CN106555618B - The tip clearance control system and its method of gas turbine - Google Patents
The tip clearance control system and its method of gas turbine Download PDFInfo
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- CN106555618B CN106555618B CN201510639164.3A CN201510639164A CN106555618B CN 106555618 B CN106555618 B CN 106555618B CN 201510639164 A CN201510639164 A CN 201510639164A CN 106555618 B CN106555618 B CN 106555618B
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- tip clearance
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Abstract
The present invention provides the tip clearance control systems and its method of a kind of gas turbine, the control system includes gas turbine casing, rotor blade and several cooling lines, there is a tip clearance between the gas turbine casing and the rotor blade, the cooling line is arranged circumferentially in the gas turbine casing, several impact openings are offered on the cooling line, for cooling gas or heat gas to be blown to the gas turbine casing, to control the temperature of the gas turbine casing.The tip clearance control method of the gas turbine uses the tip clearance control system of gas turbine as described above.The tip clearance control system and its method of gas turbine of the present invention can effectively improve gas turbine due to the performance degradation that tip clearance becomes larger and generates by adjusting impact distance, to extend gas turbine service life.
Description
Technical field
The present invention relates to gas turbine field, in particular to the tip clearance control system of a kind of gas turbine and its side
Method.
Background technique
In gas turbine field, the tip clearance of gas turbine is to influence one of the key factor of its efficiency.Such as whirlpool
Fan engine, turbine clearance every reduction 0.25mm, SFC (oil consumption rate) can reduce 0.8%-1%.But the degeneration of tip clearance
And the one of the major reasons for causing gas turbine performance to fail.Under normal circumstances, gas turbine in the process of running, due to by
To the influence of the various factors such as transition state, external load, blade tip can be generated with casing certain touches mill.These touch mill and can directly lead
It causes tip clearance to become larger, so that becoming larger from the air flow rate of tip leakage, gas turbine performance is caused to fail.Such as it is civilian
Aviation turbofan engine, the result is that engine oil consumption rate increases caused by the decline of usual tip clearance, and exhaust temperature when taking off
Degree increases.
In response to the above problems, tip clearance control is a kind of more general technology, and a kind of common method is to casing
It is cooled down or is heated, so that tip clearance obtains optimal matching in different operating points.With mature civil aviation turbofan
For engine, big multipair high-pressure turbine, low-pressure turbine carry out actively or passively gap and control, generally use to turbine casing into
Row is cooling or heating consumes so that tip clearance obtains optimal matching in the duty cycle of engine to reduce engine
Oil cut rate.Usual this control mode be in the entire life cycle of gas turbine it is constant, tip clearance can not be eliminated become larger and lead
The performance degradation of cause.
The method of gap control includes actively and passively two ways, wherein active mode are as follows: in impact cooling line
Air flow rate be adjusted, in the different operating points of gas turbine, the impinging cooling of varying strength is carried out to casing, so that machine
Casket is different in the radial-deformation of different operating points, so that tip clearance has optimal matching value.And passive mode is not to air-flow
Flow is adjusted, therefore passive mode effect is not so good as active mode.
It is to change cooling or heat gas flow by the usual way that clearance control system improves tip clearance,
Such as after engine is using several circulations, tip clearance touches mill again and becomes larger at this time, it can be by changing gap control
System valve opening, so that cooling or heat gas changes in flow rate, changes the thermal deformation of casing, so as to improve between blade tip
Gap.
In conclusion gas turbine can cause tip clearance to increase due to touching the factors such as mill in use, causing property
It can fail, so that service life of aeroengine is reduced.Therefore, caused since tip clearance becomes larger in order to eliminate gas turbine
Performance degradation, the method that those skilled in the art urgently research and solve the above problem.
Summary of the invention
The technical problem to be solved by the present invention is in order to overcome in gas turbine use process in the prior art can performance decline
It moves back, leads to the defect of service life reduction, the tip clearance control system and its method of gas turbine are provided.
The present invention is to solve above-mentioned technical problem by following technical proposals: a kind of tip clearance control of gas turbine
System processed, it is characterized in that comprising gas turbine casing, rotor blade and several cooling lines, the gas turbine casing
There is a tip clearance between the rotor blade, the cooling line is arranged circumferentially in the gas turbine casing, institute
It states and offers several impact openings on cooling line, for cooling gas or heat gas to be blown to the gas turbine casing, with
Control the temperature of the gas turbine casing.
Preferably, the every two adjacent cooling line is spaced apart from each other arrangement.
