CN106555619B - The control device and method in gas turbine blade gap - Google Patents
The control device and method in gas turbine blade gap Download PDFInfo
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- CN106555619B CN106555619B CN201510639396.9A CN201510639396A CN106555619B CN 106555619 B CN106555619 B CN 106555619B CN 201510639396 A CN201510639396 A CN 201510639396A CN 106555619 B CN106555619 B CN 106555619B
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Abstract
The present invention relates to a kind of control device and methods in gas turbine blade gap.The device includes an impact pipeline, is distributed with multiple impact openings against the periphery of the turbine casing of gas turbine, on the surface of the impinging cooling pipeline, and it is inconsistent that one group of parameter related with heat transfer effect of multiple impact opening is pre the circumferential direction along the impact pipeline；Wherein this group of parameter includes aperture, pitch of holes and at least one at a distance from the periphery of the turbine casing, the heat transfer effect is according to the required deformation adjustment amount of turbine casing circumferential direction different location, the temperature current according to casing, it precalculates to obtain, wherein deformation adjustment amount is bigger, and the heat transfer effect is bigger.The present invention can eliminate influencing for the even factor of circumferential asymmetry that tip clearance is subject to.
Description
Technical field
The present invention relates to gas turbine field, the control device more particularly, to a kind of gas turbine blade gap and side
Method.
Background technology
Gas turbine (Gas Turbine) is a kind of being converted to machinery using the gas continuously flowed as working medium, thermal energy
The rotary power machinery of work(.In the gas turbine, be maintained between the moving blade blade tip of turbine and shell inward faces it
Between required radial clearance for being important for turbine performance and part durability.By taking fanjet as an example,
Turbine clearance often reduces 0.25mm, and oil consumption rate (SFC) can reduce 0.8%-1%.Influence tip clearance factor be it is very more,
Deformation caused by thermal deformation, centrifugal distortion including rotor, the thermal deformation of casing and gas inside and outside differential pressure, these deformations are logical
Often it is uniform in circumferential position.Under different working condition, above-mentioned deflection is different engine, and tip clearance is caused to exist
Different conditions point is varied from.Ripe civil aviation fanjet at present, big multipair high-pressure turbine and low-pressure turbine carry out
Actively or passively clearance control.The method generally use of clearance control carries out circumferential air-impingement cooling to turbine casing or adds
Heat.Since above-mentioned deformation is usually uniform in circumferential position, circumferential cooling or heating is also uniform, and such pipeline 11 is in week
The size of upward impact opening 12 is generally identical with aperture, referring to Fig.1 shown in middle schematic diagram, eliminates the uniform factor pair of above-mentioned circumferential direction
The influence in gap.
But in addition to caused by the uniform factor of above-mentioned circumferential direction deform other than except, the also even factor of some circumferential asymmetries is led
The deformation of cause, such as the degree of eccentricity of rotor and casing, engine is oval by the casing that the external loads such as gyroscopic couple, gravity generate
The factors such as degree and global vibration of engine.Above-mentioned uneven factor can make the tip clearance of gas turbine circumferentially have compared with
Big difference, circumferential gap is not of uniform size, certain inhomogeneities is presented.It is general at present to casing carry out it is circumferential uniformly cooling or
The method of heating, can not eliminate this gap increase that partially circumferentially uneven factor generates and efficiency reduces.
Invention content
Technical problem to be solved by the invention is to provide a kind of control device and method in gas turbine blade gap, with
Eliminate tip clearance by the even factor of circumferential asymmetry influenced.
The present invention the technical solution adopted is that proposes a kind of gas turbine blade gap to solve above-mentioned technical problem
Control device, including an impact pipeline divide against the periphery of the turbine casing of gas turbine on the surface of the impinging cooling pipeline
Multiple impact openings are furnished with, one group of parameter related with heat transfer effect of multiple impact opening is pre the week along the impact pipeline
To inconsistent；Wherein this group of parameter include aperture, pitch of holes and at a distance from the periphery of the turbine casing at least within it
One, which is the temperature current according to casing according to the required deformation adjustment amount of turbine casing circumferential direction different location
Degree, precalculates to obtain, wherein deformation adjustment amount is bigger, the heat transfer effect is bigger.
