CN106091881B - Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method - Google Patents
Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method Download PDFInfo
- Publication number
- CN106091881B CN106091881B CN201610423632.8A CN201610423632A CN106091881B CN 106091881 B CN106091881 B CN 106091881B CN 201610423632 A CN201610423632 A CN 201610423632A CN 106091881 B CN106091881 B CN 106091881B
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- outer shroud
- fixed blade
- blade ring
- ring outer
- gas turbine
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/02—Measuring arrangements characterised by the use of mechanical techniques for measuring length, width or thickness
Abstract
Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method, it is related to mechanical measurement tool and the measurement method using the tool, with solve the problems, such as at present can not be to the horizontal plane range measurement of the bottom surface of fixed blade ring outer shroud dovetail groove to fixed blade ring outer shroud center line, it includes pedestal, measures body and two bolts；Gas turbine fixed blade ring outer shroud is placed on the arc surface of pedestal, it includes tablet and dovetail to measure body；It is equipped with bolt on pinned hole and pin hole.Measurement method mainly comprises the following steps：Step 1: gas turbine fixed blade ring outer shroud is placed on the arc surface of pedestal, the end of dovetail is placed in the dovetail groove of gas turbine fixed blade ring outer shroud, bolt is inserted on pinned hole and pin hole successively；Step 2: the calculating distance between the upper surface of calculate flat board and the lower face of pedestal.Center line horizontal plane range measurement of the present invention for fixed blade ring outer shroud dovetail groove bottom to gas turbine fixed blade ring outer shroud.
Description
Technical field
The present invention relates to the measurement methods of mechanical measurement tool and the use tool.
Background technology
Gas turbine fixed blade ring is most crucial one of the component of gas turbine.Fixed blade ring outer shroud dovetail groove bottom is to combustion gas wheel
The distance of the center line horizontal plane of machine fixed blade ring outer shroud, decides stator blade assembling quality in fixed blade ring, directly affects combustion gas
Therefore the efficiency of turbine unit measures the bottom surface of fixed blade ring outer shroud dovetail groove to the center line water of gas turbine fixed blade ring outer shroud
Flat plan range is particularly significant.
Invention content
The present invention is for solve at present can not be to the water of the bottom surface of fixed blade ring outer shroud dovetail groove to fixed blade ring outer shroud center line
The problem of flat plan range measures, and then a kind of gas turbine fixed blade ring outer shroud dovetail groove survey tool of offer and method.
The present invention adopts the technical scheme that in order to solve the above problem：
Gas turbine fixed blade ring outer shroud dovetail groove survey tool includes pedestal, measures body and two bolts；
Pedestal is arc-shaped base, and the upper surface of pedestal is the circular arc to match with the extrados of gas turbine fixed blade ring outer shroud
Face；Gas turbine fixed blade ring outer shroud is placed on the arc surface of pedestal, it includes tablet and dovetail to measure body；The root of dovetail
It is connected with horizontally disposed tablet, the end of dovetail is placed in the dovetail groove of gas turbine fixed blade ring outer shroud, is located at dovetail groove
There are two pin holes for setting on the pedestal at length direction both ends；
There are two pinned holes for processing on tablet；Face is arranged one by one respectively for pinned hole and pin hole, pinned hole and pin hole
On be equipped with bolt, the gear of bolt is along acting against on the upper surface of tablet.
Gas turbine fixed blade ring outer shroud dovetail groove measurement method follows the steps below：
Step 1: gas turbine fixed blade ring outer shroud is placed on the arc surface of pedestal, the end of dovetail is placed in combustion
In the dovetail groove of gas-turbine fixed blade ring outer shroud, bolt is inserted on pinned hole and pin hole successively, the gear edge of bolt acts against
On the upper surface of tablet, gas turbine fixed blade ring outer shroud is made to be located between two bolts；
Step 2: the extrados design radial of gas turbine fixed blade ring outer shroud is R, under the upper surface and dovetail of tablet
Designed distance between end face is X, and arc surface minimum point to the designed distance between the lower face of pedestal of pedestal is Y, dovetail
The designed distance at the bottom surface of slot to the center of gas turbine fixed blade ring outer shroud is M, obtains K0=X+Y+R-M, wherein K0For tablet
Calculating distance between upper surface and the lower face of pedestal, the measurement distance between the upper surface of tablet and the lower face of pedestal are
K, K-K0=H, if the margins of tolerance of the H beyond dovetail groove bottom to the designed distance M at the center of gas turbine fixed blade ring outer shroud,
Then the designed distance M at dovetail groove bottom to the center of gas turbine fixed blade ring outer shroud is unqualified, needs to re-work gas turbine
Fixed blade ring outer shroud, until H falls the margin of tolerance in dovetail groove bottom to the designed distance M at the center of gas turbine fixed blade ring outer shroud
It is interior, at this point, the processing of gas turbine fixed blade ring outer shroud is qualified.
