CN103982248B - There is the vane sealing device of gap control function - Google Patents
There is the vane sealing device of gap control function Download PDFInfo
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- CN103982248B CN103982248B CN201410217589.0A CN201410217589A CN103982248B CN 103982248 B CN103982248 B CN 103982248B CN 201410217589 A CN201410217589 A CN 201410217589A CN 103982248 B CN103982248 B CN 103982248B
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Abstract
The present invention has the vane sealing device of gap control function, is arranged on the stator of rotor periphery, comprises lantern, blade assembly, lower lantern and control ring; Blade assembly is installed between lantern and lower lantern; Control ring is adjacent with lower lantern.The present invention can be applicable on various rotating machinery, be particularly useful on the equipment such as aeroengine, gas turbine, not only can response apparatus state adjust seal clearance fast, and allow seal arrangement short time and Rub-impact and do not affect sealability, make equipment be in more economic state operation 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 is produced at modern industry and is had a very important role in scientific technological advance.No matter improve scientific technological advance and industrial production technology level, or in technical innovation and Plant reconstruction plant modernization and renewal, sealing technique all in occupation of consequence with carry 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 engine, sealing technique directly affects the performance of motor.Sprue flow leakage directly affects the efficiency of each parts of motor; And for air system, the key technology of sealing technique its success or failure especially.
The research in U.S. Louis research center is thought, the return that the more advanced sealing technique of exploitation is brought is huge.For commercial aircraft, the direct operating expense of large motor 3% can be reduced, the direct operating expense of region motor 5%, the fuel consumption of 10% can be reduced, the NOx discharge of 50% can be decreased beyond, 7dB noise (being equivalent to the acoustic energy of minimizing 3/4) can be reduced.In addition, because the leakage of air system Secondary Flow sealing can make engine inner chamber temperature increase, and then each component performance is caused to reduce, therefore, more advanced sealing technique significantly can also 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 the significance of seal clearance in aeroengine and present Research.
Research shows, high-pressure turbine tip clearance often reduces 0.254mm (0.01in), and fuel consumption rate about reduces by 1%, and delivery temperature about reduces 10 DEG C.Due to the reduction of delivery temperature, the working life of each parts significantly can be increased.
When in the accelerating process of motor from slow train to maximum (top) speed, because rotor has deformed more than the radial extent amount of casing under heat load under mechanical load, tip clearance has declined rapidly, occurs a minimum value; When cruising condition, rotating speed has reached basicly stable, and the thermal response of turbine is also tending towards saturated, and along with the rising gradually of casing temperature, tip clearance also slowly becomes large.When engine retard, just the opposite when the variation tendency of tip clearance curve and acceleration; During thrust reversing rating, motor accelerates to make tip clearance reach minimum again; Taking off with in land process, the state point of gap minimum value can be there is respectively, namely the most easily touch the point of mill.
Based on the analysis of above-mentioned tip clearance at an aerial mission internal clearance variation characteristic, develop a kind of seal arrangement with gap control function and seem particularly important.Prior art mainly controls tip clearance by cooling casing, this technology grasp by the external aero engine manufacturers of part and apply, but domestic research and apply is subject to the restriction of foreign patent barrier, is in progress comparatively slow.
In addition, due to the technology controlling tip clearance by cooling casing 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 clearance control technique realizing response fast always both at home and abroad at present, but mostly just carry out some conceptual researchs, the further investigation of special topic is also nowhere near, and lacks the technological scheme being easy to realize especially.
In fact, not only in aeroengine, on other a lot of high-speed rotating machine, seal clearance is all along with the change of equipment state changes.But conventional technological scheme is sealed into master with comb tooth, and seal clearance cannot adjust in the equipment operation stage, and can only reserve enough large seal clearance in the Installation and Debugging stage, the equipment that ensures in theory does not touch mill under being in 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 touches mill, and namely 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 machinery, be particularly useful on the equipment such as aeroengine, gas turbine, can according to equipment operation state automatic regulating gap, and belong to a kind of flexible sealing, once can elastic yield with rotor contact, the short time touch the permanent expansion that mill can not cause seal clearance.
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 axially airflow direction set gradually, 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 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 °; Axially airflow direction, the axial angle of above-mentioned blade element and rotor is 0 ~ 45 °; The axial clearance of 0 ~ 1mm is provided with between above-mentioned blade element free end and lower lantern.
Above-mentioned control ring comprises support end face, and can move vertically by relative vane element free end, and support end face and blade element are oppositely arranged.Without under differential pressure conditions, the spacing supported between end face and blade element free end side is adjustable; In practical application, due to the effect of pressure reduction, blade element to low voltage side resiliently deformable, blade element free end with support end face with control ring and lean, namely above-mentioned elastic deformation amount is determined by the axial position of control ring.
Moving axially of above-mentioned control ring realizes by multiple technologies scheme, the mode etc. comprising Mechanical Driven mode, pressure-driven mode, thermal drivers mode and combine, as long as can move axially by drived control ring.In order to improve the speed of response of gap control, and save the installing space of seal arrangement, above-mentioned control ring realizes moving axially preferably by pressure-driven mode.
