CN106813603A - A kind of fuel assembly deflection bilayer supersonic detection method - Google Patents
A kind of fuel assembly deflection bilayer supersonic detection method Download PDFInfo
- Publication number
- CN106813603A CN106813603A CN201510860491.1A CN201510860491A CN106813603A CN 106813603 A CN106813603 A CN 106813603A CN 201510860491 A CN201510860491 A CN 201510860491A CN 106813603 A CN106813603 A CN 106813603A
- Authority
- CN
- China
- Prior art keywords
- layer
- fuel assembly
- grid spacer
- ultrasonic inspection
- inspection probe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Monitoring And Testing Of Nuclear Reactors (AREA)
- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
- Length Measuring Devices Characterised By Use Of Acoustic Means (AREA)
Abstract
The invention belongs to physical size field of measuring technique, and in particular to a kind of fuel assembly deflection bilayer supersonic detection method.Apparatus of the present invention include six groups of ultrasonic testing systems and fixed seat, and six groups of ultrasonic testing systems are uniformly fixed in fixed seat, and ultrasonic testing system includes one layer of ultrasonic inspection probe, two layers of ultrasonic inspection probe and fixed plate；One layer of ultrasonic inspection probe includes two probes, and two layers of ultrasonic inspection probe include two probes, and probe is fixedly mounted in fixed plate, and fixed plate is arranged in fixed seat, and fixed plate is hollow ring plate.The inventive method includes that step 1, fuel assembly deformation detection prepare；Step 2, the detection of fuel assembly down process；Step 3, result are calculated；Step 4, the detection of fuel assembly lifting process.The present invention can be eliminated due to the fuel assembly deformation detection error that the machine error of refueling machine is introduced, and improve fuel assembly deformation detection precision.
Description
Technical field
The invention belongs to physical size field of measuring technique, and in particular to a kind of fuel assembly deformation
The double-deck supersonic detection method of amount.
Background technology
In shutdown discharging or charging process, the fuel assembly to part postdose is carried out nuclear power station
Deformation detection.
Fuel assembly deflection is carried out by the relative space position of spacer grid of fuel assembly
Calculate, certain power station uses hexagon fuel assembly.
Testing equipment is circular platform structure, wherein circumferentially arranging 6 groups of laser measuring device for measuring.
During detection, inspection equipment is placed on fuel pit screen work；One group of fuel stack is captured using refueling machine
Part, circular hole falls and above carries in the middle of the circular platform, and period, 6 groups of laser were respectively to fuel assembly
6 faces are projected, and are received by light path and processed, and realize that fuel assembly deformation is measured.
There is following defect in the laser measuring technology for using at present：
(1) refueling machine is plant equipment, there is machine error and fit tolerance；During detection,
Lifting and underthrust fuel assembly process, the refueling machine working beam presence for capturing fuel assembly are rocked,
Introduce detection error.
(2) laser detection system, detection platform is complicated under water, radioresistance is poor, reliability
Difference, the service life of equipment is short.
The content of the invention
Present invention solves the technical problem that：A kind of fuel assembly deflection bilayer ultrasound detection is provided
Method, eliminates due to the fuel assembly deformation detection error that the machine error of refueling machine is introduced, and carries
Fuel assembly deformation detection precision high.
The technical solution adopted by the present invention：
1. a kind of fuel assembly deflection bilayer supersonic detection device, it is characterised in that：Including six
Group ultrasonic testing system and fixed seat, six groups of ultrasonic testing systems are uniformly fixed in fixed seat,
Ultrasonic testing system includes one layer of ultrasonic inspection probe, two layers of ultrasonic inspection probe and fixed plate；
One layer of ultrasonic inspection probe includes two probes, and two layers of ultrasonic inspection probe include two probes,
Probe is fixedly mounted in fixed plate, and fixed plate is arranged in fixed seat, and fixed plate is hollow ring
Shape plate.
