CN107932057B - A kind of aero-engine power turbine torch measuring system assembly method - Google Patents
A kind of aero-engine power turbine torch measuring system assembly method Download PDFInfo
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- CN107932057B CN107932057B CN201711126631.8A CN201711126631A CN107932057B CN 107932057 B CN107932057 B CN 107932057B CN 201711126631 A CN201711126631 A CN 201711126631A CN 107932057 B CN107932057 B CN 107932057B
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- latch
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- clamping sleeve
- plug
- output shaft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
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- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A kind of aero-engine power turbine torch measuring system assembly method, the aero-engine power turbine torch measuring system is formed by passing through reference axis, output shaft, clamping sleeve, reference rings that two latch successively connect from inside to outside, it includes the following steps: step A, one the first plug is provided and assembles the clamping sleeve, step B provides second plug and assembles the reference rings.A kind of aero-engine power turbine torch measuring system assembly method provided by the present invention can ensure datum tooth and survey and turn round tooth angle degree and disposably assemble qualification, latch once mounting in place, to provide production efficiency significantly.
Description
Technical field
The present invention relates to aero-engine mounting technology field, in particular to a kind of aero-engine power turbine is turned round
Square measuring system assembly method.
Background technique
Fig. 1 is a kind of partial cross principle schematic diagram of aero-engine power turbine torch measuring system,
Fig. 2 be Fig. 1 A-A sectional structure schematic illustration, Fig. 2 mainly for illustrate survey turn round tooth and datum tooth positional relationship, referring to
Shown in Fig. 1-2, the aero-engine power turbine torch measuring system by successively being connected from inside to outside by two latch 5
Reference axis 1, output shaft 2, clamping sleeve 3, the composition of reference rings 4 connect, clamping sleeve 3 are provided in 180 ° of symmetrical two excitations
Tooth that is to say that tooth 31 is turned round in survey, is provided in the reference rings 4 in 180 ° of symmetrical two datum tooths 41, tooth 31 is turned round in the survey
Typical torque measurement structure is formed with the datum tooth 41.
Fig. 3 is the structural schematic diagram of the output shaft and reference axis of Fig. 1 in assembled state, shown in Figure 3, the latch
5 be straight pin, and the first connecting hole 11 that the reference axis 1 is used to connect the latch 5 is circular hole, and the output shaft 2 is used for
The second connecting hole 21 for connecting latch 5 is waist-shaped hole, maximum radially of second connecting hole 21 in the output shaft 1
Size L2 is greater than the diameter of the latch 5.The clamping sleeve 3 is used to connect the third connecting hole and described second of latch 5
21 shape of connecting hole, size are identical, and the reference rings 4 are used to connect the 4th connecting hole and first connecting hole of latch 5
11 shapes, size are identical.The latch 5 is interference fit with the reference axis 2, the reference rings 4.For example, described first
The diameter D1 of connecting hole 11 can be 0.01mm bigger than the diameter of the latch 5, also means that the straight of the 4th connecting hole
Diameter is 0.01mm bigger than the diameter of the latch 5.
It is shown in Figure 2, the assembling process of aero-engine power turbine torch measuring system shown in Fig. 1
In, ensure that the benchmark angle α of the axis for surveying torsion tooth 31 and the datum tooth 41 is assembly key point and difficult point, the benchmark
The angle of tooth 31 and the datum tooth 41 is turned round in the survey that angle α can be the upper left corner at the visual angle A-A, and numberical range need to be
90 ° (- 20 '~-1 ° 20 '), the benchmark angle α is for example unqualified, directly affects the accuracy of sensor measurement data, to starting
Machine causes severe compromise.But benchmark angle α adjustment nargin is natively small, and the diameter of output shaft 2 and reference axis 1 is all smaller
Cause angularly to adjust sensitivity requirement height, and the angle measurement is difficult in assembling, it is difficult to it controls；Again because the latch 5 is distinguished
It is interference fit with the reference axis 1, the reference rings 4, and the clamping sleeve 3 and the output shaft 2 are also interference fit, because
Once this benchmark angle α is unqualified, because can not adjust under component states, destructive decomposition is just needed, cause increase assembly period,
The production cost increases.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of aero-engine power turbine torch measuring system dresses
Method of completing the square, the problem of being formerly mentioned is reduced or avoided.