In one embodiment of this invention, the ratio in the pitch of holes of the impact opening of circumferential different location and aperture 2-18 it
Between, the difference of the pitch of holes of impact opening is between 0.5-7 times of aperture.
In one embodiment of this invention, the aperture of the impact opening of circumferential different location is between 0.4mm-2mm, aperture it
Difference is between 0.2-1mm.
In one embodiment of this invention, the impact opening of circumferential different location at a distance from the periphery of the turbine casing in 3-
Between 25 times of apertures, the difference of the distance of circumferential different location is within 22 times of apertures.
In one embodiment of this invention, the calculating of the deformation adjustment amount considers the degree of eccentricity of rotor and turbine casing, hair
The casing ovality and global vibration of engine that motivation is generated by external load.
The present invention also proposes a kind of control method in gas turbine blade gap, including：An impact pipeline is provided, against combustion
Multiple impact openings are distributed on the surface of the impinging cooling pipeline in the periphery of the turbine casing of gas-turbine, multiple impact opening
It is inconsistent that one group of parameter related with heat transfer effect is pre the circumferential direction along the impact pipeline；Wherein this group of parameter includes hole
Diameter, pitch-row and at a distance from the periphery of the turbine casing at least one, the heat transfer effect be according to the turbine casing week
To the required deformation adjustment amount of different location, the temperature current according to casing precalculates to obtain.
In one embodiment of this invention, the ratio in the pitch of holes of the impact opening of circumferential different location and aperture 2-18 it
Between, the difference of the pitch of holes of impact opening is between 0.5-7 times of aperture.
In one embodiment of this invention, the aperture of the impact opening of circumferential different location is between 0.4mm-2mm, aperture it
Difference is between 0.2-1mm.
In one embodiment of this invention, the impact opening of circumferential different location at a distance from the periphery of the turbine casing in 3-
Between 25 times of apertures, the difference of the distance of circumferential different location is within 22 times of apertures.
In one embodiment of this invention, the calculating of the deformation adjustment amount considers the degree of eccentricity of rotor and turbine casing, hair
The casing ovality and global vibration of engine that motivation is generated by external load.
The present invention due to using the technology described above, is allowed to compared with prior art, according to casing different location deflection
Difference, different impact pitchs of holes, aperture, distance etc. be set, realizes that each position deflection is essentially identical, the coordinating and unifying, disappears
In addition to tip clearance is in circumferential inhomogeneities.
Description of the drawings
For the above objects, features and advantages of the present invention can be clearer and more comprehensible, below in conjunction with attached drawing to the tool of the present invention
Body embodiment elaborates, wherein：
Fig. 1 shows the impact opening distribution schematic diagram of known tip clearance control device.
Fig. 2A, 2B show the structural schematic diagram of the tip clearance control device of one embodiment of the invention.
Fig. 3 shows the impact opening distribution schematic diagram of the tip clearance control device of one embodiment of the invention.
Fig. 4 shows the impact opening distribution schematic diagram of the tip clearance control device of another embodiment of the present invention.
Fig. 5 shows impact pore size distribution design process according to an embodiment of the invention.
Fig. 6 shows the operating diagram of the tip clearance control device of one embodiment of the invention.
Specific implementation mode
Many details are elaborated in the following description to facilitate a thorough understanding of the present invention, still the present invention can be with
Implemented different from other manner described here using other, therefore the present invention do not limited by following public specific embodiment
System.