2. a kind of fuel assembly deflection bilayer supersonic detection method, it is characterised in that：Including with
Lower step：
Step 1, fuel assembly deformation detection prepare：
Double-deck supersonic detection device is fixed, fuel assembly to be detected is captured with refueling machine, prepared
Detection.
Step 2, the detection of fuel assembly down process：
When being inserted into one layer of ultrasonic inspection probe test position under fuel assembly ground floor grid spacer,
One layer of ultrasonic inspection probe measures ground floor grid spacer position for X1-1, two layers of ultrasound detection
Probe measurement goes out second layer grid spacer position X2-2；
When being inserted into one layer of ultrasonic inspection probe test position under fuel assembly second layer grid spacer,
One layer of ultrasonic inspection probe measures second layer grid spacer position for X1-2, two layers of ultrasound detection
Probe measurement goes out third layer grid spacer position X2-3；
When being inserted into one layer of ultrasonic inspection probe test position under fuel assembly third layer grid spacer,
One layer of ultrasonic inspection probe measures third layer grid spacer position for X1-3, two layers of ultrasound detection
Probe measurement goes out the 4th layer of grid spacer position X2-4；
……
When being inserted into one layer of ultrasonic inspection probe detecting position under N-1 layers of grid spacer of fuel assembly
Put, one layer of ultrasonic inspection probe measures n-th layer grid spacer position X1-(N-1), two layers surpass
Sound detection probe test position measures n-th layer grid spacer position X2-N。
Step 3, result are calculated：
Step 3.1 fuel assembly bending deformation quantity is calculated：
Each grid spacer position measurement of fuel assembly is as follows：
1st layer of grid spacer position X1=X1-1；
2nd layer of grid spacer relative position X2=X2-2；
3rd layer of grid spacer relative position X3=X2-2+(X2-3-X1-2)；
4th layer of grid spacer relative position X4=X2-2+(X2-3-X1-2)+(X2-4-X1-3)；
5th layer of grid spacer relative position X5=X2-2+(X2-3-X1-2)+(X2-4-X1-3)+
(X2-5-X1-4)；
……
N-th layer grid spacer relative position X13=X2-2+(X2-3-X1-2)+(X2-4-X1-3)
+(X2-5-X1-4)+……+(X2-N-X1-(N-1))；
According to above-mentioned formula, ground floor grid spacer is calculated relative to n-th layer grid spacer
Position, obtains fuel assembly bending deformation quantity.
Step 3.2 fuel assembly torsional deformation amount is calculated：
One layer of ultrasonic inspection probe measures N layers of grid spacer positional distance respectively X11-NWith
X12-N, because fuel assembly has torsional deformation, cause fuel assembly n-th layer grid spacer
It is not parallel with one layer of ultrasonic inspection probe, there is angle α1-n。
According to formula
α1-n=arc cos { L1/(X12-n-X11-n)} (1)
Wherein：L1For in one layer of ultrasonic inspection probe two probe the distance between；
According to same method, calculate N+1 layers of grid spacer of fuel assembly and two layers super
Angle α between sound detection probe2-(n+1)
α2-(n+1)=arc cos { L2/(X22-(n+1)-X21-(n+1))} (2)
Wherein：L2For in two layers of ultrasonic inspection probe two probe the distance between；
N+1 layers of grid spacer is α relative to the N layers of distortion angle of grid spacern+1：
αn+1=α2-(n+1)-α1-n (3)
Step 4, the detection of fuel assembly lifting process：
Method according to step 2 and step 3 is lifted to fuel assembly and detected, lifting process
It is consistent with down process detection method, principle, detected by lifting process, further amendment is missed
Difference, improves fuel assembly deformation detection precision.
Beneficial effects of the present invention：
(1) a kind of fuel assembly deflection bilayer supersonic detection method that the present invention is provided, energy
Fuel assembly deformation detection is enough in, fuel assembly size detection precision is improved；
(2) a kind of fuel assembly deflection bilayer supersonic detection method that the present invention is provided, energy
Other similar continuous physical dimensional measurements are enough applied to, accuracy of detection is improved.