The beneficial effects of the invention are as follows：The configuration of the present invention is simple, reasonable design can measure the slot bottom of dovetail groove to combustion gas wheel
The distance of machine fixed blade ring outer shroud center line horizontal plane, is measured with indirect method outside the slot bottom to gas turbine fixed blade ring of dovetail groove
The distance of ring center line horizontal plane can very easily measure indirect size with the measurement of this survey tool, be measured to reach
Purpose.The present invention is used for the bottom surface of gas turbine fixed blade ring outer shroud dovetail groove to the horizontal plane distance of fixed blade ring outer shroud center line
It measures, greatly improves stator blade assembling quality in fixed blade ring.
Description of the drawings
Fig. 1 is the front view of gas turbine fixed blade ring outer shroud dovetail groove survey tool of the present invention；
Fig. 2 is the vertical view of Fig. 1；
The pedestal front view that Fig. 3 is；
Fig. 4 is the vertical view of Fig. 3；
Fig. 5 is to measure body front view；
Fig. 6 is the vertical view of Fig. 5；
Fig. 7 is No.1 latch structure schematic diagram；
Fig. 8 is No. two latch structure schematic diagrames；
Fig. 9 is to use gas turbine fixed blade ring outer shroud schematic top plan view；
Figure 10 is the schematic diagram of the dovetail groove of gas turbine fixed blade ring outer shroud in Fig. 9；
Figure 11 is the vertical view of Fig. 9.
Specific implementation mode
Specific implementation mode one：Illustrate in conjunction with Fig. 1-Figure 11, the gas turbine fixed blade ring outer shroud dovetail groove of present embodiment
Survey tool, it includes pedestal 1, measures body 2 and two bolts 3；
Pedestal 1 is arc-shaped base, and the upper surface of pedestal 1 is to match with the extrados of gas turbine fixed blade ring outer shroud 4
Arc surface；Gas turbine fixed blade ring outer shroud 4 is placed on the arc surface of pedestal 1, it includes tablet 2-1 and dovetail 2- to measure body 2
2；The root of dovetail 2-2 is connected with horizontally disposed tablet 2-1, and the end of dovetail 2-2 is placed in outside gas turbine fixed blade ring
In the dovetail groove 4-1 of ring 4, being located at setting on the pedestal 1 at dovetail groove 4-1 length directions both ends, there are two pin hole 1-1；
There are two pinned hole 2-3 for processing on tablet 2-1；Face is arranged pinned hole 2-3 and pin hole 1-1 one by one respectively, wears
Bolt 3 is equipped on pin hole 2-3 and pin hole 1-1, the gear edge of bolt 3 acts against on the upper surface of tablet 2-1.
The angled horizontal central lines for being distributed in gas turbine fixed blade ring outer shroud of two pin hole 1-1 of present embodiment
The both sides EF.Two bolts 3 of present embodiment are the pin of diameter different band handle.As shown in figure 3, two pin hole 1-1
The internal diameter of one of pin hole 1-1 is less than the internal diameter of another pin hole 1-1；One of two pinned hole 2-3 wear pin
The internal diameter of hole 2-3 be less than another pinned hole 2-3 internal diameter, one of pin hole 1-1 with it is described one of them wear pin
The aperture of hole 2-3 matches, the aperture of another pin hole 1-1 and another pinned hole 2-3 match.Bolt 3
Gear along referring to single order table top 3-1.
Specific implementation mode two：It is illustrated with reference to Fig. 1, the line of centres CD and water of two pin hole 1-1 of present embodiment
Angle theta between flat center line EF is 56 °.So set, meeting the design requirements and the actual needs.Other and specific implementation mode one
It is identical.
Specific implementation mode three：Illustrate in conjunction with Fig. 3, the lower face of the pedestal 1 of present embodiment is rectangular end face.So set
It sets, stable structure is reliable, meets the design requirements and the actual needs.It is other the same as one or two specific embodiments.
