CN110434625A - A kind of method and device for blade surplus centering long-pending folded axle when uneven - Google Patents
A kind of method and device for blade surplus centering long-pending folded axle when uneven Download PDFInfo
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- CN110434625A CN110434625A CN201910626544.1A CN201910626544A CN110434625A CN 110434625 A CN110434625 A CN 110434625A CN 201910626544 A CN201910626544 A CN 201910626544A CN 110434625 A CN110434625 A CN 110434625A
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- blade
- spring contact
- compression spring
- uneven
- turbo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
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- Mechanical Engineering (AREA)
- Nonmetal Cutting Devices (AREA)
Abstract
The invention discloses a kind of method and devices for blade surplus centering long-pending folded axle when uneven, principle is automatically positioned by precision apparatus blade type face mechanics, find out the practical long-pending folded axle in each section of blade, solve blade blade surplus it is uneven when, the problem of how blade type face being adjusted to most reasonable position, so that the practical long-pending folded axle in each section of blade is overlapped with the center line of precision apparatus, can it is most economical most effectively reduce tenon processing after blade with respect to tenon benchmark error, to improve cast blade utilization rate and cost performance.
Description
Technical field
The invention belongs to turbo blade technical fields, and in particular to centering long-pending folded axle when one kind is uneven for blade surplus
Method and device.
Background technique
Blade Aeronautics and Astronautics, navigation and in terms of be widely used, and play highly important work
With.Especially in terms of aviation, blade is the core part of engine, and engine is the heart of aircraft.The manufacturing quality of blade
Directly affect the service performance of engine and the flight safety of service life or even aircraft.In addition, quantity is huge within the engine for blade
It greatly and is most important and complicated part.
High-precision space coordinate measurement be not only to judge blade whether He Ge foundation, during more becoming blade processing
One important link of quality control.How quickly and accurately to detect blade geometry precision and guarantees that processing quality becomes one
The problem of urgent need to resolve.
In aviation field, without surplus turbo blade, guide vane, the technique being usually machined is using leaf for hot investment casting
The precision positioning of body positioning process tenon, blade type face is very important, and blade is with respect to tenon after tenon is processed in the prior art
There are large error, cast blade utilization rate and cost performance are all affected head benchmark.
Summary of the invention
It is an object of the invention to: a kind of method and device for blade surplus centering long-pending folded axle when uneven is provided,
Blade is adjusted to the precision positioning of optimum position, effectively reduce tenon processing after blade with respect to tenon benchmark error, thus
Improve cast blade utilization rate and cost performance.
The technical solution adopted by the invention is as follows:
A kind of device for blade surplus centering long-pending folded axle when uneven, including it is internal equipped with for placing turbo blade
Cavity precision apparatus ontology, precision apparatus ontology is provided with the first locating bar for attachment of turbine blades blade tip, is used for
The second locating bar of attachment of turbine blades blade root and third locating bar for attachment of turbine blades blade, precision apparatus ontology
It is provided with eight compression spring contacts for pushing against turbo blade.
Further, compression spring contact includes the first pressure spring contact for being located at turbo blade leaf basin side, the second pressure
Power spring contact, third compression spring contact, the 4th compression spring contact and the 5th pressure positioned at turbo blade blade back side
Spring contact, the 6th compression spring contact, the 7th compression spring contact and the 8th compression spring contact.
Further, first pressure spring contact, third compression spring contact, the 6th compression spring contact and the 8th pressure
Spring contact is located at turbo blade blade tip direction, the second pressure spring contact, the 4th compression spring contact, the 5th pressure bullet
Spring contact and the 7th compression spring contact are located at turbo blade blade root direction.
Further, compression spring contact includes telescopic contact members and the spring part that is set in the contact members.
Further, contact members are connected with displacement sensor.
Using above-mentioned apparatus centering long-pending folded axle and the method that adjusts blade type face, comprising the following steps:
S1. turbo blade is put into precision apparatus ontology；
S2. it is automatically positioned principle using blade type face mechanics, it is real to find out each section of turbo blade blade by precision apparatus
Border long-pending folded axle；
It is overlapped the center line of precision apparatus with the practical long-pending folded axle of turbo blade blade, and turbo blade is fixed.