Preferably, the distance of the impact opening on the cooling line to the gas turbine casing be cooling gas or
The impact distance of heat gas.
The present invention also provides a kind of tip clearance control methods of gas turbine, for eliminating declining for gas turbine performance
It moves back, it is characterized in that, the method uses the tip clearance control system of gas turbine as described above comprising following steps
S1, judge whether the engine of gas turbine uses the circulation of fixed quantity or the nargin of delivery temperature is
It is no to be reduced to preset value；If so, entering step S2；If it is not, then entering step S3；
S2, the impact opening on the adjustment cooling line to the distance of the casing, that is, adjust the impact distance,
So that casing shrinkage becomes larger, the tip clearance reduces；
S3, engine works on.
Preferably, in the step S1It is before further comprising the steps of: to start the engine work of gas turbine, institute
Clearance control system is stated to cool down the casing under the initial impact distance.
Preferably, in the step S3Later, with the use of the engine of the gas turbine, repeating said steps S1,
Until the engine stop of the gas turbine is run.
Preferably, the step S2The mode of the middle adjustment impact distance is to adjust the impinging cooling pipeline and described
Mounting distance or mounting means between gas turbine casing.
Preferably, the circulation of the fixed quantity of the engine of the gas turbine is 0-4000 circulation.
Preferably, the delivery temperature of the engine of the gas turbine is 0-30K.
The positive effect of the present invention is that: the tip clearance control system and its method of gas turbine of the present invention pass through
Adjustment impact distance can effectively improve gas turbine due to the performance degradation that tip clearance becomes larger and generates, to extend combustion
Gas-turbine service life.
Detailed description of the invention
The above and other feature of the present invention, property and advantage will pass through description with reference to the accompanying drawings and examples
And become apparent, identical appended drawing reference always shows identical feature in the accompanying drawings, in which:
Fig. 1 is the schematic diagram of the tip clearance control system of gas turbine of the present invention.
Fig. 2 is the schematic diagram in the tip clearance control system of gas turbine of the present invention by adjusting impact distance.
Fig. 3 be gas turbine of the present invention tip clearance control system after different operating recycles the variation of tip clearance show
It is intended to.
Fig. 4 is the flow chart of the tip clearance control method of gas turbine of the present invention.
Fig. 5 is the signal that the tip clearance control system of gas turbine of the present invention adjusts one embodiment of impact distance
Figure.
Specific embodiment
For the above objects, features and advantages of the present invention can be clearer and more comprehensible, below in conjunction with attached drawing to tool of the invention
Body embodiment elaborates.
In the following description, numerous specific details are set forth in order to facilitate a full understanding of the present invention, but the present invention can be with
It is different from other way described herein using other and implements, therefore the present invention is by the limit of following public specific embodiment
System.
Fig. 1 is the schematic diagram of the tip clearance control system of gas turbine of the present invention.Fig. 2 is the leaf of gas turbine of the present invention
By adjusting the schematic diagram of impact distance in intercuspal space control system.Fig. 3 is that the tip clearance of gas turbine of the present invention controls system
The variation schematic diagram of system tip clearance after different operating circulation.
As shown in Figure 1 to Figure 3, the invention discloses a kind of tip clearance control systems of gas turbine comprising combustion gas
Turbine casing 20, rotor blade 30 and several cooling lines 10.Have one between gas turbine casing 20 and rotor blade 30
Tip clearance X, and cooling line 10 is arranged circumferentially in 20 outside of gas turbine casing.Particularly, it is also opened on cooling line 10
Equipped with several impact openings 40, for cooling gas or heat gas to be blown to gas turbine casing 20, to reach control combustion gas
The purpose of the temperature of turbine casing 20.
Herein, every two adjacent cooling line 10 is spaced apart from each other arrangement.Impact opening 40 on cooling line 10 is to combustion gas
The distance of turbine casing 20 is the impact distance of cooling gas or heat gas, is controlled by the temperature to casing to reach
The target of its thermal deformation is controlled, to realize the control to tip clearance.
In gas turbine field, influence impinging cooling/heating effect principal element include air flow rate, temperature and
Impact distance (as shown in Figure 2).Impact distance is the distance from the aperture 40 on impinging cooling pipe to gas turbine casing 20, is led to
Normal impact distance is closer, and (impact distance d' as shown in Figure 2 is less than impact distance d), and impinging cooling effect is better.Work as engine
After structure design is completed, impact distance is typically all constant in the life cycle of entire engine.