Brief description of the drawings
A kind of fuel assembly deflection bilayer supersonic detection device knot that Fig. 1 is provided for the present invention
Structure schematic diagram；
In a kind of fuel assembly deflection bilayer supersonic detection method that Fig. 2 is provided for the present invention
Torsional deformation amount calculates schematic diagram；
In figure：Mono- layer of ultrasonic inspection probe of 1-, bis- layers of ultrasonic inspection probes of 2-, 3- fixed plates,
4- fixed seats.
Specific embodiment
Below according to a kind of fuel assembly deformation that the drawings and specific embodiments are provided the present invention
The double-deck supersonic detection method of amount is described in detail.
As shown in figure 1, a kind of fuel assembly deflection bilayer ultrasound detection dress that the present invention is provided
Put, including six groups of ultrasonic testing systems and fixed seat 4, six groups of ultrasonic testing systems are uniformly fixed
In fixed seat 4, by taking one of which as an example, ultrasonic testing system includes that one layer of ultrasound detection is visited
First 1, two layers of ultrasonic inspection probe 2 and fixed plate 3；One layer of ultrasonic inspection probe 1 includes two
Individual probe, two layers of ultrasonic inspection probe 2 include two probes, and probe is fixedly mounted on fixed plate
On 3, fixed plate is arranged in fixed seat 4, and fixed plate 4 is hollow ring plate.
A kind of fuel assembly deflection bilayer supersonic detection method that the present invention is provided, including it is following
Step：
Step 1, fuel assembly deformation detection prepare：
Double-deck supersonic detection device is fixed, fuel assembly to be detected is captured with refueling machine, prepared
Detection.
Step 2, the detection of fuel assembly down process：
When being inserted into one layer of detecting position of ultrasonic inspection probe 1 under fuel assembly ground floor grid spacer
Put, one layer of ultrasonic inspection probe 1 measures ground floor grid spacer position for X1-1, two layers surpass
Sound detection probe 2 measures second layer grid spacer position X2-2；
When being inserted into one layer of detecting position of ultrasonic inspection probe 1 under fuel assembly second layer grid spacer
Put, one layer of ultrasonic inspection probe 1 measures second layer grid spacer position for X1-2, two layers surpass
Sound detection probe 2 measures third layer grid spacer position X2-3；
When being inserted into one layer of detecting position of ultrasonic inspection probe 1 under fuel assembly third layer grid spacer
Put, one layer of ultrasonic inspection probe 1 measures third layer grid spacer position for X1-3, two layers surpass
Sound detection probe 2 measures the 4th layer of grid spacer position X2-4；
……
When being inserted into one layer of detecting position of ultrasonic inspection probe 1 under N-1 layers of grid spacer of fuel assembly
Put, one layer of ultrasonic inspection probe 1 measures n-th layer grid spacer position X1-(N-1), two layers
The test position of ultrasonic inspection probe 2 measures n-th layer grid spacer position X2-N。
Step 3, result are calculated：
Step 3.1 fuel assembly bending deformation quantity is calculated：
Each grid spacer position measurement of fuel assembly is as follows：
1st layer of grid spacer position X1=X1-1；
2nd layer of grid spacer relative position X2=X2-2；
3rd layer of grid spacer relative position X3=X2-2+(X2-3-X1-2)；
4th layer of grid spacer relative position X4=X2-2+(X2-3-X1-2)+(X2-4-X1-3)；
5th layer of grid spacer relative position X5=X2-2+(X2-3-X1-2)+(X2-4-X1-3)+
(X2-5-X1-4)；
……
N-th layer grid spacer relative position X13=X2-2+(X2-3-X1-2)+(X2-4-X1-3)
+(X2-5-X1-4)+……+(X2-N-X1-(N-1))；
According to above-mentioned formula, ground floor grid spacer is calculated relative to n-th layer grid spacer
Position, obtains fuel assembly bending deformation quantity.