Blade is analyzed with respect to the location error of tenon coordinate system, offset, deflection, partial twist can be attributed to；The offset of blade,
Skewed error is all eliminated, and partial twist error is shared equally, i.e., blade takes in optimal adjustment position.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
1, solved in the present invention blade blade surplus it is uneven when, how blade type face is adjusted to most reasonable position
The problem of, it finds out the practical long-pending folded axle in each section of turbo blade blade and makes the practical long-pending folded axle and precision apparatus in each section of blade
Center line be overlapped；
2, the present invention can cost-effectively reduce tenon processing after blade with respect to tenon benchmark error, to improve casting
Make blade utilization rate and cost performance；
3, the present invention makes turbo blade skewed error using blade type face mechanics automatic positioning principle in clamping process
It all eliminates, partial twist error is shared equally, i.e., blade takes in optimal adjustment position.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below will be to needed in the embodiment attached
Figure is briefly described, it should be understood that the following drawings illustrates only certain embodiments of the present invention, therefore is not construed as pair
The restriction of range for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 is the top view of the device of the invention；
Fig. 2 is the bottom view of the device of the invention；
Fig. 3 is the structural schematic diagram of turbo blade；
Marked in the figure: 1- turbo blade, 2- precision apparatus ontology, 11- first pressure spring contact, 12- second pressure bullet
Spring contact, 13- third compression spring contact, the 4th compression spring contact of 14-, the 5th compression spring contact of 21-, 22- the 6th are pressed
Power spring contact, the 7th compression spring contact of 23-, the 8th compression spring contact of 24-.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that described herein, specific examples are only used to explain the present invention, not
For limiting the present invention, i.e., described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is logical
The component for the embodiment of the present invention being often described and illustrated herein in the accompanying drawings can be arranged and be designed with a variety of different configurations.
Therefore, the detailed description of the embodiment of the present invention provided in the accompanying drawings is not intended to limit below claimed
The scope of the present invention, but be merely representative of selected embodiment of the invention.Based on the embodiment of the present invention, those skilled in the art
Member's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
It should be noted that the relational terms of term " first " and " second " or the like be used merely to an entity or
Operation is distinguished with another entity or operation, and without necessarily requiring or implying between these entities or operation, there are any
This actual relationship or sequence.Moreover, the terms "include", "comprise" or its any other variant be intended to it is non-exclusive
Property include so that include a series of elements process, method, article or equipment not only include those elements, but also
Further include other elements that are not explicitly listed, or further include for this process, method, article or equipment it is intrinsic
Element.In the absence of more restrictions, the element limited by sentence "including a ...", it is not excluded that including described
There is also other identical elements in the process, method, article or equipment of element.
Feature and performance of the invention are described in further detail with reference to embodiments.
Embodiment
A kind of device for blade surplus centering long-pending folded axle when uneven that present pre-ferred embodiments provide, including it is interior
Portion is equipped with the precision apparatus ontology 2 for placing the cavity of turbo blade 1, and precision apparatus ontology 2 is provided with for fixed turbine
First locating bar 3 of 1 blade tip of blade, for 1 blade root of attachment of turbine blades the second locating bar 4 and be used for attachment of turbine blades
The third locating bar 5 of 1 blade, precision apparatus ontology 2 are provided with eight compression spring contacts for pushing against turbo blade 1.
Wherein, compression spring contact includes the first pressure spring contact 11 for being located at 1 leaf basin side of turbo blade, second pressure
Spring contact 12, third compression spring contact 13, the 4th compression spring contact 14 and positioned at the 5th of 1 blade back side of turbo blade
Compression spring contact 21, the 6th compression spring contact 22, the 7th compression spring contact 23 and the 8th compression spring contact 24；First
Compression spring contact 11, third compression spring contact 13, the 6th compression spring contact 22 and the 8th compression spring contact 24 are located at
1 blade tip direction of turbo blade, second pressure spring contact 12, the 4th compression spring contact 14,21 and of the 5th compression spring contact
7th compression spring contact 23 is located at 1 blade root direction of turbo blade.
Wherein, compression spring contact includes telescopic contact members and the spring part that is set in the contact members；Contact
Part is connected with displacement sensor；Displacement sensor sends data to computer, it is known that whether the state of adjustment rear blade surpasses
Difference, to determine whether the blade can continue to process.
Using above-mentioned apparatus centering long-pending folded axle and the method that adjusts blade type face, comprising the following steps:
S1. turbo blade is put into precision apparatus ontology；
S2. it is automatically positioned principle using blade type face mechanics, it is real to find out each section of turbo blade blade by precision apparatus
Border long-pending folded axle；
It is overlapped the center line of precision apparatus with the practical long-pending folded axle of turbo blade blade, and turbo blade is fixed.
