CN1474038A - Tiltable bush spring sheet assembly for gas turbine - Google Patents
Tiltable bush spring sheet assembly for gas turbine Download PDFInfo
- Publication number
- CN1474038A CN1474038A CNA031337392A CN03133739A CN1474038A CN 1474038 A CN1474038 A CN 1474038A CN A031337392 A CNA031337392 A CN A031337392A CN 03133739 A CN03133739 A CN 03133739A CN 1474038 A CN1474038 A CN 1474038A
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- China
- Prior art keywords
- gas turbine
- rotor
- spring
- watt
- spring lamination
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- 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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- Sliding-Contact Bearings (AREA)
- Support Of The Bearing (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The tiltable bush-spring sheet assembly for gas turbine has separated main bush and auxiliary bush supported onto the spring sheet assembly tiltably. The spring sheet assembly comprising several laminated spring sheets is used to balance the loads on different bushes caused by their tilt and unevenness. Via measuring the rigidity of each spring sheet, the rigidity of the laminated spring sheet assembly is calculated. During trial or running of the gas turbine, the spring sheet assembly is forced to deform, and measuring the axial displacement of the rotor can measure the axial force of the rotor.
Description
Affiliated technical field
The present invention relates to transmit in a kind of gas turbine of forming by gas compressor, firing chamber and turbine parts watt spring lamination that inclines of epitrochanterian pneumatic axial force.The gas compressor of gas turbine and turbine parts are formed stator by actionless casing and blade, also have the gas compressor of high speed rotating, the dish of turbine and the rotor that blade is formed.Rotor bearing is on radial sliding bearing, and the thrust disc of epitrochanterian pneumatic axial force by rotation is delivered on the static blocking type major-minor tilting-pad bearing and slides and be delivered to the elastic component that gas turbine stator casing gets on.
Background technique
Characteristics such as gas turbine not only has the cycle efficiency height, and is easy to operate, the needs of energy fast adaptation load variations in addition.Therefore carry to have obtained widely on booster station, chemical industry and the ship power at generating, natural gas and use.
Gas turbine generally is made up of gas compressor, firing chamber, turbine three big parts.Gas compressor is sent into the firing chamber after air is sucked supercharging, sprays into fuel oil in the firing chamber, and the high-temperature high-pressure fuel gas after the burning does work at turbine expansion.Gas turbine working medium produce power after thermodynamic cycle is used for driving various machine tool operations.
Gas turbine generally is made up of stationary components and Runner assembly (rotor).Stationary components comprises compressor casing and the tandem blade that is installed on it, firing chamber and combustion box, the tandem nozzle vane of turbine casing machine and top loading.Rotor is made up of wheel disc, the axle of gas compressor and turbine and tandem gas compressor and the turbine blade that is contained on the wheel disc.Acting on working medium on the blade of rotor and applying gas force on it, its tangent direction is tried hard to recommend moving rotor high-speed rotation, and axial direction power reaches the static casing of gas turbine with gas force merga pass thrust bearing on the dish and gets on.Along with combustion turbine power constantly increases, rotor quality constantly increases and to the requirement in gas turbine life-span, the bearing of support rotor adopts radial sliding bearing, and the thrust bearing of bearing axial pushing force adopts the blocking type major-minor watt thrust bearing that can incline more.
Can incline in the existing gas turbine and watt adopt the bias point supporting and adopt hinged beam lever principle to come each tile fragment load of autobalance, this supporting form complex structure, each tile fragment unbalance stress brings certain difficulty to the direction and the numerical value of detection rotor axial force.
Summary of the invention
The technical problem to be solved in the present invention is, in the gas turbine of the above-mentioned type, adopt a device, it can be in the load ricing that realizes on the rotor axial power reliable delivery basis between minimum tile fragment, and the direction and the numerical value of rotor axial power can utilize this device to measure gas turbine operation the time.
It is in comprising the gas turbine of being made up of static casing and rotor that the present invention solves technological scheme that its concrete technical problem adopts, rotor is supported on by the antero posterior axis neck on the sliding bearing that is located on the stator casing supporting element, transmits the quality and the uncompensated load of rotor.Epitrochanterian axial force is passed to the blocking type major and minor thrust bearing that can incline by being fixed on thrust disc on the rotor journal.Main thrust watt is placed in the main thrust face side of thrust disc, and secondary thrust bearing shoe valve is placed in the opposite side of thrust disc, and thrust bearing shoe valve is designed to tilting-type, and thrust bearing shoe valve rear support point is in the arc-shaped, and it is bearing on the special-purpose spring lamination.Spring lamination is by long-pending folded the forming of some board-like elastic components, it has certain rigid and its rigidity is adjustable, face of spring sheet contacts with watt back side circular arc that can incline, its another side leaves the spring assembly deformation space in the middle of being contained in the bearing casing, and can transmit axial force and to the stator casing, go, blocking type can incline and watt respectively have some to be distributed in the thrust disc both sides, and the every thrust bearing shoe valve back side all is lined with the spring lamination of a special use.