Specific implementation mode four：Illustrate in conjunction with Fig. 1-Figure 11, the gas turbine fixed blade ring outer shroud dovetail groove of present embodiment
Measurement method follows the steps below：
Step 1: gas turbine fixed blade ring outer shroud 4 is placed on the arc surface of pedestal 1, the end of dovetail 2-2 is set
In in the dovetail groove 4-1 of gas turbine fixed blade ring outer shroud 4, bolt 3 is inserted into successively on pinned hole 2-1 and pin hole 1-1, is inserted
The gear of pin 3 makes gas turbine fixed blade ring outer shroud 4 be located between two bolts 3 along acting against on the upper surface of tablet 2-1；
Step 2: the extrados design radial of gas turbine fixed blade ring outer shroud 4 is R, the upper surface of tablet 2-1 and dovetail
Designed distance between the lower face of 2-2 is X, the arc surface minimum point of pedestal 1 to the designed distance between the lower face of pedestal 1
Designed distance for Y, bottom surface to the center of gas turbine fixed blade ring outer shroud 4 of dovetail groove 4-1 is M, obtains K0=X+Y+R-M,
Wherein K0For the calculating distance between the upper surface and the lower face of pedestal 1 of tablet 2-1, upper surface and the pedestal 1 of tablet 2-1
Measurement distance between lower face is K, K-K0=H, if H is beyond in dovetail groove bottom to gas turbine fixed blade ring outer shroud 4
The margin of tolerance of the designed distance M of the heart, then the designed distance M of dovetail groove bottom to the center of gas turbine fixed blade ring outer shroud 4 is not
Qualification needs to re-work gas turbine fixed blade ring outer shroud 4, until, H is fallen in the bottom surfaces dovetail groove 4-1 to gas turbine fixed blade ring
In the margin of tolerance of the designed distance M at the center of outer shroud 4, at this point, gas turbine fixed blade ring outer shroud 4 processes qualification.
Present embodiment is according to K values and theoretical value K0Compare, you can show whether M values are qualified.Also it just completes using combustion
The measurement of gas-turbine fixed blade ring outer shroud dovetail groove survey tool.The slot bottom of the dovetail groove of present embodiment is to gas turbine fixed blade ring
The distance of the center line horizontal plane of outer shroud refers to the straight line that the slot bottom of dovetail groove arrived the center of gas turbine fixed blade ring outer shroud
Vertical range between the horizontal plane of place.Indirect method measures dovetail groove bottom to the distance of center line horizontal plane, is surveyed with this
The measurement of amount tool can very easily measure indirect size, to reach measurement purpose.The present invention is used for gas turbine fixed blade ring
Horizontal plane range measurement of the bottom surface of outer shroud dovetail groove to fixed blade ring outer shroud center line.
Claims (4)
1. gas turbine fixed blade ring outer shroud dovetail groove survey tool, it is characterised in that：It includes pedestal（1）, measure body（2）With two
A bolt（3）；
Pedestal（1）For arc-shaped base, pedestal（1）Upper surface be and gas turbine fixed blade ring outer shroud（4）Extrados match
Arc surface；Pedestal（1）Arc surface on be placed with gas turbine fixed blade ring outer shroud（4）, measure body（2）Including tablet（2-1）
And dovetail（2-2）；Dovetail（2-2）Root be connected with horizontally disposed tablet（2-1）, dovetail（2-2）End set
In gas turbine fixed blade ring outer shroud（4）Dovetail groove（4-1）It is interior, it is located at dovetail groove（4-1）The pedestal at length direction both ends（1）On
There are two pin holes for setting（1-1）；
Tablet（2-1）There are two pinned holes for upper processing（2-3）；Pinned hole（2-3）And pin hole（1-1）Face is set one by one respectively
It sets, pinned hole（2-3）And pin hole（1-1）On be equipped with bolt（3）, bolt（3）Gear along acting against tablet（2-1）Upper end
On face.
2. gas turbine fixed blade ring outer shroud dovetail groove survey tool according to claim 1, it is characterised in that：Two bolts
Hole（1-1）The line of centres（CD）With horizontal central line（EF）Between angle（θ）It is 56 °.
3. gas turbine fixed blade ring outer shroud dovetail groove survey tool according to claim 1 or 2, it is characterised in that：Pedestal
（1）Lower face be rectangular end face.