Wherein, be automatically positioned principle according to blade type face mechanics, it is as follows to carry out concrete operations: analysis blade is sat with respect to tenon
The location error for marking system, can be attributed to offset, deflection, partial twist.
In the six-freedom degree of turbo blade blade positioning, first distinguish in blade blade tip section, blade root section leading edge
The first locating bar 3 and the second locating bar 4 are fixed, an anchor point, the positioning as axial direction (Z axis) are set on blade listrium
Point, it is fixed using third locating bar 5；Totally three fixed anchor points, elimination three degree of freedom there remains a movement above,
Two rotational freedoms, for adjusting offset, the deflection, partial twist error of blade.The adjustment of blade is set to be reduced to adjustment three in this way
A freedom degree.
Offset, the deflection, partial twist error of blade are automatically adjusted using mechanics positioning mode, the principle is as follows:
As shown in Figure 1 and Figure 2, first pressure spring contact 11, second pressure spring contact 12, third compression spring contact
13, the 4th compression spring contact 14, the 5th compression spring contact 21, the 6th compression spring contact 22, the 7th compression spring contact
23 and the 8th compression spring contact 24 respectively correspond eight anchor points of A, B, C, D, E, F, G, H on turbo blade 1.
When eight contacts are in theoretical position, they are consistent the pressure of the standard turbo blade 1 of not error, when
When not having the standard turbo blade 1 of error to be placed into 2 ontology of precision apparatus, the standard turbo blade 1 of error is not at three
Under stationary positioned and the collective effect of eight compression spring contacts, reach standing balance, makes the long-pending folded axle and pallet of blade
Center line be overlapped.
When there is the turbo blade 1 of error to be placed into precision apparatus ontology 2, if blade is deviated to leaf basin, then acting on
Because of compressed spring, it is big to be compared to be used in four, blade back direction power for four power on leaf basin, certainly will push automatically blade to blade back,
The resultant force on leaf basin is shifted onto equal to the resultant force on blade back, is overlapped the central plane of power and the central plane of blade stacking axis, it is complete
It totally disappeared except offset error.
Similarly, if blade tip section is to leaf basin deflection, the stress of two anchor point of A, B is greater than E, F, to push blade tip extremely
A+B=E+F completely eliminates the error of deflection.
Similarly, if blade tip is vented Bian Xiangye basin direction partial twist, i.e. A > E, F > B generate a torque M, force C=
The original balance of G, D=H, which are destroyed, will generate countertorque N and M balance.
Last blade reaches standing balance under the space force system collective effect that three stationary positioneds, eight power form, and makes X
The resultant force in direction is zero, and the resultant force of Y-direction is zero, equalising torque, and the offset of blade, skewed error are all eliminated, partial twist error
It shares equally, i.e., blade takes in optimal adjustment position.
Therefore, the device of the invention equally makes blade surplus uniform in the blade having a margin, the optimum state that error is shared equally.
Above-mentioned adjustment is completed at the same time in clamping process.Whole system precision and stability control 0.02mm with
It is interior.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (6)
1. a kind of device for blade surplus centering long-pending folded axle when uneven, it is characterised in that: be equipped with including inside for putting
The precision apparatus ontology (2) of the cavity of turbo blade (1) is set, the precision apparatus ontology (2) is provided with for fixed turbine leaf
First locating bar (3) of piece (1) blade tip, for attachment of turbine blades (1) blade root the second locating bar (4) and for fixing whirlpool
The third locating bar (5) of impeller blade (1) blade, the precision apparatus ontology (2) are provided with eight for pushing against turbo blade (1)
A compression spring contact.
2. the device according to claim 1 for blade surplus centering long-pending folded axle when uneven, it is characterised in that: described
Compression spring contact includes first pressure spring contact (11), the second pressure spring contact positioned at turbo blade (1) leaf basin side
(12), third compression spring contact (13), the 4th compression spring contact (14) and be located at turbo blade (1) blade back side the 5th
Compression spring contact (21), the 6th compression spring contact (22), the 7th compression spring contact (23) and the 8th compression spring contact
(24)。
3. the device according to claim 2 for blade surplus centering long-pending folded axle when uneven, it is characterised in that: described
First pressure spring contact (11), third compression spring contact (13), the 6th compression spring contact (22) and the 8th compression spring
Contact (24) is located at turbo blade (1) blade tip direction, the second pressure spring contact (12), the 4th compression spring contact
(14), the 5th compression spring contact (21) and the 7th compression spring contact (23) are located at turbo blade (1) blade root direction.