Step 3.2 fuel assembly torsional deformation amount is calculated：
As shown in Fig. 2 one layer of ultrasonic inspection probe 1 measure N layers of grid spacer position away from
From respectively X11-NAnd X12-N, because fuel assembly has torsional deformation, cause fuel assembly
N-th layer grid spacer is not parallel with one layer of ultrasonic inspection probe 1, there is angle α1-n。
According to formula
α1-n=arc cos { L1/(X12-n-X11-n)} (1)
Wherein：L1For in one layer of ultrasonic inspection probe 1 two probe the distance between；
According to same method, calculate N+1 layers of grid spacer of fuel assembly and two layers super
Angle α between sound detection probe 22-(n+1)
α2-(n+1)=arc cos { L2/(X22-(n+1)-X21-(n+1))} (2)
Wherein：L2For in two layers of ultrasonic inspection probe 2 two probe the distance between；
N+1 layers of grid spacer is α relative to the N layers of distortion angle of grid spacern+1：
αn+1=α2-(n+1)-α1-n (3)
Step 4, the detection of fuel assembly lifting process：
Method according to step 2 and step 3 is lifted to fuel assembly and detected, lifting process
It is consistent with down process detection method, principle, detected by lifting process, further amendment is missed
Difference, improves fuel assembly deformation detection precision.
Claims (2)
1. a kind of fuel assembly deflection bilayer supersonic detection device, it is characterised in that：Including six
Group ultrasonic testing system and fixed seat (4), six groups of ultrasonic testing systems are uniformly fixed on fixed seat
(4) on, ultrasonic testing system includes one layer of ultrasonic inspection probe (1), two layers of ultrasound detection
Probe (2) and fixed plate (3)；One layer of ultrasonic inspection probe (1) includes two probes, two
Layer ultrasonic inspection probe (2) includes two probes, and probe is fixedly mounted in fixed plate (3),
Fixed plate is arranged in fixed seat (4), and fixed plate (4) is hollow ring plate.
2. a kind of fuel assembly deflection bilayer supersonic detection method, it is characterised in that：Including with
Lower step：
Step (1), fuel assembly deformation detection prepare：
Double-deck supersonic detection device is fixed, fuel assembly to be detected is captured with refueling machine, prepared
Detection；
Step (2), the detection of fuel assembly down process：
Detected when one layer of ultrasonic inspection probe (1) is inserted under fuel assembly ground floor grid spacer
Position, one layer of ultrasonic inspection probe (1) measures ground floor grid spacer position for X1-1,
Two layers of ultrasonic inspection probe (2) measure second layer grid spacer position X2-2；
Detected when one layer of ultrasonic inspection probe (1) is inserted under fuel assembly second layer grid spacer
Position, one layer of ultrasonic inspection probe (1) measures second layer grid spacer position for X1-2,
Two layers of ultrasonic inspection probe (2) measure third layer grid spacer position X2-3；
Detected when one layer of ultrasonic inspection probe (1) is inserted under fuel assembly third layer grid spacer
Position, one layer of ultrasonic inspection probe (1) measures third layer grid spacer position for X1-3,
Two layers of ultrasonic inspection probe (2) measure the 4th layer of grid spacer position X2-4；
……
Examined when one layer of ultrasonic inspection probe (1) is inserted under N-1 layers of grid spacer of fuel assembly
Location is put, and one layer of ultrasonic inspection probe (1) measures n-th layer grid spacer position X1-(N-1),
Two layers of ultrasonic inspection probe (2) test position measure n-th layer grid spacer position X2-N；
Step (3), result are calculated：
Step (3.1) fuel assembly bending deformation quantity is calculated：
Each grid spacer position measurement of fuel assembly is as follows：
1st layer of grid spacer position X1=X1-1；
2nd layer of grid spacer relative position X2=X2-2；
3rd layer of grid spacer relative position X3=X2-2+(X2-3-X1-2)；
4th layer of grid spacer relative position X4=X2-2+(X2-3-X1-2)+(X2-4-X1-3)；
