CN103982248A - Blade type sealing device having clearance control function - Google Patents
Blade type sealing device having clearance control function Download PDFInfo
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- CN103982248A CN103982248A CN201410217589.0A CN201410217589A CN103982248A CN 103982248 A CN103982248 A CN 103982248A CN 201410217589 A CN201410217589 A CN 201410217589A CN 103982248 A CN103982248 A CN 103982248A
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Abstract
The invention discloses a blade type sealing device having a clearance control function. The blade type sealing device having the clearance control function is installed on stators which are arranged at the periphery of a rotor and comprises an upstream ring, a blade assembly, a downstream ring and a control ring; the blade assembly is arranged between the upstream ring and the downstream ring; the control ring is adjacent to the downstream ring. The blade type sealing device having the clearance control function has the advantages of being applied to various rotary machinery and particularly applied to devices such as an aircraft engine and a gas turbine, rapidly responding to device states and adjusting sealing clearance, allowing a sealing device and the rotor being in collision for a short time and not influencing the sealing performance and enabling the devices to operate in an economic state for a long time.
Description
Technical field
The present invention relates to vane sealing device, be particularly useful on the high-speed rotating machine such as aeroengine, gas turbine.
Background technique
Sealing technique has a very important role in modern industry production and scientific technological advance.No matter to improve scientific technological advance and industrial production technology level, or aspect technical innovation and Plant reconstruction plant modernization and renewal, sealing technique all in occupation of consequence with bearing key player.This sentences aeroengine is example, and the significance of sealing technique is described.
As everyone knows, no matter for military aero-engine or civil aviation motor, sealing technique directly affects the performance of motor.Sprue flow leakage directly affects the efficiency of the each parts of motor; And for air system, sealing technique is the key technology of its success or failure especially.
The research in U.S. Louis research center thinks, the return that the more advanced sealing technique of exploitation is brought is huge.For commercial aircraft, can reduce the direct operating expense of large motor 3%, the direct operating expense of region motor 5%, can reduce by 10% fuel consumption, the NOx discharge amount that exceedes 50% can be reduced, 7dB noise (being equivalent to reduce 3/4 acoustic energy) can be reduced.In addition, increase because the leakage of air system Secondary Flow sealing can make cavity temperature in motor, and then cause each component performance to reduce, therefore, more advanced sealing technique can also significantly reduce the maintenance cost in lifetime, extends the working life of each component.
The sealing of design is numerous in aeroengine, and this sentences high-pressure turbine blade tip and is sealed into example and illustrates and control significance and the present Research of seal clearance in aeroengine.
Research shows, the every minimizing of high-pressure turbine tip clearance 0.254mm (0.01in), and fuel consumption rate approximately reduces by 1%, and delivery temperature approximately reduces 10 DEG C.Due to the reduction of delivery temperature, can significantly increase the working life of each parts.
When in the accelerating process of motor from slow train to maximum (top) speed, because rotor has exceeded the radial extent amount of casing under heat load in the distortion under mechanical load, tip clearance declines rapidly, occurs a minimum value; In the time of cruising condition, it is basicly stable that rotating speed has reached, and it is saturated that the thermal response of turbine is also tending towards, and along with the rising gradually of casing temperature, it is large that tip clearance also slowly becomes.In the time of engine retard, just the opposite when the variation tendency of tip clearance curve and acceleration; When thrust reversing rating, motor accelerates to make tip clearance to reach minimum again; Take off with land process in, can there is respectively the state point of gap minimum value, the most easily touch the point of mill.
Analysis based on above-mentioned tip clearance at an aerial mission internal clearance variation characteristic, develops a kind of seal arrangement with gap control function and seems particularly important.Prior art is mainly to control tip clearance by cooling casing, and this technology is grasped and applied by the external aeroengine MANUFACTURER of part, but domestic research and application are subject to the restriction of foreign patent barrier, make progress comparatively slow.