4. the device according to claim 1 for blade surplus centering long-pending folded axle when uneven, it is characterised in that: described
Compression spring contact includes telescopic contact members and the spring part that is set in the contact members.
5. the device according to claim 4 for blade surplus centering long-pending folded axle when uneven, it is characterised in that: described
Contact members are connected with displacement sensor.
6. the method for using device centering long-pending folded axle of any of claims 1-5 and adjusting blade type face, feature
It is, comprising the following steps:
S1. turbo blade is put into precision apparatus ontology；
S2. it is automatically positioned principle using blade type face mechanics, the practical product in each section of turbo blade blade is found out by precision apparatus
Folded axis；
It is overlapped the center line of precision apparatus with the practical long-pending folded axle of turbo blade blade, and turbo blade is fixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910626544.1A CN110434625A (en) | 2019-07-11 | 2019-07-11 | A kind of method and device for blade surplus centering long-pending folded axle when uneven |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910626544.1A CN110434625A (en) | 2019-07-11 | 2019-07-11 | A kind of method and device for blade surplus centering long-pending folded axle when uneven |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110434625A true CN110434625A (en) | 2019-11-12 |
Family
ID=68430260
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910626544.1A Pending CN110434625A (en) | 2019-07-11 | 2019-07-11 | A kind of method and device for blade surplus centering long-pending folded axle when uneven |
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| Country | Link |
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| CN (1) | CN110434625A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112405350A (en) * | 2020-11-04 | 2021-02-26 | 中国航发南方工业有限公司 | Offline positioning and reference correcting device for blade with shaft neck |
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| US4033569A (en) * | 1976-10-15 | 1977-07-05 | Dunn Garf L | Deformation-preventing workpiece-holding fixture for machine tools |
| CN86107876A (en) * | 1986-11-19 | 1988-06-01 | 航空工业部第六二五研究所 | The mechanical automatic positioning method of blade profile and device |
| DE3932571C1 (en) * | 1989-09-29 | 1991-03-28 | Mtu Muenchen Gmbh | |
| DE10026829C2 (en) * | 2000-05-30 | 2003-02-20 | Arthur Prib | Device for clamping a workpiece with an uneven surface |
| CN102357813A (en) * | 2011-09-09 | 2012-02-22 | 山东大学 | Fixture for processing and detecting blade of aircraft engine |
| CN103111877A (en) * | 2012-12-28 | 2013-05-22 | 北京航鹤童科技有限公司 | Stacking shaft positioning method and device of vane molded surface |
| CN106500637A (en) * | 2016-10-11 | 2017-03-15 | 中国航空工业集团公司北京航空精密机械研究所 | A kind of device calibrated by engine blade measurement apparatus |
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2019
- 2019-07-11 CN CN201910626544.1A patent/CN110434625A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4033569A (en) * | 1976-10-15 | 1977-07-05 | Dunn Garf L | Deformation-preventing workpiece-holding fixture for machine tools |
| CN86107876A (en) * | 1986-11-19 | 1988-06-01 | 航空工业部第六二五研究所 | The mechanical automatic positioning method of blade profile and device |
| DE3932571C1 (en) * | 1989-09-29 | 1991-03-28 | Mtu Muenchen Gmbh | |
| DE10026829C2 (en) * | 2000-05-30 | 2003-02-20 | Arthur Prib | Device for clamping a workpiece with an uneven surface |
| CN102357813A (en) * | 2011-09-09 | 2012-02-22 | 山东大学 | Fixture for processing and detecting blade of aircraft engine |
| CN103111877A (en) * | 2012-12-28 | 2013-05-22 | 北京航鹤童科技有限公司 | Stacking shaft positioning method and device of vane molded surface |
| CN106500637A (en) * | 2016-10-11 | 2017-03-15 | 中国航空工业集团公司北京航空精密机械研究所 | A kind of device calibrated by engine blade measurement apparatus |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112405350A (en) * | 2020-11-04 | 2021-02-26 | 中国航发南方工业有限公司 | Offline positioning and reference correcting device for blade with shaft neck |
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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Application publication date: 20191112 |