The embodiment of the present invention describes the control device and its method in gas turbine blade gap.Between the blade tip of gas turbine
Gap is influenced by various factors, can there is a situation where that circumferential asymmetry is even.Therefore the present invention proposes a kind of to gas turbine
Casing carries out the even cooling of circumferential asymmetry or heating with the even technology of the tip clearance circumferential asymmetry eliminated or alleviated.
It is different to adjust the required heat transfer effect of different casing degree of deformations, and different heat transfer effects can be by whirlpool
Wheel casing carries out the distribution of the impact opening of the impact tube road of impinging cooling or heating to control.Therefore, pass through calculated in advance
Heat transfer effect, you can be pre-designed the distribution of the impact opening of impact tube road, to provide needed for heat transfer effect to casing into
Row is heated or cooled, and controls required degree of deformation adjustment.
Fig. 2A, 2B show the structural schematic diagram of the tip clearance control device of one embodiment of the invention.With reference to figure 2A, 2B institutes
Show, the control device 200 in gas turbine blade gap includes impact pipeline 210.Turbine of the impact pipeline 210 against gas turbine
The periphery of casing 220.Turbine casing 220 is a loop configuration, and cross section (such as Fig. 2 B) is substantially circular.Accordingly
Ground, the cross section for impacting pipeline 210 are also substantially rounded.But due to the influence of various uneven factors, turbine casing
220 cross section will not just be round.Dashed circle O is drawn in Fig. 2 B as reference, it is uneven caused by deformation to show
Evenness.
It impacts on the surface of pipeline 210 and multiple impact openings 211 is distributed with.One group of these impact openings 211 and heat transfer effect
Related parameter is pre inconsistent along the circumferential direction for impacting pipeline 210.Here, heat transfer effect is according to turbine casing 220 weeks
To the required deformation adjustment amount of different location, the temperature current according to casing precalculates to obtain.It is bigger to deform adjustment amount,
Heat transfer effect is bigger.Here, heat transfer effect and the relationship for needing the size of deflection approximate can regard direct ratio as, it can also be accurate
The form of increasing function is converted to, specific implementation needs to be selected according to the precision of design.
For example, above-mentioned one group parameter related with heat transfer effect includes aperture, pitch of holes and and turbine casing
Periphery distance at least one.Aperture indicates the diameter of impact opening.Pitch of holes be between adjacent impact opening away from
From being indicated with distance between the center of circle.It is all to determine due to the region of the pore size distribution of impinging cooling pipeline 210, pitch of holes
Represent the thin of impact opening, solid matter cloth.The impact opening edge on impinging cooling pipeline 210 is represented at a distance from the periphery of turbine casing
The distance of a point on radial direction to the periphery of turbine casing.In cooling or heating, impact opening can be along radius side
Gas is provided to inside.In order to make heat transfer effect inconsistent along the circumferential direction of impact pipeline 210, thus also can be along turbine casing
220 circumferential direction is inconsistent, and the aperture of the impact opening of each circumferential position can be allowed different, and pitch-row is different or impact opening and turbine
The distance of the periphery of casing is different.When needed, can also allow in these parameters two or more are different.