In addition, due to control by cooling casing the technology of tip clearance exist speed of response slow, from the bleed of fan or gas compressor to deficiencies such as engine performance have a negative impact, scientific research personnel is finding the approach of the active gap control technology of response fast that realizes always both at home and abroad at present, but some conceptual researchs are mostly just carried out, the further investigation of special topic is also nowhere near, and lacks especially the technological scheme that is easy to realization.
In fact, not only, in aeroengine, on other a lot of high-speed rotating machines, seal clearance is all along with the change of equipment state changes.But conventional technological scheme is sealed into master with comb tooth, seal clearance cannot be adjusted in the equipment operation stage, can only reserve enough large seal clearance in the Installation and Debugging stage, and the equipment that ensures in theory does not touch mill under any state.But in practical application, high-speed rotating machine still often can run into some uncertain instantaneous pernicious operating modes, the comb tooth sealing generation short time is touched mill, and seal clearance can permanently expand.
Summary of the invention
The object of this invention is to provide the vane sealing device with gap control function, be applied on various rotating machineries, be particularly useful on the equipment such as aeroengine, gas turbine, can be according to equipment operation state capable of automatic regulating gap, and belong to a kind of flexible sealing, once contacting with rotor can elastic yield, the permanent expansion of touching mill and can not cause seal clearance of short time.
For achieving the above object, technological scheme of the present invention is:
There is the vane sealing device of gap control function, be arranged on the stator of rotor periphery, comprise lantern, blade assembly, lower lantern and control ring; Blade assembly is installed between lantern and lower lantern; Control ring is adjacent with lower lantern.
Above-mentioned upper lantern, blade assembly, lower lantern and control ring set gradually along axial flow direction, and axial flow direction is the direction that low voltage side is pointed in high pressure side.
Above-mentioned blade assembly comprises the above blade element of a slice, and each blade element is along circumferentially evenly distributed, and blade element one end is fixed end, and the other end is free end, and free end forms sealing endoporus.
In the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 0～60 °; Along axial flow direction, the axial angle of above-mentioned blade element and rotor is 0～45 °; Between above-mentioned blade element free end and lower lantern, be provided with the axial clearance of 0～1mm.
Above-mentioned control ring comprises support end face, and can move vertically relative to blade element free end, supports end face and blade element and is oppositely arranged.Without under differential pressure conditions, the spacing supporting between end face and blade element free end side is adjustable; In practical application, due to the effect of pressure reduction, blade element is to low voltage side resiliently deformable, blade element free end with support end face with control ring and lean, above-mentioned elastic deformation amount is determined by the axial position of control ring.
Moving axially of above-mentioned control ring can realize by multiple technologies scheme, comprises Mechanical Driven mode, pressure-driven mode, hot driving mode and the mode that combines etc., as long as can drive control ring to move axially.In order to improve the speed of response of gap control, and save the installing space of seal arrangement, above-mentioned control ring is preferably realized and being moved axially by pressure-driven mode.
Above-mentioned gap control function is that in the sealing by regulating some blade element free ends formation, hole size is realized; Above-mentioned control ring moves toward high pressure side, and sealing endoporus expands; Move toward low voltage side, sealing endoporus dwindles.
Claimant finds after deliberation, and above-mentioned control ring moves toward low voltage side, and when blade element is out of shape to low voltage side, blade element and rotor radial angle can diminish, and make to seal endoporus and dwindle, otherwise sealing endoporus expands.
The above-mentioned vane sealing device with gap control function also comprises expansion bend, and expansion bend one end connects stator, and the other end connects control ring.
Above-mentioned expansion bend can be adjusted length vertically, drives control ring to move axially, and then makes seal clearance obtain rationally adjusting in time, reduces and reveals.Above-mentioned axial finger rotary machine rotor axially.
Preferably, also comprise and drive the flexible drive system of expansion bend, drive control ring to move vertically.Drive system comprises pressure controller, high-pressure air source, pressurizing valve, pressure setting chamber and reduction valve, one end, pressure setting chamber communicates with expansion bend, the other end is communicated with high-pressure air source, and pressure controller, pressurizing valve and reduction valve are located at the connectivity part of pressure setting chamber and high-pressure air source.
