CN108318182A - Multistage Low Pressure Turbine Rotor subassembly is without tooling balance method - Google Patents
Multistage Low Pressure Turbine Rotor subassembly is without tooling balance method Download PDFInfo
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- CN108318182A CN108318182A CN201711452433.0A CN201711452433A CN108318182A CN 108318182 A CN108318182 A CN 108318182A CN 201711452433 A CN201711452433 A CN 201711452433A CN 108318182 A CN108318182 A CN 108318182A
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- Prior art keywords
- pressure turbine
- low
- balance
- assembly
- tooling
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/30—Compensating unbalance
- G01M1/32—Compensating unbalance by adding material to the body to be tested, e.g. by correcting-weights
Abstract
Subassembly balance methods at different levels in a kind of multistage Low Pressure Turbine Rotor system of present invention offer, the balance method does not use special balancing tooling, but based on low-pressure turbine shaft assembly (1), first low-pressure turbine shaft assembly is balanced, its assembly relation is pressed later, assembling second level low pressure disc combination part (2), third level low pressure disc combination part (3) and first order low pressure disc combination part (4) step by step, and be balanced step by step.
Description
Technical field
The invention belongs to aero-engine, gas turbine manufacturing fields, are related to multistage Low Pressure Turbine Rotor subassembly without work
Fill balance method
Background technology
For aero-engine multistage Low Pressure Turbine Rotor internal system low-pressure turbine disc combination part at different levels and low pressure whirlpool
Shaft balancing is taken turns, the common balance method in home and abroad is processing special balancing tooling at present, then relies on special balancing tooling complete
Multistage each component of Low Pressure Turbine Rotor internal system is balanced in pairs.It is final to each component in rotor-support-foundation system inside to reduce tooling
The influence of unbalance residual content, it is desirable that tooling and be balanced component and have higher cooperation precision, centering precision and balance quality；Or
Person rejects the unbalance residual content of tooling using indexable balancing method.
High-precision tooling difficulty of processing is big, and the process-cycle is longer, and cost is high.Indexing balance is compensation tooling error
Effective ways, although tooling processing spend it is less, the process-cycle is also shorter, balance when need being dismounted for multiple times rotor assembly and
Tooling, balance spend the time longer；When rotor assembly and tooling are interference fit, it is likely that hot charging, hot charging workpiece is needed to need
Just allow to be balanced after being cooled to room temperature, the time for balancing cost is again longer.
Invention content
Goal of the invention
To solve the above problems, having invented a kind of multistage Low Pressure Turbine Rotor subassembly without tooling balance method, purpose
It is not have to special balancing tooling, with minimum cost, most fast speed to multistage Low Pressure Turbine Rotor and its low-pressure turbine at different levels
Disc combination part reaches the balance quality of requirement into action balance.
Technical solution
Advantageous effect
The present invention can save tooling input cost, for N grades of turbine rotor systems, it is possible to reduce N set balance works
The input of dress；Balance method without special balancing tooling can save tooling process-cycle and corresponding human input；In addition,
Using the real work support of rotor as the support of balance, is really coordinated with each inter-module and coordinated instead of tool component, eliminated
Influence that tooling residual unbalance, balances spare part eliminates balance tooling and balanced component coaxiality deviation to balance
Influence, eliminate balance tooling and influence of the fit clearance to balance that is balanced component.
Description of the drawings
Wherein：
Fig. 1 low-pressure turbine shaft assemblies；
The second level Fig. 2 low-pressure turbine disc combination part balance；
Fig. 3 third level low-pressure turbine disc combination parts balance；
Fig. 4 first order low-pressure turbine disc combination parts balance.
Specific implementation mode
The specific embodiment of the invention is described below in detail
A) step 1：The assembly to low-pressure turbine shaft assembly (1) is completed, and with Low Pressure Turbine Rotor system actual support
Face makes its satisfaction itself put down low-pressure turbine shaft assembly (1) on the qualified balancing machine of calibration as support into action balance
Weighing apparatus required precision；When actual support surface is blocked by spare part, permission is less than in rotor-support-foundation system with actual support surface concentricity
The cylindrical surface of 0.005mm replaces supporting surface to support rotor-support-foundation system；It marks and the remnants for recording low-pressure turbine shaft assembly (1) is uneven
Measurement and direction.