Fig. 3 shows the impact opening distribution schematic diagram of the tip clearance control device of one embodiment of the invention.In the implementation of Fig. 3
In example, impact opening is that density degree design in hole is different.In the present embodiment, design criteria is：The big position of casing deflection, punching
The quantity for hitting hole 211 is significantly more than the small position of deflection, and it is that deflection is small to correspond to the region A, C in Fig. 3, and hole count relatively dredges place；B
Region is deflection general goal, and hole count is more intensive.The foundation of design is with reference to the schematic diagram about deflection in Fig. 2 B, and difference becomes
The heat transfer effect of shaped position distribution is different, to need to carry out the density design in hole.In the fig. 3 embodiment, pitch of holes and hole
The ratio of diameter usually between 2-18, but not limited to this range, but can be adjusted according to the demand of heat transfer effect；And
And typically circumferentially the difference of the pitch of holes of different location usually between 0.5-7 times of aperture.For example, by taking Fig. 2 B as an example, casing circumferential 3
Point and 9 o'clock direction radial-deformation ratio it is circumferential 12 points and 6 o'clock direction it is big, about exceed 0.2mm, casing is elliptical.Due to
Casing 220 it is circumferential 3 points and 9 o'clock direction radial-deformation it is larger, then closeer in this circumferential position hole, pitch of holes is small, such as
Pitch of holes is 5 times of apertures or so；And casing 220 it is circumferential 12 points and 6 o'clock Direction distortion amount it is smaller, hole is more sparse, Kong Jian
Away from big, such as pitch of holes is in 12 times of apertures or so.Arrangement in this way can make casing in the radial direction of circumferential different location
Shrinkage is different, and 12 points of 3 points of illustrative example circumferential direction and 9 o'clock direction ratio and 6 o'clock radial contraction amount are about
0.2mm offsets the ovality of casing.
Fig. 4 shows the impact opening distribution schematic diagram of the tip clearance control device of one embodiment of the invention.In the implementation of Fig. 4
In example, impact opening is that aperture design is different.It, can be in the region E for needing deflection big with reference to D, E, F area schematic of Fig. 4
It arranges the larger hole in aperture, and the smaller hole in aperture is arranged in deflection small region D, F.In the present embodiment, impact opening
Aperture is usually between 0.4mm-2mm, but not limited to this range, and can be adjusted according to the demand of tolerance；Usually week
To aperture difference between 0.2mm-1mm.For example, equally with the example of Fig. 2 B, casing 220 circumferential 3 points and 9 o'clock direction radial direction
For deflection than 12 points and 6 o'clock direction about 0.2mm circumferential, casing is elliptical；Due at casing 220 circumferential 3 points and 9 o'clock
Direction radial-deformation is larger, then larger in this circumferential position aperture, such as aperture about 1.5mm or so；And in casing circumferential 12
Point and 6 o'clock Direction distortion amount are smaller, and aperture is smaller, such as aperture about 0.7mm.Arrangement in this way can make casing
It is different in the radial contraction amount of circumferential different location, an illustrative example circumferential 3 points and 12 points and 6 points of 9 o'clock direction ratio
Clock radial contraction amount about 0.2mm, offsets the ovality of casing.
Similarly, when impact opening is different to the design of the distance of casing, substantially circular circumferential pipeline 210 can be enabled suitable
Work as deformation.In the position that casing deflection is larger, the distance of impact opening to casing is closer to smaller on the contrary.Such as circumferential different positions
At a distance from the periphery of the turbine casing between 3-25 times of aperture, the difference of the distance of circumferential different location exists the impact opening set
Within 22 times of apertures.
The calculating of casing unevenness is the foundation for carrying out clearance control and distributing different amount of air entrainment.It is described below with reference to Fig. 5
Illustrative impact pore size distribution design process.
In step 501, three dimensional temperature field computation is carried out to rotor and casing.
Special consideration should be given to the even property of the circumferential asymmetry of rotor and casing heat transfer boundary condition in the embodiment of the present invention, to obtain
Three-dimensional temperature field.In contrast, conventional lower Temperature calculating is counted using circumferentially uniform heat transfer boundary condition hypothesis
It calculates.
In step 502, on the basis of circumferential asymmetry even three-dimensional temperature field is calculated, while rotor and casing are considered
The degree of eccentricity, the factors such as casing ovality that engine is generated by external load and global vibration of engine, to casing into
Row inhomogeneous deformation calculates.Here, external load is by can be gyroscopic couple, gravity etc..
By taking high-pressure turbine as an example, typically circumferentially unevenness is about 0.2mm or so.
In step 503, the deflection even according to casing circumferential asymmetry obtains circumferential different location casing deformation adjustment amount.