As shown in Figure 3, the engine of gas turbine is in entire life cycle, tip clearance meeting due to touching mill etc.
It is gradually increased, is reduced so as to cause engine efficiency, performance decline.Such as the bold portion in Fig. 2 gives tip clearance and exists
The example being gradually increased in the engine life period.
According to above structure, the present invention also provides a kind of tip clearance control methods of gas turbine, for eliminating combustion
The decline of gas turbine performance.Fig. 4 is the flow chart of the tip clearance control method of gas turbine of the present invention.
As shown in figure 4, the method uses the tip clearance control system of gas turbine as described above comprising following
Step
Step 1: start the engine work of gas turbine, the clearance control system is in the initial impact
The casing is cooled down apart from lower.Specifically, new engine is normally started work, pass through the leaf of the gas turbine
Intercuspal space control system cools down gas turbine casing under initial impact distance, to realize gap control effect.
With the increase for the recurring number that engine uses, abrasion due to blade tip to stator, tip clearance can be gradually
Become larger, will gradually fail along with engine performance, and the nargin of engine exhaust temperature reduces.
Step 2: judge the engine of gas turbine whether use fixed quantity circulation or delivery temperature it is abundant
Whether degree is reduced to preset value；If so, entering step three；If it is not, then entering step four.
Usually judge that the nargin decreasing value of loop number or delivery temperature is obtained by testing, common numerical value
Range is that 0-4000 engine is reduced using the nargin of circulation or the delivery temperature of 0-30K, but is not limited in actual use
In this numberical range.
Step 3: the distance of the impact opening on the cooling line to the casing is adjusted, that is, adjusts the impact
Distance, so that casing shrinkage becomes larger, the tip clearance reduces.
The mode generallyd use is the aperture of adjustment valve to adjust cooling gas flow, realizes the purpose for reducing gap.So
And the present invention proposes numerical value given when designing according to engine to adjust impact distance, reinforces to the cold of gas turbine casing
But, so that the shrinkage of gas turbine casing becomes larger, tip clearance reduces, to realize the mesh for slowing down engine performance decline
's.The method for adjusting impact distance usually can be by adjusting the installation between impinging cooling pipeline 10 and gas turbine casing 20
Distance or mounting means, realize different impact distances.The adjusting method of impact distance mainly includes both the above, but this hair
Bright to be not limited to above two mode, other modes that can be realized adjustment impact distance can also use.
Step 4: engine works on.
Step 5: with the use of the engine of the gas turbine, repeating said steps two, until the gas turbine
Engine it is retired.
Fig. 5 is the signal that the tip clearance control system of gas turbine of the present invention adjusts one embodiment of impact distance
Figure.
It is further illustrated, as shown in figure 5, in conjunction with Fig. 4, when engine has run C1After a duty cycle, blade tip
Gap width x increases than former design result.According to the design experiences and experimental test result of gap control, judgement has needed to carry out
The adjusting of impact distance reduces tip clearance value to increase casing deflection.
The method for reducing impact distance mainly includes following manner but not limited to this method, by adjusting installation cooling tube
10 fastening structure, the difference of the installation and adjustment mode of the fastening structure, can change the distance of impact opening to gas turbine casing.
Reinforce the cooling to gas turbine casing 20 by reducing impact distance, so that 20 radial contraction amount of gas turbine casing increases
Add, so that tip clearance at this time reduces, to counteract tip clearance decline, realizing improves engine performance decline rate
Target.
As shown in figure 5, for example impinging cooling pipe 10 is mounted on horizontal support 60 and radial struts 70, passing through bolt
80, for 90 location and installations on gas turbine casing 20, the bolt hole 61,71 on horizontal support 60 and radial struts 70 is set as long
Bar shaped.When needing to adjust impact distance, change the peace of the bolt 90 on the bolt 80 and radial struts 70 on horizontal support 60
Holding position may make that horizontal support 60 and radial struts 70 are translated, that is, can reach the purpose for adjusting impact distance.
Likewise, when engine is continued to use to C2、C3After a duty cycle, when tip clearance increases again, need
Continue to reduce impact distance, can further offset tip clearance decline, and then reach improvement engine performance decline, extends hair
The target of motivation service life.
In the entire life cycle of engine, the adjustment of impact distance is specifically carried out after how many a duty cycles, into
The adjustment of capable impact distance several times, should determine depending on the particular condition in use of engine.
Although specific embodiments of the present invention have been described above, it will be appreciated by those of skill in the art that these
It is merely illustrative of, protection scope of the present invention is defined by the appended claims.Those skilled in the art is not carrying on the back
Under the premise of from the principle and substance of the present invention, various changes or modifications can be made to these embodiments, but these are changed
Protection scope of the present invention is each fallen with modification.
Claims (6)
1. the tip clearance control method of a kind of gas turbine, for eliminating the decline of gas turbine performance, which is characterized in that institute
The tip clearance control system that method uses gas turbine is stated, the tip clearance control system of the gas turbine includes combustion gas wheel
Machine casing, rotor blade and several cooling lines, between a blade tip between the gas turbine casing and the rotor blade
Gap, the cooling line are arranged circumferentially in the gas turbine casing, and several impact openings are offered on the cooling line, are used
In cooling gas or heat gas are blown to the gas turbine casing, to control the temperature of the gas turbine casing；
The distance of the impact opening to the gas turbine casing on the cooling line is cooling gas or heat gas
Impact distance；By adjusting the mounting means between cooling line and gas turbine casing, different impact distances is realized；
The cooling line is mounted on horizontal support and radial struts, and by bolt location and installation in the gas turbine machine
On casket, the bolt hole of strip is set on the horizontal support and the radial struts, when needing to adjust impact distance, is changed
Installation site of the bolt on the horizontal support and in the radial struts；The every two adjacent cooling line phase
Mutual arranged for interval；
The tip clearance control method of the gas turbine the following steps are included:
S1, judge whether the engine of gas turbine uses whether the circulation of fixed quantity or the nargin of delivery temperature reduce
To preset value；If so, entering step S2；If it is not, then entering step S3；
S2, the impact opening on the adjustment cooling line to the gas turbine casing distance, that is, adjust the impact away from
From so that the gas turbine casing shrinkage becomes larger, the tip clearance reduces；
S3, engine works on.
2. the tip clearance control method of gas turbine as described in claim 1, which is characterized in that in the step S1Before
It is further comprising the steps of: to start the engine work of gas turbine, the tip clearance control system is in initial impact
The gas turbine casing is cooled down apart from lower.
3. the tip clearance control method of gas turbine as described in claim 1, which is characterized in that in the step S3Later,
With the use of the engine of the gas turbine, repeating said steps S1, until the engine stop of the gas turbine is transported
Row.
4. the tip clearance control method of gas turbine as described in claim 1, which is characterized in that the step S2Middle adjustment
The mode of the impact distance is the mounting means adjusted between the cooling line and the gas turbine casing.
5. the tip clearance control method of gas turbine as described in claim 1, which is characterized in that the hair of the gas turbine
The circulation of the fixed quantity of motivation is 0-4000 circulation.
6. the tip clearance control method of gas turbine as described in claim 1, which is characterized in that the hair of the gas turbine
The nargin decreasing value of the delivery temperature of motivation is 0-30K.
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| CN201510639164.3A CN106555618B (en) | 2015-09-30 | 2015-09-30 | The tip clearance control system and its method of gas turbine |
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| CN201510639164.3A CN106555618B (en) | 2015-09-30 | 2015-09-30 | The tip clearance control system and its method of gas turbine |
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| CN106555618B true CN106555618B (en) | 2019-09-13 |
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| CN107435563B (en) * | 2017-05-05 | 2023-04-07 | 西北工业大学 | Casing structure with blade tip clearance control and blade tip flow control |
| CN114812476A (en) * | 2021-01-28 | 2022-07-29 | 中国人民解放军63833部队 | Low-temperature rapid temperature change test device and method for blade tip clearance sensor |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104508254A (en) * | 2012-07-25 | 2015-04-08 | 通用电气公司 | Active clearance control system |
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| US5779436A (en) * | 1996-08-07 | 1998-07-14 | Solar Turbines Incorporated | Turbine blade clearance control system |
| US7431557B2 (en) * | 2006-05-25 | 2008-10-07 | General Electric Company | Compensating for blade tip clearance deterioration in active clearance control |
| JP5174190B2 (en) * | 2009-01-20 | 2013-04-03 | 三菱重工業株式会社 | Gas turbine equipment |
| US8342798B2 (en) * | 2009-07-28 | 2013-01-01 | General Electric Company | System and method for clearance control in a rotary machine |
| GB201004381D0 (en) * | 2010-03-17 | 2010-04-28 | Rolls Royce Plc | Rotor blade tip clearance control |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104508254A (en) * | 2012-07-25 | 2015-04-08 | 通用电气公司 | Active clearance control system |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Applicant after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Applicant before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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