4. the method for measuring dovetail groove using the gas turbine fixed blade ring outer shroud dovetail groove survey tool described in claims 1 or 22,
It is characterized in that：The gas turbine fixed blade ring outer shroud dovetail groove measurement method follows the steps below：
Step 1: by gas turbine fixed blade ring outer shroud（4）It is placed on pedestal（1）Arc surface on, by dovetail（2-2）End
It is placed in gas turbine fixed blade ring outer shroud（4）Dovetail groove（4-1）It is interior, by bolt（3）It is inserted into pinned hole successively（2-1）And bolt
Hole（1-1）On, bolt（3）Gear along acting against tablet（2-1）Upper surface on, make gas turbine fixed blade ring outer shroud（4）It is located at
Two bolts（3）Between；
Step 2: gas turbine fixed blade ring outer shroud（4）Extrados design radial be（R）, tablet（2-1）Upper surface and dovetail
Tenon（2-2）Lower face between designed distance be X, pedestal（1）Arc surface minimum point to pedestal（1）Lower face between
Designed distance is Y, dovetail groove（4-1）Bottom surface to gas turbine fixed blade ring outer shroud（4）Center designed distance be M, obtain
K0=X+Y+R-M, wherein K0For tablet（2-1）Upper surface and pedestal（1）Lower face between calculating distance, tablet（2-1）
Upper surface and pedestal（1）Lower face between measurement distance be K, K-K0=H, if H is beyond dovetail groove bottom to combustion gas wheel
Machine fixed blade ring outer shroud（4）Center designed distance M the margin of tolerance, then dovetail groove（4-1）Bottom surface is to gas turbine fixed blade ring
Outer shroud（4）Center designed distance M it is unqualified, need to re-work gas turbine fixed blade ring outer shroud（4）, until H is fallen in swallow
Stern notch bottom surface is to gas turbine fixed blade ring outer shroud（4）Center designed distance M the margin of tolerance in, at this point, gas turbine is quiet
Leaf joint outer shroud（4）Processing is qualified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610423632.8A CN106091881B (en) | 2016-06-15 | 2016-06-15 | Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610423632.8A CN106091881B (en) | 2016-06-15 | 2016-06-15 | Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106091881A CN106091881A (en) | 2016-11-09 |
| CN106091881B true CN106091881B (en) | 2018-07-27 |
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ID=57845596
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610423632.8A Active CN106091881B (en) | 2016-06-15 | 2016-06-15 | Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method |
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| CN (1) | CN106091881B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112548485A (en) * | 2020-10-27 | 2021-03-26 | 中国船舶重工集团公司第七0三研究所 | Non-impact press-fitting method for stationary blade ring of gas turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101456141A (en) * | 2007-12-14 | 2009-06-17 | 上海电气电站设备有限公司 | Combustion-engine fixed blade ring exterior-ring sheave-groove processing feeler-block |
| CN201653336U (en) * | 2010-01-18 | 2010-11-24 | 成都发动机（集团）有限公司 | General measuring instrument of high pressure air compressor turntable mortise |
| CN102818527A (en) * | 2012-07-11 | 2012-12-12 | 沈阳富创精密设备有限公司 | Method for measuring size of opening of transition arc dovetail groove |
| CN104501754A (en) * | 2014-10-14 | 2015-04-08 | 哈尔滨汽轮机厂有限责任公司 | Measuring tool for dovetail groove of gas turbine disk and measuring method using same |
-
2016
- 2016-06-15 CN CN201610423632.8A patent/CN106091881B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101456141A (en) * | 2007-12-14 | 2009-06-17 | 上海电气电站设备有限公司 | Combustion-engine fixed blade ring exterior-ring sheave-groove processing feeler-block |
| CN201653336U (en) * | 2010-01-18 | 2010-11-24 | 成都发动机（集团）有限公司 | General measuring instrument of high pressure air compressor turntable mortise |
| CN102818527A (en) * | 2012-07-11 | 2012-12-12 | 沈阳富创精密设备有限公司 | Method for measuring size of opening of transition arc dovetail groove |
| CN104501754A (en) * | 2014-10-14 | 2015-04-08 | 哈尔滨汽轮机厂有限责任公司 | Measuring tool for dovetail groove of gas turbine disk and measuring method using same |
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| Publication number | Publication date |
|---|---|
| CN106091881A (en) | 2016-11-09 |
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