Above-mentioned expansion bend is more than one, preferably, along circumferentially uniform 4 expansion bends of seal arrangement, is located at respectively position, upper and lower, left and right, adjusts respectively the length of expansion bend according to clearance measurement situation, can adjust respectively the seal clearance of corresponding position.
Adopt technique scheme, even if equipment moves under eccentric state, also can in the equipment operation phase, by adjusting the expansion bend of diverse location, to realize sealing endoporus concentric with rotor, not only realize efficient sealedly, and can suppress the problems such as flow-induced vibration that bias brings.
Expansion bend is the cavity structure with expansion joint, and expansion bend is provided with suction port, is communicated with the drive system that drives expansion bend on suction port.
Preferably, the sealing of expansion bend one end, the other end are provided with suction port, are provided with expansion joint between two end part.
Above-mentioned drive system is carried out the length of regulation telescopic unit by gas pressure in adjusting cavity.
Above-mentioned blade assembly comprises screening flow, hides flow and is located between blade element upstream, upper lantern and blade element, and blade element free end exceeds screening flow.
Preferably, above-mentioned screening flow inward flange is radially provided with and cracks.Arrange along periphery of rotor circular that be shaped as that hides flow entirety, adopts technique scheme can make to hide flow and can fit with blade element side under axial pressure difference effect.Above-mentioned inward flange refers to hide the inner diameter location of flow, and cracking is along being radially to open toward the direction of external diameter from hiding flow internal diameter.
Preferably, adjacent two angles between cracking are 3～30 °.
The setting of above-mentioned screening flow is in order to have reduced the leakage between blade element, and has strengthened the structure stability of blade element under unstable airflow function.
For further lift-off seal performance, screening flow arranges two-layer vertically, stacked setting, and cracking of two-layer screening flow staggered.
Preferably, above-mentioned screening flow is welded in lantern, and is clamped between lantern and blade element fixed end.
In order to adapt to above-mentioned blade assembly internal-and external diameter difference, blade assembly also comprises distance piece, distance piece is located at the fixed end of blade element, every one or more blade element settings, the thickness of distance piece and quantity had both needed to ensure that blade element free end was not crowded, needed again to ensure that blade element free end is enough closely knit, at blade element free end, between each blade element, can mutually cover gap, leakage is reduced to the level that approaches zero.
Preferably, above-mentioned radially angle is 30～50 °, and above-mentioned axial angle is 15～35 °, and the axial clearance between blade element free end and lower lantern is 0.2～0.8mm.
Claimant finds after deliberation, in sealing, the adjustment amount of hole size is mainly determined by the axial clearance between blade element and rotor radial angle, axially angle and blade element free end and lower lantern, adjust above-mentioned axial clearance by control ring and can reach the object of adjusting hole size in sealing, and then obtain the seal clearance of expection.The adjustment of above-mentioned axial clearance is easy to realize.
Preferably, blade assembly also comprises front plate and rear plate, and blade element and distance piece are located between front plate and rear plate, and front plate and rear plate are located between lantern and lower lantern.Be convenient to like this easy-maintenance of manufacturing and increase seal arrangement.
Preferably, blade element and distance piece are welded between front plate and rear plate, and blade assembly is clamped between lantern and lower lantern, and upper lantern and lower lantern are fixed by the mode of welding; Further preferably, upper lantern, blade assembly and downstream ring are welded as a whole.
Preferably, the thickness of blade element is 0.05～0.3mm, and distance piece thickness is 0.03～0.1mm, hides flow thickness 0.1～0.5mm.
Preferably, above-mentioned blade element, distance piece and screening flow all select sheet metal to make.
The NM technology of the present invention is prior art.
Above-mentioned seal arrangement is applied to sealing place of aeroengine high-pressure turbine blade tip, is installed in stator conduit.Taking off and land state, expansion bend is shorter, and seal clearance is larger; In aircraft cruising condition, expansion bend is longer, and seal clearance diminishes, and reduces and leaks, capable of saving fuel oil.