Above-mentioned gap control function is that in the sealing by regulating some blade element free ends to be formed, hole size realizes; Above-mentioned control ring moves toward high pressure side, and sealing endoporus expands; Move toward low voltage side, sealing endoporus reduces.
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 sealing endoporus is reduced, 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, the other end connection control ring.
Above-mentioned expansion bend can adjust length vertically, and drived control ring moves axially, and then makes seal clearance obtain timely Reasonable adjustment, reduces and reveals.Above-mentioned axis refers to the axis of rotary machine rotor.
Preferably, also comprise the drive system driving expansion bend flexible, namely drived control ring moves 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 uniform 4 expansion bends of seal arrangement circumference, is located at position, upper and lower, left and right respectively, adjusts the length of expansion bend according to clearance measurement situation respectively, can adjust the seal clearance of corresponding position respectively.
Adopt technique scheme, even if equipment runs under being in eccentric state, also can by adjusting the expansion bend of diverse location, to realize sealing endoporus concentric with rotor in the equipment operation phase, not only achieve efficient sealed, and the problem such as the flow-induced vibration that bias can be suppressed to bring.
Expansion bend is the cavity structure of band expansion joint, and expansion bend is provided with suction port, suction port is communicated with the drive system driving expansion bend.
Preferably, expansion bend one end is closed, the other end is provided with suction port, is provided with expansion joint between two end part.
Above-mentioned drive system carrys out the length of regulation telescopic unit by regulating gas pressure in cavity.
Above-mentioned blade assembly comprises screening flow, and flow is located at blade element upstream, between upper lantern and blade element, blade element free end exceeds screening flow in screening.
Preferably, above-mentioned screening flow inward flange is radially provided with and cracks.The shape hiding flow entirety be along periphery of rotor arrange circular, adopt technique scheme that screening flow can be made to fit with blade element side under axial pressure difference effect.Above-mentioned inward flange refers to the inner diameter location hiding flow, and namely cracking is be radially open from screening flow internal diameter toward the direction of external diameter.
Preferably, adjacent two crack between angle be 3 ~ 30 °.
The setting of above-mentioned screening flow is the leakage in order to reduce between blade element, and enhances the structure stability of blade element under unstable airflow function.
In order to further lift-off seal performance, hide flow and arrange two-layer vertically, stacked setting, and two-layer cracking of screening flow is 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, arrange every one or more blade element, the thickness of distance piece and quantity had both needed to ensure that blade element free end is not crowded, needed again to ensure that blade element free end is enough closely knit, at blade element free end, mutually gap can be covered, leaking the level be reduced to close to zero between each blade element.
Preferably, above-mentioned radial 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 determined primarily of blade element and the axial clearance between rotor radial angle, axial angle and blade element free end and lower lantern, adjust by control ring the object that above-mentioned axial clearance can reach hole size in adjustment 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 the easy-maintenance of manufacturing and increase seal arrangement like this.
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, saving fuel oil.
The present invention has the vane sealing device of gap control function, not only can response apparatus state adjust seal clearance fast, and allows seal arrangement short time and Rub-impact and do not affect sealability, makes equipment be in more economic state operation for a long time.
Accompanying drawing explanation
Fig. 1 adopts the aeroengine tip clearance of traditional comb tooth sealing at an aerial mission internal clearance variation characteristic curve.
Fig. 2 is that the embodiment of the present invention 1 has the radial section of the vane sealing device of gap adjustment function and the assembly structure schematic diagram of equipment rotor and stator, and in figure, seal clearance is in the upper limit.
Fig. 3 be vane sealing device that the embodiment of the present invention 1 has a gap adjustment function to be fixed in stator conduit and with the schematic diagram of rotor engagement, in figure, seal clearance is in lower limit.
Fig. 4 is the view that the embodiment of the present invention 1 seal clearance is in blade element in limited time.
Fig. 5 is the view that the embodiment of the present invention 1 seal clearance is in down blade element in limited time.
Fig. 6 is the installing orientation schematic diagram of the blade element of the embodiment of the present invention 1, distance piece and screening flow.
Fig. 7 is the expansion bend circumference installation position schematic diagram 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.
The aeroengine tip clearance of Fig. 9 achieved by the employing embodiment of the present invention 1 is at an aerial mission internal clearance variation characteristic curve.
Figure 10 is the structural representation that the expansion bend of the embodiment of the present invention 2 is in shortening state.
Figure 11 is the structural representation that the expansion bend of the embodiment of the present invention 2 is in 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 to touch mill point, H is gap adjustment amount, X is axially, Y is radial, 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, the other end connection control ring; Drive system can drive expansion bend to stretch.