In order to solve the above technical problems, the invention proposes a kind of aero-engine power turbine torch measuring systems
Assembly method, the aero-engine power turbine torch measuring system by successively being connected from inside to outside by two latch
Reference axis, output shaft, clamping sleeve, the reference rings composition connect, clamping sleeve are provided in 180 ° of symmetrical two excitation teeth
It is to survey to turn round tooth, is provided in the reference rings in 180 ° of symmetrical two datum tooths, the latch is straight pin, institute
Stating first connecting hole of the reference axis for connecting the latch is circular hole, and the output shaft is used to connect the second company of latch
Connecing hole is waist-shaped hole, and second connecting hole is greater than the straight of the latch in the full-size radially of the output shaft
Diameter.The third connecting hole that the clamping sleeve is used to connect latch is identical as the second connection hole shape, size, the benchmark
The 4th connecting hole that ring is used to connect latch is identical as the first connection hole shape, size.The latch respectively with institute
Reference axis, the reference rings are stated as interference fit, and the clamping sleeve and the output shaft are also interference fit comprising as follows
Step:
Step A assembles the clamping sleeve, provides first plug, and first plug includes the first cylindrical section and waist
The diameter of shape shell of column, first cylindrical section is 0.01-0.02mm smaller than the diameter of first connecting hole of the reference axis,
The radial full-size of the kidney-shaped shell of column=second connecting hole full-size-[(exports described in π *
Axis outer diameter/360) * (90 ° of-∠ A)],
In above formula, the value of ∠ A is the numberical range surveyed and turn round the benchmark angle of axis of tooth and the datum tooth,
First by the output sleeve on the reference axis, keep first connecting hole corresponding with second connecting hole,
Then it will quickly be covered on the output shaft after clamping sleeve heating, and be inserted into first plug, make first cylinder
Section is inserted into first connecting hole, rotates the clamping sleeve later, makes the section movement surveyed and turn round benchmark angle described in teeth directional
It is close to the kidney-shaped shell of column to the clamping sleeve, after the clamping sleeve is cooling, pulls up first plug.
Step B assembles the reference rings, provides second plug, and second plug includes the second cylindrical section and handle
The diameter of means, second cylindrical section is 0.01-0.02mm smaller than the diameter of the circular hole of the reference axis, second circle
The length of shell of column is more than or equal to the length of the latch, by the benchmark ring set on the mounted clamping sleeve of step A,
Keep the 4th connecting hole corresponding with the third connecting hole, and two opposite third connecting holes is made to be located at horizontal position
It sets, second plug is inserted into the 4th connecting hole, second cylindrical section is made to be inserted into first connecting hole
Then the latch is assembled in place in the 4th connecting hole of the other end, removes second plug later by bottom,
And assemble second latch in place in corresponding position, so far complete the aero-engine power turbine torque
The assembly of measuring system.
Preferably, in step, the ∠ A value range is 90 ° (- 1 °~-40 ').
It preferably, in stepb, first will be after the latch liquid nitrogen cooling during assembling the latch
It is reloaded into.
A kind of aero-engine power turbine torch measuring system assembly method provided by the present invention, can ensure base
Quasi- tooth and survey and turn round tooth angle degree and disposably assemble qualification, latch once mounting in place, to provide production efficiency significantly.
Detailed description of the invention
The following drawings are only intended to schematically illustrate and explain the present invention, not delimit the scope of the invention.Wherein,
Fig. 1 is a kind of partial cross principle schematic diagram of aero-engine power turbine torch measuring system；
Fig. 2 is the A-A sectional structure schematic illustration of Fig. 1；
Structural schematic diagram of the output shaft and reference axis that Fig. 3 is Fig. 1 in assembled state；
Fig. 4 is a kind of aero-engine power turbine torque measurement system of a specific embodiment according to the present invention
The stereochemical structure schematic illustration of first plug of bulk cargo method of completing the square；
Fig. 5 is the cross section structure schematic diagram of the kidney-shaped shell of column of Fig. 4；
Fig. 6 is the operation principle schematic diagram of the first plug of Fig. 4；
Fig. 7 is the stereochemical structure schematic illustration of the second plug matched with the first plug of Fig. 4；
Fig. 8 is the principle schematic diagram of the second plug of Fig. 7.
Specific embodiment
For a clearer understanding of the technical characteristics, objects and effects of the present invention, this hair of Detailed description of the invention is now compareed
Bright specific embodiment.Wherein, identical component uses identical label.