The present invention has the vane sealing device of gap control function, not only response apparatus state adjust seal clearance fast, and allow the seal arrangement short time not affect sealability with Rub-impact, equipment is moved in more economic state for a long time.
Brief description of the drawings
Fig. 1 adopts the aeroengine tip clearance of traditional comb tooth sealing at an aerial mission internal clearance variation characteristic curve.
Fig. 2 is the radially section of vane sealing device and the assembly structure schematic diagram of equipment rotor and stator that the embodiment of the present invention 1 has gap adjustment function, and in figure, seal clearance is in the upper limit.
Fig. 3 is that the vane sealing device that the embodiment of the present invention 1 has a gap adjustment function is fixed in stator conduit and the schematic diagram coordinating with rotor, and in figure, seal clearance is in lower limit.
Fig. 4 is that the embodiment of the present invention 1 seal clearance is in the upper view of blade element in limited time.
Fig. 5 is that the embodiment of the present invention 1 seal clearance is in the lower view of blade element in limited time.
Fig. 6 is the installing orientation schematic diagram of blade element, distance piece and the screening flow of the embodiment of the present invention 1.
Fig. 7 is the circumferential installation position schematic diagram of the expansion bend of the embodiment of the present invention 1.
Fig. 8 is the schematic diagram of the drive system of the embodiment of the present invention 1.
Fig. 9 adopts the achieved aeroengine tip clearance of the embodiment of the present invention 1 at an aerial mission internal clearance variation characteristic curve.
Figure 10 is that the expansion bend of the embodiment of the present invention 2 is in shortening the structural representation of state.
Figure 11 is that the expansion bend of the embodiment of the present invention 2 is in the structural representation of elongation state.
In figure, 1 for having the vane sealing device of gap control function, 2 is stator, 3 is rotor, 4 is air-flow, 11 is upper lantern, 12 is blade assembly, 13 is lower lantern, 14 is control ring, 15 is expansion bend, 15a is the expansion bend of shortening state, 15b is the expansion bend of elongation state, 16 is drive system, 21 is stator conduit, 120 is blade element free end, 121 blade elements, 121a is free state blade element, 121b is elastic deformation blade element, 122 is distance piece, 123 for hiding flow, 124 for cracking, 125 is sealing endoporus, 141 for supporting end face, 151 is left side expansion bend, 152 is upside expansion bend, 161 is pressure controller, 162 is high-pressure air source, 163 is pressurizing valve, 164 is pressure setting chamber, 165 is reduction valve, c1 is the seal clearance upper limit, c2 is seal clearance lower limit, x1 is high pressure side, x2 is low voltage side, A is takeoff condition, B is cruising condition, C is land state, D is for slowing down, E oppositely accelerates, F is for easily touching mill point, H is gap adjustment amount, X is axial, Y is for radially, R is sense of rotation.
Embodiment
Embodiment 1
There is the vane sealing device of gap control function, comprise lantern, blade assembly, lower lantern, control ring, expansion bend and drive system; Blade assembly is embedded between lantern and lower lantern; Control ring is adjacent with lower lantern; Expansion bend one end connects stator, and the other end connects control ring; Drive system can drive expansion bend flexible.
Above-mentioned expansion bend is circumferentially evenly equipped with 4 along seal arrangement, is located at respectively position, upper and lower, left and right, adjusts respectively the length of expansion bend according to clearance measurement situation, can adjust respectively the seal clearance of corresponding position.The variable quantity of above-mentioned expansion bend length and the adjustment amount of seal clearance are substantially linear.
Expansion bend is the cavity structure with expansion joint, and expansion joint is concave, and the sealing of expansion bend one end, the other end are provided with suction port, and expansion joint is located between two end part.Above-mentioned drive system adjustable and retractable device internal pressure, and then reach the object of regulation telescopic unit length.