Above-mentioned expansion bend is evenly equipped with 4 along seal arrangement circumference, is located at position, upper and lower, left and right respectively, adjusts the length of expansion bend according to clearance measurement situation respectively, can adjust the seal clearance of corresponding position respectively.The variable quantity of above-mentioned expansion bend length and the adjustment amount of seal clearance substantially linear.
Expansion bend is the cavity structure of band expansion joint, and expansion joint is concave, and expansion bend one end is closed, the other end is 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 pressurizing valve and reduction valve respectively, can regulate the pressure in pressure setting chamber, and pressure setting chamber is connected with expansion bend, and namely the pressure of expansion bend inner chamber also adjusts thereupon.
Blade assembly comprises blade element, distance piece, front plate, rear plate and screening flow; Blade element has two or more, 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.
Hide flow and be located at blade element upstream, between upper lantern and blade element; The free end of blade element exceeds control ring and hides flow.
Screening flow inward flange is radially provided with and cracks; Adjacent two crack between angle be 10 °.
In the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 40 °; Axially airflow direction, the axial angle of above-mentioned blade element and rotor is 20 °; The axial clearance of 0.25mm is provided with between blade element free end and lower lantern.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, expansion bend often extends 0.1mm, and 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; Hide flow adjacent two crack between angle be 3 °, and two panels hides flow stacked setting, cracks and mutually staggers.In the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 30 °; Axially airflow direction, the axial angle of above-mentioned blade element and rotor is 20 °; The axial clearance of 0.5mm is provided with between blade element free end and lower lantern.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, expansion bend often extends 0.1mm, and 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: hide flow adjacent two crack between angle be 30 °; In the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 52 °; Axially airflow direction, the axial angle of above-mentioned blade element and rotor is 27 °; The axial clearance of 0.6mm is provided with between blade element free end and lower lantern; 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, expansion bend often extends 0.1mm, and 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, the technological scheme that the mode that all employings are equal to replacement or equivalent transformation obtains, and all drops in protection scope of the present invention.
Claims (9)
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;
Above-mentioned control ring comprises support end face, and can move vertically by relative vane element free end, and support end face and blade element are oppositely arranged.
2. have the vane sealing device of gap control function as claimed in claim 1, it is characterized in that: also comprise expansion bend, expansion bend one end connects stator, the other end connection control ring.
3. there is the vane sealing device of gap control function as claimed in claim 2, it is characterized in that: expansion bend has four, uniform along seal arrangement circumference, be located at position, upper and lower, left and right respectively.
4. the vane sealing device with gap control function as described in claims 1 to 3 any one, is characterized in that: blade assembly comprises blade element, distance piece and screening flow; Blade element has two or more, 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; Hide flow and be located at blade element upstream, between upper lantern and blade element.
5. there is the vane sealing device of gap control function as claimed in claim 4, it is characterized in that: the free end of blade element exceeds control ring and hides flow.
6. there is the vane sealing device of gap control function as claimed in claim 2 or claim 3, it is characterized in that: expansion bend is the cavity structure of band expansion joint, and expansion bend is provided with suction port, suction port is communicated with the drive system driving expansion bend; 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.
7. there is the vane sealing device of gap control function as claimed in claim 4, it is characterized in that: hide flow inward flange and be radially provided with and crack, adjacent two crack between angle be 3 ~ 30 °.
8. there is the vane sealing device of gap control function as claimed in claim 7, it is characterized in that: the upper two panels that is provided with between lantern and blade element hides flow, and stacked setting, cracks and mutually stagger.
9. have the vane sealing device of gap control function as claimed in claim 4, it is characterized in that: in the sense of rotation of rotor, above-mentioned blade element and rotor radial angle are 0 ~ 60 °; Axially airflow direction, the axial angle of above-mentioned blade element and rotor is 0 ~ 45 °; The axial clearance of 0 ~ 1mm is provided with between above-mentioned blade element free end and lower lantern.
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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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| 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 CN103982248A (en) | 2014-08-13 |
| CN103982248B true CN103982248B (en) | 2016-04-06 |
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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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| EP1479951A2 (en) * | 2003-05-21 | 2004-11-24 | Mitsubishi Heavy Industries, Ltd. | Shaft seal |
| CN203258068U (en) * | 2013-04-24 | 2013-10-30 | 石伟伟 | Blade type sealing device |
| 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 |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10253646A (en) * | 1997-03-07 | 1998-09-25 | Nippon Seiko Kk | Sensor mounting part for rolling bearing unit with rotational-speed detecting device |
| US6918739B2 (en) * | 2002-12-26 | 2005-07-19 | United Technologies Corporation | Seal support |
| FR2914384B1 (en) * | 2007-03-27 | 2009-08-21 | Turbomeca Sa | DOUBLE JOINT WITH PRESSURIZED LIP. |
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2014
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| EP1479951A2 (en) * | 2003-05-21 | 2004-11-24 | Mitsubishi Heavy Industries, Ltd. | Shaft seal |
| CN203258068U (en) * | 2013-04-24 | 2013-10-30 | 石伟伟 | Blade type sealing device |
| 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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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. |