B) step 2：The mode of material is easily extractd with addition, the residue for further adjusting low-pressure turbine shaft assembly is uneven
It weighs, reaching tooling balance quality, (usually when balancing speed is not less than 800rpm, unbalance residual content is not more than
0.5gcm) require；
C) step 3：Complete the assembly of low-pressure turbine shaft assembly (1) and second level low-pressure turbine disc combination part (2)；
If two sub-assemblies are to be bolted, bolt and nut pairing is weighed, it is little that difference organizes other bolt and nut weight difference
In 0.05g, difference is organized other bolt and nut and is circumferentially arranged, is distributed using the principle of minimum amount of unbalance；Nut is tightened
Sequence meets crossing method, and screw-down torque meets the requirement of the files such as HB6125, and the screw-down torque of each bolt is consistent.Assembly
After the completion, it is support to low-pressure turbine shaft assembly (1) and second level low-pressure turbine disc combination part (2) with the supporting surface in a)
Component after assembly makes its residual unbalance, meet design requirement into action balance；It marks and records second level low-pressure turbine
The unbalance residual content of disc combination part (2) and direction.
D) step 4：Material is easily extractd with addition, removal, part remove or mobile original easy mode for extracing material,
The residue of component after further adjustment low-pressure turbine shaft assembly (1) and second level low-pressure turbine disc combination part (2) assemble
Amount of unbalance reaches tooling balance quality requirement；
E) step 5：Complete the assembly to component in third level low-pressure turbine disc combination part (3) and step 4；If third
Grade low-pressure turbine disc combination part (3) and step 4 component are to be bolted, then bolt and nut pairing are weighed, different groups
Other bolt and nut weight difference is not more than 0.05g, and difference is organized other bolt and nut and is circumferentially arranged, using the original of minimum amount of unbalance
Then it is distributed；The sequence of tightening of nut meets crossing method, and screw-down torque meets the requirement of the files such as HB6125, and each spiral shell
The screw-down torque of bolt is consistent.To low-pressure turbine shaft assembly (1), second level low-pressure turbine disc combination part (2) after the completion of assembly
And the component after third level low-pressure turbine disc combination part (3) assembly makes its residual unbalance, meet design into action balance
It is required that；Mark and record unbalance residual content and the direction of third level low-pressure turbine disc combination part (3).
F) step 6：Material is easily extractd with addition, removal, part remove or mobile original easy mode for extracing material,
Further adjustment low-pressure turbine shaft assembly (1), second level low-pressure turbine disc combination part (2) and third level low-pressure turbine disc
The residual unbalance, of component after sub-assembly (3) assembly, reaches tooling balance quality requirement；
G) step 7：Complete the assembly to first order low-pressure turbine disc combination part (4)；If first order low-pressure turbine disc
Sub-assembly (4) and assembling assembly are to be bolted, then bolt and nut pairing are weighed, difference organizes other bolt and nut weight
Amount difference is not more than 0.05g, and difference is organized other bolt and nut and is circumferentially arranged, is distributed using the principle of minimum amount of unbalance；Spiral shell
Female sequence of tightening meets crossing method, and screw-down torque meets the requirement of the files such as HB6125, and the screw-down torque of each bolt
Unanimously.To low-pressure turbine shaft assembly (1), second level low-pressure turbine disc combination part (2), third level low-pressure turbine disk after assembly
Component makes its residual unbalance, into action balance after chip assembly (3) and first order low-pressure turbine disc combination part (4) assembly
Meet design requirement；Record the size and Orientation of unbalance residual content.
H) step 8：Sub-assembly balancing works at different levels are completed, and extract all easy excision materials on component, and by final component
Decompose to low-pressure turbine shaft assembly (1), first order low-pressure turbine disc combination part (4), second level low-pressure turbine disc combination
Part (2), third level low-pressure turbine disc combination part (3).
If also N grades needs to balance, after step 5, press Step 4: the method for step 5 repeats n times, to N grades remaining
Disc combination part is balanced.