Above-mentioned drive system comprises pressure controller, high-pressure air source, pressurizing valve, pressure setting chamber and reduction valve.Pressure controller regulates respectively pressurizing valve and reduction valve, can regulate the pressure in pressure setting chamber, and pressure setting chamber is connected with expansion bend, and the pressure of expansion bend inner chamber is also adjusted thereupon.
Blade assembly comprises blade element, distance piece, front plate, rear plate and screening flow; Blade element has more than two, and blade element one end is fixed end, and the other end is free end; Distance piece is located between the fixed end of blade element; Blade element and distance piece are located between front plate and rear plate, and front plate and rear plate are located between lantern and lower lantern.
Hiding flow is located between blade element upstream, upper lantern and blade element; The free end of blade element exceeds control ring and hides flow.
Hiding flow inward flange is radially provided with and cracks; Adjacent two angles between cracking are 10 °.
In the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 40 °; Along axial flow direction, the axial angle of above-mentioned blade element and rotor is 20 °; Between blade element free end and lower lantern, be provided with the axial clearance of 0.25mm.The thickness of blade element is 0.1mm, and distance piece thickness is 0.06mm, hides flow thickness 0.3mm.
Through calculating, adopt above-mentioned design parameter, the every elongation of expansion bend 0.1mm, seal clearance reduces about 0.18mm, and the controlled variable of seal clearance is about 0.45mm.
Embodiment 2
Substantially the same manner as Example 1, difference is: the expansion joint of expansion bend is outer convex type; Hiding the angle of flow adjacent two between cracking is 3 °, and two hide the stacked settings of flow, cracks and mutually staggers.In the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 30 °; Along axial flow direction, the axial angle of above-mentioned blade element and rotor is 20 °; Between blade element free end and lower lantern, be provided with the axial clearance of 0.5mm.The thickness of blade element is 0.08mm, and distance piece thickness is 0.03mm, hides flow thickness 0.1mm.
Through calculating, adopt above-mentioned design parameter, the every elongation of expansion bend 0.1mm, seal clearance reduces about 0.14mm, and the controlled variable of seal clearance is about 0.7mm.
Embodiment 3
Substantially the same manner as Example 1, difference is: hiding the angle of flow adjacent two between cracking is 30 °; In the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 52 °; Along axial flow direction, the axial angle of above-mentioned blade element and rotor is 27 °; Between blade element free end and lower lantern, be provided with the axial clearance of 0.6mm; The thickness of blade element is 0.3mm, and distance piece thickness is 0.1mm, hides flow thickness 0.5mm.
Through calculating, adopt above-mentioned design parameter, the every elongation of expansion bend 0.1mm, seal clearance reduces about 0.17mm, and the controlled variable of seal clearance is about 1mm.
Above-described embodiment does not limit the present invention in any form, and all employings are equal to replaces or technological scheme that the mode of equivalent transformation obtains, all drops in protection scope of the present invention.
Claims (10)
1. there is the vane sealing device of gap control function, be arranged on the stator of rotor periphery, it is characterized in that: comprise lantern, blade assembly, lower lantern and control ring; Blade assembly is installed between lantern and lower lantern; Control ring is adjacent with lower lantern.
2. the vane sealing device with gap control function as claimed in claim 1, is characterized in that: above-mentioned control ring comprises support end face, and can move vertically relative to blade element free end, supports end face and blade element and is oppositely arranged.
3. the vane sealing device with gap control function as claimed in claim 1, is characterized in that: also comprise expansion bend, expansion bend one end connects stator, and the other end connects control ring.
4. the vane sealing device with gap control function as claimed in claim 3, is characterized in that: expansion bend has four, circumferentially uniform along seal arrangement, is located at respectively position, upper and lower, left and right.
5. the vane sealing device with gap control function as described in claim 1～4 any one, is characterized in that: blade assembly comprises blade element, distance piece and screening flow; Blade element has more than two, and blade element one end is fixed end, and the other end is free end; Distance piece is located between the fixed end of blade element; Hiding flow is located between blade element upstream, upper lantern and blade element.