Fig. 1 is a kind of partial cross principle schematic diagram of aero-engine power turbine torch measuring system；
Fig. 2 is the A-A sectional structure schematic illustration of Fig. 1；Structural representation of the output shaft and reference axis that Fig. 3 is Fig. 1 in assembled state
Figure；Fig. 4 is that a kind of aero-engine power turbine torch measuring system of a specific embodiment according to the present invention fills
The stereochemical structure schematic illustration of first plug of method of completing the square；Fig. 5 is the cross section structure schematic diagram of the kidney-shaped shell of column of Fig. 4；Fig. 6 is
The operation principle schematic diagram of the first plug of Fig. 4；Fig. 7 is that the stereochemical structure of the second plug matched with the first plug of Fig. 4 is former
Manage schematic diagram；Fig. 8 is the principle schematic diagram of the second plug of Fig. 7.Referring to shown in Fig. 1-8, the present invention provides a kind of boats
Empty engine power turbine rotor torch measuring system assembly method, the aero-engine power turbine torque measurement system
System is formed by passing through the reference axis 1 that two latch 5 successively connect from inside to outside, output shaft 2, clamping sleeve 3, reference rings 4, is compressed
Set 3, which is provided with, that is to say that tooth 31 is turned round in survey in 180 ° of symmetrical two excitation teeth, and it is right in 180 ° to be provided in the reference rings 4
Claim two datum tooths 41 of distribution, the latch 5 is straight pin, and the reference axis 1 is for connecting the first of the latch 5
Connecting hole 11 is circular hole, and the second connecting hole 21 that the output shaft 2 is used to connect latch 5 is waist-shaped hole, second connection
Hole 21 is greater than the diameter of the latch 5 in the full-size L2 radially of the output shaft 1.The clamping sleeve 3 is for connecting
The third connecting hole for connecing latch 5 is identical as 21 shape of the second connecting hole, size, and the reference rings 4 are for connecting stop
4th connecting hole of pin 5 is identical as 11 shape of the first connecting hole, size.The latch 5 respectively with the reference axis 1,
The reference rings 4 are interference fit, and the clamping sleeve 3 and the output shaft 1 are also interference fit comprising following steps:
Step A assembles the clamping sleeve 3, provides first plug 6, and first plug 6 includes the first cylindrical section 61
It is smaller than the diameter D1 of first connecting hole 11 of the reference axis 1 with the diameter of kidney-shaped shell of column 62, first cylindrical section 61
0.01-0.02mm,
Full-size L2- [(the π * of second connecting hole 21 described in the radial full-size L1=of the kidney-shaped shell of column 62
1 outer diameter D/360 of output shaft) * (90 ° of-∠ A)],
In above formula, the value range of ∠ A is the number surveyed and turn round the benchmark angle α of axis of tooth 31 and the datum tooth 41
It is worth range,
For example, as stated in the background art, since the numberical range of the benchmark angle α is 90 ° (- 20 '~-1 ° 20 '), because
This ∠ A can value be 89 ° 80 ', be also possible to 80 °, can also be 88 ° 80 '.
First by 2 sets of the output shaft on the reference axis 1, make first connecting hole 11 and second connecting hole 21
It is corresponding, it then will quickly cover on the output shaft 2, and be inserted into first plug 6, make described after the clamping sleeve 3 heating
First cylindrical section 62 is inserted into first connecting hole 11, rotates the clamping sleeve 3 later, and the survey is made to turn round tooth 31 to the benchmark
The section of angle α moves to the clamping sleeve 3 and is close to the kidney-shaped shell of column 62, after the clamping sleeve 3 is cooling, pulls up described the
One plug 6.
As described in background, because the latch 5 is matched respectively with the reference axis 1, the reference rings 4 for interference
It closes, and the clamping sleeve 3 and the output shaft 2 are also interference fit, therefore, as long as can ensure that tooth 31 is turned round in the survey in assembly
The position for surveying torsion tooth 31 and the datum tooth 41 can be also ensured with the position of the reference axis 1.The present invention passes through described
First plug 6 enables the clamping sleeve 3 once to assemble in place,
Referring to fig. 2, can making the third connecting hole with the reference axis 1 after rotating the clamping sleeve 3 shown in 6
The plane of symmetry 300 of axis perpendicular be subjected to displacement, that is, the axis 100 of the plane of symmetry 300 and first plug 6 produces
Gap is given birth to, also means that forming the survey of benchmark angle α torsion tooth 31 can move to the section of the benchmark angle α,
So as to ensure 3 once mounting of clamping sleeve in place by the radial full-size L1 for controlling the kidney-shaped shell of column 62.