A kind of specific embodiment of the present invention is as follows：
A) its residual unbalance, is made to meet design requirement into action balance low-pressure turbine shaft assembly (Fig. 1)；
B) using the method for easily extracing material (such as plasticine) is pasted, the residue of adjustment low-pressure turbine shaft assembly is uneven
Amount, reaches balance tooling required precision；
C) as shown in Fig. 2, completing the assembly of low-pressure turbine shaft assembly and second level low-pressure turbine disc combination part, and it is right
It makes its residual unbalance, meet design requirement into action balance, and records the size and Orientation of unbalance residual content；
D) using the method for patch plasticine, low-pressure turbine shaft assembly+second level low-pressure turbine disc combination part is adjusted
Residual unbalance, reaches balance tooling required precision；
E) as shown in figure 3, completing the assembly to third level low-pressure turbine disc combination part, and it is made into action balance
Its residual unbalance, meets design requirement, and records the size and Orientation of unbalance residual content；
It f), will be by low-pressure turbine shaft assembly, second level low-pressure turbine disc combination part, the using the method for patch plasticine
The residual unbalance, for the component that three-level low-pressure turbine disc combination part is constituted is adjusted to balance tooling required precision；
G) as shown in figure 4, completing the assembly to first order low-pressure turbine disc combination part, and it is made into action balance
Its residual unbalance, meets design requirement, records the size and Orientation of unbalance residual content；
……
It h) can be according to said method step by step to fourth stage low-pressure turbine disc combination part, level V low-pressure turbine disc combination
Part ... (if having) is into action balance.
I) balance is completed, and removes plasticine, and by multistage Low Pressure Turbine Rotor system decomposition to disc combination part, low pressure whirlpool
Wheel shaft sub-assembly state.
Claims (5)
1. multistage Low Pressure Turbine Rotor subassembly is without tooling balance method, which is characterized in that special balancing tooling is not used, but
Based on low-pressure turbine shaft assembly (1), first low-pressure turbine shaft assembly is balanced, assembles the turbine disks at different levels step by step later
Chip assembly and step by step into action balance.
2. multistage Low Pressure Turbine Rotor subassembly according to claim 1 is without tooling balance method, which is characterized in that assembly
Before next stage turbine disk chip assembly, the component balance quality that upper level assembly is completed is adjusted to meeting tooling balance quality and is wanted
It asks in range.
3. according to the multistage Low Pressure Turbine Rotor subassembly described in claim 2 without tooling balance method, which is characterized in that specific packet
Include following steps：
Step 1, to low-pressure turbine shaft assembly (1) into action balance, so that it is met balance quality requirement itself；
Step 2, the mode that material is easily extractd with addition, further adjust the residual unbalance, of low-pressure turbine shaft assembly, make
It reaches tooling balance quality requirement；
Step 3, the assembly for completing low-pressure turbine shaft assembly (1) and second level low-pressure turbine disc combination part (2), and to low pressure
Component after turbine shaft assembly (1) and second level low-pressure turbine disc combination part (2) assembly keeps it remaining not into action balance
Aequum meets design requirement；
Step 4, the mode that material is easily extractd with addition, further adjust low-pressure turbine shaft assembly (1) and second level low pressure whirlpool
The residual unbalance, of component after wheel disc chip assembly (2) assembly, reaches tooling balance quality requirement；
Step 5 completes assembly to third level low-pressure turbine disc combination part (3), and to low-pressure turbine shaft assembly (1), the
Component after two level low-pressure turbine disc combination part (2) and third level low-pressure turbine disc combination part (3) assembly into action balance,
Its residual unbalance, is set to meet design requirement；
Step 6, the mode that material is easily extractd with addition, further adjust low-pressure turbine shaft assembly (1), second level low-pressure turbine
The residual unbalance, of component after disc combination part (2) and third level low-pressure turbine disc combination part (3) assembly, reaches
The requirement of tooling balance quality；
Step 7 completes assembly to first order low-pressure turbine disc combination part (4), and to low-pressure turbine shaft assembly (1), the
Two level low-pressure turbine disc combination part (2), third level low-pressure turbine disc combination part (3) and first order low-pressure turbine disc combination
Part (4) assembles laggard action balance, its residual unbalance, is made to meet design requirement.