In step 504, according to the required deformation adjustment amount of circumferential different location casing, the temperature current according to casing,
Casing is calculated in the required throughput of circumferential different location.
It needs to carry out impact pore size distribution, such as pitch of holes after the heat transfer effect for determining circumferential each position in step 505
Calculate the calculating with different pore size value.
To realize that the heat transfer effect that cooling strain needs is realized not by designing pitch of holes and the aperture of corresponding position
Different heat transfer effects is distributed with position.Trepanning density schematic diagram with reference to Fig. 3, the ratio in pitch of holes and aperture usually 2-18 it
Between, but not limited to this range can be adjusted according to the demand of heat transfer effect；The typically circumferentially difference of the pitch of holes of different location
Usually between 0.5-7 times of aperture.With reference to Fig. 4, aperture is usually between 0.4mm-2mm for impact opening pore size schematic diagram, but
Not limited to this range can be adjusted according to the demand of heat transfer effect, and typically circumferentially the difference in aperture is between 0.2-1mm.
In step 506, the design of the density and pore size of impact opening is verified.
It is verified here, verification can be numerical simulation calculation, or verification experimental verification；
In step 507, after the verification of step 506, accordance judgement is carried out, if design meets wanting for cooling strain
It asks, is then practiced；If above-mentioned design is unsatisfactory for cooling strain requirement, need to return to step 204 re-start calculating with
Design, until the pitch of holes met the requirements, aperture value and arrangement result.
Fig. 6 shows the operating diagram of the tip clearance control device of one embodiment of the invention.Refering to what is shown in Fig. 6, blade tip
Gap control device includes pipeline 210 circumferentially, is distributed impact opening 211 on pipeline 210.When device works, pass through one
Executing agency's (not shown) controls the throughput to impact pipeline 210.Executing agency for example can be by controlling each valve opening
To control flow.Air-flow 212 flows through each impact opening 211, and impinging cooling or heating are carried out to casing 220.The ellipse of dotted line in Fig. 6
Casing 220 when shape is without clearance control, there is the even deformations of circumferential asymmetry for casing at this time, cause tip clearance circumferential not
Uniformly.After processing by tip clearance control device, the casing 220 ' that the ellipse of realization indicates is reverted to.
The above embodiment of the present invention can reduce gas turbine due to bias by circumferential asymmetry even cooling or heating
The even property of circumferential asymmetry for the tip clearance that the casing ovality that the external loads such as degree, gyroscopic couple, gravity generate generates, avoids office
Portion gap is excessive, realizes that each position gap width is almost the same, to improve gas turbine proficiency；And improve gas turbine week
Uneven to gap and generation the risk for touching mill, and slow down the rate of gas turbine performance decline.
Although the present invention is described with reference to current specific embodiment, those of ordinary skill in the art
It should be appreciated that above embodiment is intended merely to illustrate the present invention, can also make in the case of no disengaging spirit of that invention
Go out various equivalent change or replacement, therefore, as long as to the variation of above-described embodiment, change in the spirit of the present invention
Type will all be fallen in the range of following claims.
Claims (10)
1. a kind of control device in gas turbine blade gap, including an impact pipeline, the turbine casing of opposite gas turbine
Periphery, is distributed with multiple impact openings on the surface of the impinging cooling pipeline, and related with heat transfer effect the one of multiple impact opening
It is inconsistent that group parameter is pre the circumferential direction along the impact pipeline；
Wherein this group of parameter include aperture, pitch of holes and impact opening at a distance from the periphery of the turbine casing at least within it
One, which is the temperature current according to casing according to the required deformation adjustment amount of turbine casing circumferential direction different location
Degree, precalculates to obtain, wherein deformation adjustment amount is bigger, the heat transfer effect is bigger.
2. the control device in gas turbine blade gap as described in claim 1, which is characterized in that circumferential different location rushes
The pitch of holes in hole and the ratio in aperture are hit between 2-18, the difference of the pitch of holes of impact opening is between 0.5-7 times of aperture.