In view of mismatch error, the value of the ∠ A can be further reduced in the numberical range of the benchmark angle α,
For example, the ∠ A may be selected to be 90 ° (- 1 °~-40 ').
Step B assembles the reference rings 4, provides second plug 7, and second plug 7 includes the second cylindrical section 71
With means 72, the diameter of second cylindrical section 71 is 0.01- smaller than the diameter D1 of the circular hole 21 of the reference axis 2
0.02mm, the length L3 of second cylindrical section 71 are more than or equal to the length L4 of the latch 5, and 4 sets of reference rings are existed
On the mounted clamping sleeve 3 of step A, keep the 4th connecting hole corresponding with the third connecting hole, and make two it is opposite
The third connecting hole be horizontally situated, by second plug 7 be inserted into the 4th connecting hole, make described second
Cylindrical section 71 is inserted into 11 bottom of the first connecting hole, then by the latch in the 4th connecting hole of the other end
5 assembly in place, remove second plug 7, and assemble second latch 5 in place, so far in corresponding position later
Complete the assembly of the aero-engine power turbine torch measuring system.
It is described to survey the position for turning round tooth 31 and first connecting hole 11 after completing the assembly of the clamping sleeve 3 of step A
Relationship it has been determined that and the latch 5 and first connecting hole 11, the 4th connecting hole are interference fit, therefore, lead to
It crosses and second cylindrical section 71 is inserted into 11 bottom of the first connecting hole, the achievable reference rings 4 and the reference axis 1
First positioning, then the 4th connecting hole described in the other end to first connecting hole 11 by the latch 5 assemble in place, i.e.,
The position that the datum tooth 41 can be fixed then takes out second plug 7, in the 4th connecting hole side vacated by institute
State the assembly of latch 5 can be completed entire assembling process in place.
It, can be straight using tools such as hammers in the normal temperature state of the latch 5 during assembling latch 5
It connects and knocks in, can also first be reloaded into (such as 5 minutes cooling in being immersed in liquid nitrogen) after the latch 5 liquid nitrogen cooling.
It is described that means 72 are mainly used for convenient for holding and operating second plug 7 therefore described that means 72 are settable
Just like planar portions shown in Fig. 7,8, so as to be easy to use tool clamping.
A kind of aero-engine power turbine torch measuring system assembly method provided by the present invention, can ensure base
Quasi- tooth and survey and turn round tooth angle degree and disposably assemble qualification, latch once mounting in place, to provide production efficiency significantly.
It will be appreciated by those skilled in the art that although the present invention is described in the way of multiple embodiments,
It is that not each embodiment only contains an independent technical solution.So narration is used for the purpose of for the sake of understanding in specification,
The skilled in the art should refer to the specification as a whole is understood, and by technical solution involved in each embodiment
Regard as and can be combined with each other into the modes of different embodiments to understand protection scope of the present invention.
The foregoing is merely the schematical specific embodiment of the present invention, the range being not intended to limit the invention.It is any
Those skilled in the art, made equivalent variations, modification and combination under the premise of not departing from design and the principle of the present invention,
It should belong to the scope of protection of the invention.