4. according to the multistage Low Pressure Turbine Rotor subassembly described in claim 3 without tooling balance method, which is characterized in that further include
Step 8：Extract all easy excision materials.
5. according to the multistage Low Pressure Turbine Rotor subassembly described in claim 3 without tooling balance method, which is characterized in that if also having
N grades of low-pressure turbine disc combination parts need to balance, then after step 5, n times are repeated by step 4, the method for step 5, to remainder
N grades of disc combination parts are balanced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711452433.0A CN108318182A (en) | 2017-12-27 | 2017-12-27 | Multistage Low Pressure Turbine Rotor subassembly is without tooling balance method |
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| CN201711452433.0A CN108318182A (en) | 2017-12-27 | 2017-12-27 | Multistage Low Pressure Turbine Rotor subassembly is without tooling balance method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109356662A (en) * | 2018-11-27 | 2019-02-19 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of process of aero-engine Low Pressure Turbine Rotor assembly |
| CN113092123A (en) * | 2021-03-25 | 2021-07-09 | 中国航发南方工业有限公司 | Method for assembling a rotor of a gas generator |
| CN115541116A (en) * | 2022-11-24 | 2022-12-30 | 中国航发沈阳发动机研究所 | Control method for reducing rotation inertia excitation of turbine rotor |
| CN115628850A (en) * | 2022-12-22 | 2023-01-20 | 中国航发沈阳发动机研究所 | Rotor balancing process method |
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| CN1587944A (en) * | 2004-08-03 | 2005-03-02 | 河南科技大学 | Multiple shaft multiple rotor dynamic balancing test method |
| CN103452914A (en) * | 2013-08-05 | 2013-12-18 | 天津机辆轨道交通装备有限责任公司 | Assembly technique for reducing dynamic balance of rotor of turbocharger |
| CN103595202A (en) * | 2013-11-19 | 2014-02-19 | 江苏航天动力机电有限公司 | Motor rotor dynamic balancing verifying method |
| US20150047191A1 (en) * | 2013-08-19 | 2015-02-19 | Rolls-Royce Deutschland Ltd & Co Kg | Method for balancing and assembling a turbine rotor |
| CN105397465A (en) * | 2015-12-08 | 2016-03-16 | 四川成发航空科技股份有限公司 | Assembly device for engine turbine |
| CN106625398A (en) * | 2017-01-03 | 2017-05-10 | 哈尔滨工业大学 | Assembling method and device of aero-engine rotor |
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Patent Citations (6)
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| CN1587944A (en) * | 2004-08-03 | 2005-03-02 | 河南科技大学 | Multiple shaft multiple rotor dynamic balancing test method |
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| US20150047191A1 (en) * | 2013-08-19 | 2015-02-19 | Rolls-Royce Deutschland Ltd & Co Kg | Method for balancing and assembling a turbine rotor |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109356662A (en) * | 2018-11-27 | 2019-02-19 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of process of aero-engine Low Pressure Turbine Rotor assembly |
| CN109356662B (en) * | 2018-11-27 | 2021-06-18 | 中国航发沈阳黎明航空发动机有限责任公司 | Process method for assembling low-pressure turbine rotor of aircraft engine |
| CN113092123A (en) * | 2021-03-25 | 2021-07-09 | 中国航发南方工业有限公司 | Method for assembling a rotor of a gas generator |
| CN113092123B (en) * | 2021-03-25 | 2024-01-23 | 中国航发南方工业有限公司 | Method for assembling a gas generator rotor |
| CN115541116A (en) * | 2022-11-24 | 2022-12-30 | 中国航发沈阳发动机研究所 | Control method for reducing rotation inertia excitation of turbine rotor |
| CN115541116B (en) * | 2022-11-24 | 2023-10-10 | 中国航发沈阳发动机研究所 | Control method for reducing rotation inertia excitation of turbine rotor |
| CN115628850A (en) * | 2022-12-22 | 2023-01-20 | 中国航发沈阳发动机研究所 | Rotor balancing process method |
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Application publication date: 20180724 |