6. the vane sealing device with gap control function as claimed in claim 5, is characterized in that: the free end of blade element exceeds control ring and hides flow.
7. the vane sealing device with gap control function as described in claim 3 or 4, is characterized in that: expansion bend is the cavity structure with expansion joint, and expansion bend is provided with suction port, is communicated with the drive system that drives expansion bend on suction port; Drive system comprises pressure controller, high-pressure air source, pressurizing valve, pressure setting chamber and reduction valve, one end, pressure setting chamber communicates with expansion bend, the other end is communicated with high-pressure air source, and pressure controller, pressurizing valve and reduction valve are located at the connectivity part of pressure setting chamber and high-pressure air source.
8. the vane sealing device with gap control function as claimed in claim 5, is characterized in that: hide flow inward flange and be radially provided with and crack, adjacent two angles between cracking are 3～30 °.
9. the vane sealing device with gap control function as claimed in claim 8, is characterized in that: between upper lantern and blade element, be provided with two and hide flow, stacked setting, cracks and mutually stagger.
10. the vane sealing device with gap control function as claimed in claim 5, is characterized in that: in the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 0～60 °; Along axial flow direction, the axial angle of above-mentioned blade element and rotor is 0～45 °; Between above-mentioned blade element free end and lower lantern, be provided with the axial clearance of 0～1mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410217589.0A CN103982248B (en) | 2014-05-21 | 2014-05-21 | There is the vane sealing device of gap control function |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410217589.0A CN103982248B (en) | 2014-05-21 | 2014-05-21 | There is the vane sealing device of gap control function |
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| CN103982248A true CN103982248A (en) | 2014-08-13 |
| CN103982248B CN103982248B (en) | 2016-04-06 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112096880A (en) * | 2020-09-11 | 2020-12-18 | 东台市光明机械密封有限公司 | Sealing gap control method of non-contact mechanical seal |
| CN112112968A (en) * | 2020-09-23 | 2020-12-22 | 中国航发沈阳发动机研究所 | Combined type non-contact seal structure |
| CN114278401A (en) * | 2020-09-28 | 2022-04-05 | 中国航发商用航空发动机有限责任公司 | Turbine casing of turbine engine and turbine engine |
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| CN203835470U (en) * | 2014-05-21 | 2014-09-17 | 南京博沃科技发展有限公司 | Blade type sealing device with clearance control function |
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| US5344284A (en) * | 1993-03-29 | 1994-09-06 | The United States Of America As Represented By The Secretary Of The Air Force | Adjustable clearance control for rotor blade tips in a gas turbine engine |
| JPH10253646A (en) * | 1997-03-07 | 1998-09-25 | Nippon Seiko Kk | Sensor mounting part for rolling bearing unit with rotational-speed detecting device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112096880A (en) * | 2020-09-11 | 2020-12-18 | 东台市光明机械密封有限公司 | Sealing gap control method of non-contact mechanical seal |
| CN112112968A (en) * | 2020-09-23 | 2020-12-22 | 中国航发沈阳发动机研究所 | Combined type non-contact seal structure |
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| CN114278401B (en) * | 2020-09-28 | 2024-04-26 | 中国航发商用航空发动机有限责任公司 | Turbine casing of turbine engine and turbine engine |
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| CN103982248B (en) | 2016-04-06 |
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Inventor after: Shi Weiwei Inventor after: Wei Hongqi Inventor after: Wang Lili Inventor after: Xu Jian Inventor before: Shi Weiwei Inventor before: Wei Hongqi Inventor before: Wang Lili |
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Effective date of registration: 20160905 Address after: 210019, room 1517, Tak Ying building, 118 Jiangdong Road, Jianye District, Jiangsu, Nanjing Patentee after: NANJING TIANCHENGHENG TECHNOLOGY CO., LTD. Address before: 210036 Nanjing, Gulou District, Jiangsu Phoenix West Street, building 150, room 3, No. 105 Patentee before: Nanjing Bowo Technology Development Co., Ltd. |