Claims (2)
1. a kind of aero-engine power turbine torch measuring system assembly method, which is characterized in that the aeroplane engine
Reference axis, the output shaft, pressure that mechanomotive force turbine rotor torch measuring system is successively connected from inside to outside by passing through two latch
Fixed, reference rings composition, clamping sleeve, which is provided with, that is to say that tooth, the reference rings are turned round in survey in 180 ° of symmetrical two excitation teeth
On be provided in 180 ° of symmetrical two datum tooths, the latch is straight pin, and the reference axis is described for connecting
First connecting hole of latch is circular hole, and the second connecting hole that the output shaft is used to connect latch is waist-shaped hole, described the
Two connecting holes are greater than the diameter of the latch in the full-size radially of the output shaft, and the clamping sleeve is for connecting
The third connecting hole of latch is identical as second connection hole shape, the size, and the reference rings are used to connect the of latch
Four connecting holes are identical as the first connection hole shape, size, and the latch is with the reference axis, the reference rings respectively
Interference fit, and the clamping sleeve and the output shaft are also interference fit comprising following steps:
Step A assembles the clamping sleeve, provides first plug, and first plug includes the first cylindrical section and kidney-shaped column
Section, the diameter of first cylindrical section is 0.01-0.02mm smaller than the diameter of first connecting hole of the reference axis,
The radial full-size of the kidney-shaped shell of column=second connecting hole full-size-is [(outside output shaft described in π *
Diameter/360) * (90 ° of-∠ A)],
In above formula, the value range of ∠ A is the numberical range surveyed and turn round the benchmark angle of axis of tooth and the datum tooth,
First by the output sleeve on the reference axis, keep first connecting hole corresponding with second connecting hole, then
It will quickly be covered on the output shaft after clamping sleeve heating, and be inserted into first plug, insert first cylindrical section
Enter first connecting hole, rotate the clamping sleeve later, the section for surveying benchmark angle described in torsion teeth directional is made to move to institute
It states clamping sleeve and is close to the kidney-shaped shell of column, after the clamping sleeve is cooling, pull up first plug,
Step B assembles the reference rings, provides second plug, and second plug includes the second cylindrical section and means,
The diameter of second cylindrical section is 0.01-0.02mm smaller than the diameter of the circular hole of the reference axis, second cylindrical section
Length be more than or equal to the latch length make institute by the benchmark ring set on the mounted clamping sleeve of step A
It states that the 4th connecting hole is corresponding with the third connecting hole, and is horizontally situated two opposite third connecting holes, it will
Second plug is inserted into the 4th connecting hole, and second cylindrical section is made to be inserted into first connecting hole bottom,
Then in the 4th connecting hole of the other end by latch assembly in place, remove second plug later, and
Corresponding position second latch assembly in place, is so far completed into the aero-engine power turbine torque measurement
The assembly of system.
2. a kind of the method as described in claim 1, which is characterized in that in stepb, in the process for assembling the latch
In, it will be first reloaded into after latch liquid nitrogen cooling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711126631.8A CN107932057B (en) | 2017-11-15 | 2017-11-15 | A kind of aero-engine power turbine torch measuring system assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711126631.8A CN107932057B (en) | 2017-11-15 | 2017-11-15 | A kind of aero-engine power turbine torch measuring system assembly method |
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| Publication Number | Publication Date |
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| CN107932057A CN107932057A (en) | 2018-04-20 |
| CN107932057B true CN107932057B (en) | 2019-05-24 |
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| CN201711126631.8A Active CN107932057B (en) | 2017-11-15 | 2017-11-15 | A kind of aero-engine power turbine torch measuring system assembly method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112008351B (en) * | 2020-07-10 | 2021-11-19 | 中国航发南方工业有限公司 | Torsion measuring ring assembling method and clamp |
| CN111982369B (en) * | 2020-07-27 | 2022-05-17 | 中国航发湖南动力机械研究所 | Output shaft torsion measuring method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202582802U (en) * | 2012-05-16 | 2012-12-05 | 郑州机械研究所 | Distortion transmission measurement device used for gear shaft extra large-range torque measurement |
| CN204479221U (en) * | 2015-01-09 | 2015-07-15 | 哈尔滨东安发动机（集团）有限公司 | Engine electricity instrument measuring torsional vibration |
| KR20150089799A (en) * | 2014-01-28 | 2015-08-05 | 주식회사 일진 | Device and method for processing ball joint |
| CN106481680A (en) * | 2016-12-13 | 2017-03-08 | 三汽车制造有限公司 | The mounting assembly of torque sensor |
| CN107246945A (en) * | 2017-05-19 | 2017-10-13 | 哈尔滨工程大学 | A kind of measuring system of dynamic twisting vibration transmission function |
-
2017
- 2017-11-15 CN CN201711126631.8A patent/CN107932057B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202582802U (en) * | 2012-05-16 | 2012-12-05 | 郑州机械研究所 | Distortion transmission measurement device used for gear shaft extra large-range torque measurement |
| KR20150089799A (en) * | 2014-01-28 | 2015-08-05 | 주식회사 일진 | Device and method for processing ball joint |
| CN204479221U (en) * | 2015-01-09 | 2015-07-15 | 哈尔滨东安发动机（集团）有限公司 | Engine electricity instrument measuring torsional vibration |
| CN106481680A (en) * | 2016-12-13 | 2017-03-08 | 三汽车制造有限公司 | The mounting assembly of torque sensor |
| CN107246945A (en) * | 2017-05-19 | 2017-10-13 | 哈尔滨工程大学 | A kind of measuring system of dynamic twisting vibration transmission function |
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| CN107932057A (en) | 2018-04-20 |
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