The present invention is based on following consideration, be that the rotor propulsion disc and the assembling back between watt tile fragment of can inclining are because processing and assembly error can produce inclination and uneven, tilt and uneven can making produces the inhomogeneous of load between week several thrust bearing shoe valves and influence the life-span of tile fragment and make bearing shell and the oil temperature rising, axial force can reach tens of tons, this inhomogeneous life-span and the reliability that will more influence the combustion machine on heavy duty gas turbine especially.
For this nonuniformity being reduced to minimum, make between tile fragment load be tending towards balanced in principle, designed long-pending folded formula spring assembly, thrust pad is supported on the spring lamination, the assembling error causes and not at ordinary times, spring sheet can absorb its deviation and reduce the inhomogeneous of all tile fragment load because of processing adds between thrust disc and tile fragment.This design can be reduced to tile fragment discontinuity degree minimum.
This invention is pointed out, the rigidity of the spring lamination under each tile fragment is consistent as far as possible, and design the rigidity of spring lamination according to the size of thrust loading, make the load ricing reduce to enough little level and do not cause rotor that too big axial displacement is arranged when gas turbine operation.
Inclination and uneven size directly influence the remaining unbalanced load between tile fragment between gas turbine rotor thrust disc and the tile, the rigidity of combustion machining and assembly quality and spring sheet are coordinated can reach the most satisfied design effect.
Some of special purpose spring chip modules are completed a set below the tile fragment that is placed on thrust disc one side, measure the comprehensive rigidity of good this cover grouped spring chip module, and draw distortion and load line figure, the numerical calculation of rotor shaft axial displacement goes out the direction and the numerical value of rotor axial power in the time of can utilizing this figure and gas turbine operation.
The beneficial effect of scheme of the present invention is to be to reduce blocking type the inhomogeneous of major-minor thrust bearing tile fragment load that can incline that slide by being placed in special purpose spring chip module below the thrust pad, the monitoring of the definite and bearing shell load of axial force when utilizing it to finish gas turbine operation simultaneously, do not influence former thrust can incline watt design performance and characteristics, simple in structure, be easy to realize the working life that to improve thrust-bearing.
Description of drawings
Fig. 1 is a spring assembly structural representation of the present invention.
Fig. 2 is that the present invention uses schematic representation on the gas turbine rotor axle.
1 gas turbine among the figure, 2 combustion machine casings, 3 rotor parts, 4 rotor shafts, 5 bearing casings, 6 radial sliding bearings, 7 thrust bearing shoe valve back side circular arc profiles, 8 main thrusts watt, 9 thrust discs, 10 secondary thrust bearing shoe valves, 11 spring shoe assemblies.
Embodiment
As shown in Figure 1, gas turbine (1) is made up of gas compressor, firing chamber and turbine, the power that turbine sends surplus power except that driving gas compressor is used for driving generator or other machine tool, wherein compressor casing, firing chamber and turbine casing (2) are actionless on gas turbine, and gas compressor and turbine rotating part are coiled by several, axle and blade are formed, and are arranged on the common rotor part (3), and epitrochanterian all parts are all around rotor spin axis high speed rotating.
There is axle (4) the rotor front end and back end of gas turbine, and rotor is supported on the static casing of gas turbine by radial sliding bearing on the antero posterior axis (6) and bearing casing (5), in order to transmit rotor quality power and rotation unbalanced force to static casing.
Be fixed with thrust disc (9) on the front axle of gas turbine rotor, epitrochanterian axial force passes to main thrust watt (8) or the secondary thrust bearing shoe valve (10) that is contained on the bearing casing (5) by it.The major-minor thrust bearing shoe valve is that blocking type can incline watt, and each is made up of some blocks of tiles, and the front of thrust bearing shoe valve is cast with wear-resisting Babbitt, and circular arc profile (7) is processed at the back side, and the tile fragment arc profile is supported on the spring lamination (11).The major-minor thrust bearing shoe valve back side all is placed with spring lamination, and a face of spring lamination contacts with tile fragment circular arc profile, and its another side contacts with the corresponding supporting surface of bearing casing (5), and the spring assembly deformation space is left in the centre.
Rate-of flow by gas turbine is along with combustion turbine power increases, the axial force that acts on the gas turbine rotor can reach several tons or tens of ton, epitrochanterian axial force will pass to the transfixion thrust pad by the thrust disc of high speed rotating during gas turbine work, again it being passed to static casing gets on, although between thrust disc and tile fragment, have lubricant film to separate, the operating conditions of thrust bearing shoe valve is still extremely abominable, its load is quite high, the processing and the assembly error of parts such as thrust disc again and tile fragment, can produce undesirable inclination and injustice between them, the size that these all will influence tile fragment load makes the inhomogeneous of load that these tile fragment spares bear.
By spring lamination being set at the major-minor thrust bearing shoe valve back side, can reduce since between the tile fragment of the inclination that causes of machining error and uneven generation load inhomogeneous, spring lamination is by long-pending folded the forming of some blocks of sheet metals, inclination between thrust disc and tile fragment absorbs by the different decrement of spring lamination with uneven, load difference between tile depends on the rigidity of spring lamination at this moment, spring plate rigidity hour is inhaled same inclination and otherwise uneven load missionary society is littler then big, therefore, need consider above-mentioned inclination and uneven size when decision spring lamination rigidity, rotor produces bigger axial displacement in the time of will considering also that rigidity can not be avoided gas turbine work too for a short time.
Some special-purpose of spring laminations are made into one group, measure the integral stiffness of this group spring sheet in advance, respectively put one group in the both sides of thrust disc during the gas turbine assembling, lay a fulcrum displacement transducer at the rotor axle head before the gas turbine test run, by measuring different operating mode axial displacements, can calculate the numerical value and the direction of gas turbine axial force according to the comprehensive rigidity of spring plate group.
Claims (3)
1, a kind of gas turbine is with watt spring lamination that can incline, the rotor element that includes high speed rotating is supported on the radial sliding bearing, the axial gas forces of bearing on the rotor is delivered on the static tile fragment by epitrochanterian thrust disc, it is characterized in that being provided with special-purpose spring lamination at the back side that the blocking type major-minor can incline watt, inhomogeneous in order to reduce between thrust pad load.
2, gas turbine according to claim 1 is with watt spring lamination that can incline, and it is characterized in that said spring lamination is foldedly to form and have certain rigidity by some Steel Spring Plates are long-pending.
3, according to claim 1,2 described gas turbines with watt spring lamination that can incline, it is characterized in that having fixing integral stiffness after spring sheet is made in groups spring lamination, on the gas turbine rotor axle head, be provided with the axial displacement sensor, can measure the numerical value and the direction of the axial force of gas turbine rotor according to the spring plate group integral stiffness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA031337392A CN1474038A (en) | 2003-07-16 | 2003-07-16 | Tiltable bush spring sheet assembly for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA031337392A CN1474038A (en) | 2003-07-16 | 2003-07-16 | Tiltable bush spring sheet assembly for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1474038A true CN1474038A (en) | 2004-02-11 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA031337392A Pending CN1474038A (en) | 2003-07-16 | 2003-07-16 | Tiltable bush spring sheet assembly for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1474038A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1897417B (en) * | 2005-06-30 | 2011-08-03 | 马里芬贝黑尔私人有限公司 | Shaftless propeller |
| CN103032464A (en) * | 2012-11-30 | 2013-04-10 | 上海电气电站设备有限公司 | Tilting pad structure of generator |
| CN104062105A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Fatigue cycling test device of first-stage disk of high-pressure compressor of aircraft engine |
| CN106812626A (en) * | 2017-01-19 | 2017-06-09 | 中国航发沈阳发动机研究所 | Contain casing outside a kind of engine |
| CN109505860A (en) * | 2019-01-14 | 2019-03-22 | 中国船舶重工集团公司第七0三研究所 | A kind of butterfly spring support tilting thrust bearing |
| CN114510798A (en) * | 2022-01-25 | 2022-05-17 | 中国航发沈阳发动机研究所 | Pneumatic axial force error-proofing analysis method for aircraft engine |
-
2003
- 2003-07-16 CN CNA031337392A patent/CN1474038A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1897417B (en) * | 2005-06-30 | 2011-08-03 | 马里芬贝黑尔私人有限公司 | Shaftless propeller |
| CN103032464A (en) * | 2012-11-30 | 2013-04-10 | 上海电气电站设备有限公司 | Tilting pad structure of generator |
| CN103032464B (en) * | 2012-11-30 | 2015-10-07 | 上海电气电站设备有限公司 | A kind of generator tilting bush structure |
| CN104062105A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Fatigue cycling test device of first-stage disk of high-pressure compressor of aircraft engine |
| CN106812626A (en) * | 2017-01-19 | 2017-06-09 | 中国航发沈阳发动机研究所 | Contain casing outside a kind of engine |
| CN106812626B (en) * | 2017-01-19 | 2019-06-28 | 中国航发沈阳发动机研究所 | Contain casing outside a kind of engine |
| CN109505860A (en) * | 2019-01-14 | 2019-03-22 | 中国船舶重工集团公司第七0三研究所 | A kind of butterfly spring support tilting thrust bearing |
| CN114510798A (en) * | 2022-01-25 | 2022-05-17 | 中国航发沈阳发动机研究所 | Pneumatic axial force error-proofing analysis method for aircraft engine |
| CN114510798B (en) * | 2022-01-25 | 2023-07-21 | 中国航发沈阳发动机研究所 | Aeroengine pneumatic axial force error-proofing analysis method |
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