apparatus for adjusting force |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106014643A CN106014643A (en) | 2016-10-12 |
| CN106014643B true CN106014643B (en) | 2017-08-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610550696.4A Active CN106014643B (en) | 2016-07-13 | 2016-07-13 | Gas turbine axial direction apparatus for adjusting force |
Country Status (1)
| Country | Link |
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| CN (1) | CN106014643B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106812798B (en) * | 2017-04-17 | 2019-04-23 | 南方科技大学 | Bearing and manufacturing method thereof |
| CN109990844B (en) * | 2019-04-24 | 2021-07-27 | 山东德浦泰管业科技有限公司 | Intelligent safety monitoring platform |
| CN112377272B (en) * | 2020-11-30 | 2024-04-19 | 浙江博旭新能源科技有限公司 | Centripetal turbine axial force adjusting device |
| CN112502832A (en) * | 2020-12-14 | 2021-03-16 | 至玥腾风科技集团有限公司 | Micro gas turbine with axial force balancing structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201461548U (en) * | 2009-07-30 | 2010-05-12 | 上海新沪电机厂有限公司 | Thrust regulating plate for pipeline shielding electric pump |
| US9617916B2 (en) * | 2012-11-28 | 2017-04-11 | Pratt & Whitney Canada Corp. | Gas turbine engine with bearing buffer air flow and method |
| CN103486087A (en) * | 2013-09-15 | 2014-01-01 | 丹东克隆先锋泵业有限公司 | Axial force balancing magnetic pump |
| CN204716308U (en) * | 2015-03-03 | 2015-10-21 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of turbine stub shaft bearing air system |
| CN205805735U (en) * | 2016-07-13 | 2016-12-14 | 上海电气燃气轮机有限公司 | A kind of gas turbine axial force adjustment structure |
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2016
- 2016-07-13 CN CN201610550696.4A patent/CN106014643B/en active Active
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| Publication number | Publication date |
|---|---|
| CN106014643A (en) | 2016-10-12 |
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