5th layer of grid spacer relative position X5=X2-2+(X2-3-X1-2)+(X2-4-X1-3)+
(X2-5-X1-4)；
……
N-th layer grid spacer relative position X13=X2-2+(X2-3-X1-2)+(X2-4-X1-3)
+(X2-5-X1-4)+……+(X2-N-X1-(N-1))；
According to above-mentioned formula, ground floor grid spacer is calculated relative to n-th layer grid spacer
Position, obtains fuel assembly bending deformation quantity；
Step (3.2) fuel assembly torsional deformation amount is calculated：
One layer of ultrasonic inspection probe (1) is measured N layers of grid spacer positional distance and is respectively
X11-NAnd X12-N, because fuel assembly has torsional deformation, cause fuel assembly n-th layer to be determined
Position screen work is not parallel with one layer of ultrasonic inspection probe (1), there is angle α1-n；
According to formula
α1-n=arc cos { L1/(X12-n-X11-n)} (1)
Wherein：L1For in one layer of ultrasonic inspection probe (1) two probe the distance between；
According to same method, calculate N+1 layers of grid spacer of fuel assembly and two layers super
Angle α between sound detection probe (2)2-(n+1)
α2-(n+1)=arc cos { L2/(X22-(n+1)-X21-(n+1))} (2)
Wherein：L2For in two layers of ultrasonic inspection probe (2) two probe the distance between；
N+1 layers of grid spacer is α relative to the N layers of distortion angle of grid spacern+1：
αn+1=α2-(n+1)-α1-n (3)
Step (4), the detection of fuel assembly lifting process：
Method according to step (2) and step (3) is detected to fuel assembly lifting, carried
The process of liter is consistent with down process detection method, principle, is detected by lifting process, further
Round-off error, improves fuel assembly deformation detection precision.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860491.1A CN106813603B (en) | 2015-11-30 | 2015-11-30 | A kind of fuel assembly deflection bilayer supersonic detection method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860491.1A CN106813603B (en) | 2015-11-30 | 2015-11-30 | A kind of fuel assembly deflection bilayer supersonic detection method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106813603A true CN106813603A (en) | 2017-06-09 |
| CN106813603B CN106813603B (en) | 2019-05-17 |
Family
ID=59157174
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510860491.1A Active CN106813603B (en) | 2015-11-30 | 2015-11-30 | A kind of fuel assembly deflection bilayer supersonic detection method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106813603B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5439657A (en) * | 1977-09-02 | 1979-03-27 | Citizen Watch Co Ltd | Outer frame inspection apparatus of nuclear fuel assembly |
| JPH06300547A (en) * | 1993-04-15 | 1994-10-28 | Ngk Insulators Ltd | Bend measurement device for beryllium reflector |
| WO1998018137A1 (en) * | 1996-10-22 | 1998-04-30 | Framatome | Method and device for geometrical control of a fuel assembly by photogrammetry |
| JP2000121347A (en) * | 1998-10-14 | 2000-04-28 | Mitsubishi Heavy Ind Ltd | Instrument and method for shape measurement |
| CN101727996A (en) * | 2008-10-31 | 2010-06-09 | 中国核动力研究设计院 | Method for detecting deformation of fuel assembly after irradiation of pressurized-water reactor nuclear power plant and implementation device thereof |
| CN102667957A (en) * | 2009-11-12 | 2012-09-12 | 阿利发Np有限公司 | Method and device for determining the deformation of a fuel element of a pressurized-water reactor |
| CN104751918A (en) * | 2013-12-31 | 2015-07-01 | 中核武汉核电运行技术股份有限公司 | Deformation measurement device and method for fuel assemblies |
| EP2966652A1 (en) * | 2014-07-08 | 2016-01-13 | Ahlberg Cameras AB | System and method for nuclear fuel assembly deformation measurement |
-
2015
- 2015-11-30 CN CN201510860491.1A patent/CN106813603B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5439657A (en) * | 1977-09-02 | 1979-03-27 | Citizen Watch Co Ltd | Outer frame inspection apparatus of nuclear fuel assembly |
| JPH06300547A (en) * | 1993-04-15 | 1994-10-28 | Ngk Insulators Ltd | Bend measurement device for beryllium reflector |