3. the control device in gas turbine blade gap as described in claim 1, which is characterized in that circumferential different location rushes
The aperture in hole is hit between 0.4mm-2mm, the difference in aperture is between 0.2-1mm.
4. the control device in gas turbine blade gap as described in claim 1, which is characterized in that circumferential different location rushes
Hole is hit at a distance from the periphery of the turbine casing between 3-25 times of aperture, the difference of the distance of circumferential different location is in 22 times of holes
Within diameter.
5. the control device in gas turbine blade gap as described in claim 1, which is characterized in that the meter of the deformation adjustment amount
The degree of eccentricity for considering rotor and turbine casing is calculated, the casing ovality and engine that engine is generated by external load are whole
Machine vibration.
6. a kind of control method in gas turbine blade gap, including：
An impact pipeline is provided to be distributed on the surface of the impinging cooling pipeline against the periphery of the turbine casing of gas turbine
Multiple impact openings, one group of parameter related with heat transfer effect of multiple impact opening be pre along the impact pipeline circumferential direction not
Unanimously；Wherein this group of parameter include aperture, pitch-row and at a distance from the periphery of the turbine casing at least one, the heat exchange
Effect is according to the required deformation adjustment amount of turbine casing circumferential direction different location, and the temperature current according to casing is counted in advance
It obtains.
7. the control method in gas turbine blade gap as claimed in claim 6, which is characterized in that circumferential different location rushes
The pitch of holes in hole and the ratio in aperture are hit between 2-18, the difference of the pitch of holes of impact opening is between 0.5-7 times of aperture.
8. the control method in gas turbine blade gap as claimed in claim 6, which is characterized in that circumferential different location rushes
The aperture in hole is hit between 0.4mm-2mm, the difference in aperture is between 0.2-1mm.
9. the control method in gas turbine blade gap as claimed in claim 6, which is characterized in that circumferential different location rushes
Hole is hit at a distance from the periphery of the turbine casing between 3-25 times of aperture, the difference of the distance of circumferential different location is in 22 times of holes
Within diameter.
10. the control method in gas turbine blade gap as claimed in claim 6, which is characterized in that the deformation adjustment amount
The degree of eccentricity for considering rotor and turbine casing is calculated, the casing ovality and engine that engine is generated by external load
Complete machine oscillation.
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| CN108019242B (en) * | 2017-12-15 | 2019-08-06 | 北京航空航天大学 | Aero-engine tip clearance active control device based on shape-memory alloy wire |
| CN209761503U (en) * | 2019-01-22 | 2019-12-10 | 北京南方斯奈克玛涡轮技术有限公司 | Turbine casing integrated with active clearance control device and turbine |
| CN111967098B (en) * | 2020-07-19 | 2022-06-21 | 复旦大学 | Turbine mechanical blade tip radial running clearance probability optimization design method |
| CN112253264B (en) * | 2020-12-21 | 2021-04-02 | 中国航发上海商用航空发动机制造有限责任公司 | Device and method for regulating rotor-stator clearance and concentricity state |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101161997A (en) * | 2006-10-12 | 2008-04-16 | 通用电气公司 | Turbine case impingement cooling for heavy duty gas turbines |
| CN104508254A (en) * | 2012-07-25 | 2015-04-08 | 通用电气公司 | Active clearance control system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| EP2574732A2 (en) * | 2011-09-29 | 2013-04-03 | Hitachi Ltd. | Gas turbine |
| US8998563B2 (en) * | 2012-06-08 | 2015-04-07 | United Technologies Corporation | Active clearance control for gas turbine engine |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101161997A (en) * | 2006-10-12 | 2008-04-16 | 通用电气公司 | Turbine case impingement cooling for heavy duty gas turbines |
| CN104508254A (en) * | 2012-07-25 | 2015-04-08 | 通用电气公司 | Active clearance control system |
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