| WO1998018137A1 (en) * | 1996-10-22 | 1998-04-30 | Framatome | Method and device for geometrical control of a fuel assembly by photogrammetry |
| JP2000121347A (en) * | 1998-10-14 | 2000-04-28 | Mitsubishi Heavy Ind Ltd | Instrument and method for shape measurement |
| CN101727996A (en) * | 2008-10-31 | 2010-06-09 | 中国核动力研究设计院 | Method for detecting deformation of fuel assembly after irradiation of pressurized-water reactor nuclear power plant and implementation device thereof |
| CN102667957A (en) * | 2009-11-12 | 2012-09-12 | 阿利发Np有限公司 | Method and device for determining the deformation of a fuel element of a pressurized-water reactor |
| CN104751918A (en) * | 2013-12-31 | 2015-07-01 | 中核武汉核电运行技术股份有限公司 | Deformation measurement device and method for fuel assemblies |
| EP2966652A1 (en) * | 2014-07-08 | 2016-01-13 | Ahlberg Cameras AB | System and method for nuclear fuel assembly deformation measurement |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106813603B (en) | 2019-05-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103336055B (en) | Method for ultrasonically detecting weld quality of main loop pipeline of nuclear power plant by phased array | |
| CN106093205A (en) | A kind of thick-walled structure defect inspection method based on the ultrasonic synthetic aperture focusing of oblique incidence | |
| CN108844978A (en) | It is a kind of for detecting the new method of honeycomb interior defect | |
| CN102998369B (en) | A kind of two dimension damage quantitative monitoring method | |
| CN105823582B (en) | A kind of short sound path ultrasonic non-destructive probe of deep camber component surface residual stress | |
| CN105866252A (en) | Method for positioning of small-and-medium rectangular box acoustic emission sources | |
| CN102537669A (en) | Method and system for detecting pipeline defect based on ultrasonic guided wave focusing | |
| CN107101756A (en) | A kind of method for measuring inside workpiece residual stress | |
| CN104142367A (en) | Ultrasonic detection method for nuclear power plant containment concrete defects | |
| CN103412053A (en) | Wave-velocity-free acoustic emission source locating method based on acoustic emission sensor arrays and wave beam formation | |
| CN103868987A (en) | Eddy detection probe for detecting surface multiple cracks of conductive structure and detection method thereof | |
| CN102506804B (en) | Device and method for measuring turning angle of cross section at 2D length position of middle part of tested pipe | |
| CN106935291A (en) | A kind of fuel assembly deflection bilayer measuring system and measuring method | |
| CN209542519U (en) | The ultrasonic scan imaging device of multifunction high-precision | |
| CN106813603A (en) | A kind of fuel assembly deflection bilayer supersonic detection method | |
| CN106017763A (en) | Supersonic residual stress measuring method capable of correcting influence of microscopic organization difference | |
| Trelinski | Inspection of CANDU reactor pressure tubes using ultrasonics | |
| CN205451794U (en) | Double -deck measurement system of fuel assembly deflection | |
| CN106229019A (en) | A kind of irradiation after-burning charge bar Diameter Measurement System under water and measuring method thereof | |
| CN106935285A (en) | AP1000 nuclear power plant containment shell deformation detecting methods | |
| CN202837254U (en) | Reference block for ultrasonic flaw of large protection ring for rotor of generator in thermal power plant | |
| KR101131996B1 (en) | An Eddy Current Examination Method for the Outside Diameter Axial Cracks in Steam Generator Tubes Using Motorized Rotating Pancake Coil | |
| CN207248826U (en) | Boiler 12Cr1MoV low-temperature reheater inside pipe wall etch pit ultrasound detection Special test blocks | |
| CN106091894A (en) | A kind of detection method of turbine rotor blade | |
| CN206269984U (en) | Bolt joint portion normal stiffness test device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |