CN110216623A - A kind of engine turbine blade quick decomposing device and method - Google Patents
A kind of engine turbine blade quick decomposing device and method Download PDFInfo
- Publication number
- CN110216623A CN110216623A CN201910435718.6A CN201910435718A CN110216623A CN 110216623 A CN110216623 A CN 110216623A CN 201910435718 A CN201910435718 A CN 201910435718A CN 110216623 A CN110216623 A CN 110216623A
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- Prior art keywords
- annulus
- fast decoupled
- fixed
- blade
- engine turbine
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Links
- 238000000034 method Methods 0.000 title claims description 5
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 9
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 9
- -1 polytetrafluoroethylene Polymers 0.000 claims description 5
- 230000006378 damage Effects 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 3
- 208000037656 Respiratory Sounds Diseases 0.000 description 2
- 238000002679 ablation Methods 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005194 fractionation Methods 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000010079 rubber tapping Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/02—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
Abstract
The invention discloses a kind of engine turbine blade quick decomposing devices, including pedestal, fixed rack beam, fast decoupled annulus and fixed bracket foot prop, fixed rack beam is installed in rotation on pedestal, fast decoupled annulus is set in chassis outer side, and gap is equipped between fast decoupled annulus and pedestal；Fast decoupled annulus is connect with fixed rack beam by fixed bracket foot prop, the fast decoupled annulus lower surface is provided with annular groove, and the present invention realizes the quick dismounting of blade, while avoiding the damage tapped to blade.
Description
Technical field
The present invention relates to engine maintenance technical field more particularly to a kind of engine turbine blade quick decomposing devices.
Background technique
Aero-turbine component is mainly made of turbo blade and turbine rotor blade, and effect is to fire engine
The kinetic energy and thermal energy of gas are converted into the mechanical work of rotation, drive other attachmentes such as compressor, turbine rotor blade is as engine
Middle thermic load and the maximum component of living load, the failures such as ablation, crackle are also easy to produce in engine operation, need to inspect periodically whirlpool
The failures such as crackle, ablation, the abrasion of rotor blades.Lower turbine rotor blade need to be divided to carry out the inspection such as detect a flaw when Engine Overhaul
It looks into.
Since turbine rotor blade is mounted at the excircle of turbo blade, between adjacent two pieces turbine rotor blade between
Gap is very small, while the tongue-and-groove of turbine rotor blade listrium and turbo blade has 10 ° or so angle restrictions, therefore causes turbine
Rotor blade splits difficult.It mainly takes at present and gently taps turbine rotor blade tip with plastic hammer is radially interior, shake loose turbine and turn
Blades carbon distribution is transferred to a piece of turbine rotor blade with hand backward, is made between its listrium with adjacent turbine rotor blade
There is gap, a piece of turbine rotor blade (backsight, counterclockwise) is transferred to backward by under with hand.It successively dials in this order
Turbine rotor blade out is fully dialing out until by a piece of turbine rotor blade.Turbine rotor blade is dismantled after striking pine, is be easy to cause
Turbine rotor blade damage, and disassembly process is cumbersome, and removal efficiency is low.
Summary of the invention
To solve the above-mentioned problems, the present invention proposes a kind of engine turbine blade quick decomposing device, it include pedestal,
Fixed rack beam, fast decoupled annulus and fixed bracket foot prop, fixed rack beam are installed in rotation on pedestal, quickly
It decomposes annulus and is set in chassis outer side, and be equipped with gap between fast decoupled annulus and pedestal；It will be fast by fixed bracket foot prop
Speed is decomposed annulus and is connect with fixed rack beam, and the fast decoupled annulus is provided with annular groove.
The fast decoupled annulus is provided with circular hole, is provided with bracket fixing bolt on fixed bracket foot prop, bracket is fixed
Bolt passes through the circular hole, and fast decoupled annulus is fixed on fixed bracket foot prop by nut.
Rotating handle is provided on the fixation rack beam.
The diameter of the fast decoupled annulus is identical as the diameter of engine turbine vane end faces.
The fast decoupled annulus is made of polytetrafluoroethylene (PTFE).
The beneficial effects of the present invention are: (1) fast decoupled annulus of polytetrafluoroethylene (PTFE) be made, and tears open in turbine rotor blade
Timesharing, polytetrafluoroethylene material is softer, can avoid the damage of turbo blade.
(2) size of fast decoupled annulus is consistent with the size of engine turbine blade side surface, every on turbo blade
The listrium of turbine rotor blade can be installed in the annular groove of fast decoupled annulus, and such structure maintains turbine rotor leaf
The angle restriction in gap and turbo blade tongue-and-groove and turbine rotor blade between piece, plays the work of fixed turbine rotor blade
With, while the landing of turbine rotor blade can be prevented.
(3) this engine turbine rotor blade quick decomposing device, screwing power by fixed bracket will be on turbo blade
Turbo blade is integrally removed, and is to overcome between turbo blade tongue-and-groove and turbine rotor blade frictional force by turbine rotor blade from whirlpool
Integrally extracted in impeller blade tongue-and-groove, it is therefore prevented that it is previous tap blade split and caused by blade injury.
(4) by the utilization of fast decoupled annulus, the blade on turbo blade can integrally be removed, the efficiency of fractionation by
60min is improved to 2~5min, damage caused by avoiding turbo blade blade from tapping.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is the structural schematic diagram of fast decoupled annulus in the present invention；
Fig. 3 is the fractionation schematic diagram of turbine rotor in comparative example；
1- pedestal, 2- fast decoupled annulus, 3- bracket fixing bolt, the fixed bracket foot prop of 4- turbo blade A, 5-, 6- are solid in figure
Fixed rack crossbeam, 7- rotating handle, 8- circular hole, 9- annular groove, 10- turbo blade tongue-and-groove, 11- turbine rotor blade listrium, 12-
Turbo blade B.
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.
As shown in Figure 1, a kind of engine turbine rotor blade quick decomposing device, including pedestal 1, fast decoupled annulus 2,
Bracket fixing bolt 3, fixed bracket foot prop 5, fixed rack beam 6 and rotating handle 7 form.
As shown in Figure 1, 2, the pedestal 1 is penetrated from 2 inner hole of fast decoupled annulus and is rotatablely connected with rack beam 6, Gu
Rotating handle 7 is provided on fixed rack crossbeam 6；Fixed 5 one end of bracket foot prop is removably attachable on fixed rack beam 6,
The other end is connected with dismountable fast decoupled annulus 2.The size of fast decoupled annulus 2 and the ruler of engine turbine vane end faces
Very little consistent, fast decoupled annulus 2 is equipped with annular groove 9, and the listrium of every turbo blade A4 can be packed into annular groove 9 on turbo blade
It is interior.The fast decoupled annulus 2 is made of polytetrafluoroethylene (PTFE).
As shown in Figure 1, 2, it is opened on fast decoupled annulus 2 there are four the circular hole 8 of annular array distribution, fixed bracket foot prop 5
It is connected with bracket fixing bolt 3, bracket fixing bolt 3 passes through the circular hole 8, and by the nut of bolt by fast decoupled annulus
2 are fixed on fixed bracket foot prop 5, and fixed bracket foot prop 5 and fast decoupled annulus 2 is made to become a unified entirety.
When turbine rotor blade is split, fast decoupled annulus 2 is directed to the listrium of every turbo blade A4 on turbo blade,
By the bracket fixing bolt 3 in the annular groove 9 of the listrium insertion fast decoupled annulus 2 of turbo blade A4, on fixed bracket foot prop 5
Circular hole 8 on fast decoupled annulus 2, and fast decoupled annulus 2 is fixed with by nut.Fixed rack beam 6
Become a unified entirety with fast decoupled annulus 2 by fixed bracket foot prop 5, rotates rotating handle 7, pass through fixed bracket
Power is screwed integrally to remove the turbo blade A4 on turbo blade.
Comparative example:
As shown in figure 3, plastic hammer radially in gently tap turbine rotor blade tip, turbo blade B12 is shaken loose, with hand by a piece of whirlpool
Impeller blade B12 tenon is transferred to backward along turbo blade tongue-and-groove 10, makes turbine rotor blade listrium 11 and adjacent turbine rotor
There is gap between blade listrium 11, a piece of turbo blade B12(backsight under being incited somebody to action with hand, counterclockwise) transfer to backward.It presses
This sequence successively transfers to turbo blade B12, until that will be fully dialing out per a piece of turbo blade B12.
Claims (6)
1. a kind of engine turbine blade quick decomposing device, which is characterized in that including pedestal (1), fixed rack beam (6),
Fast decoupled annulus (2) and fixation bracket foot prop (5), fixed rack beam (6) are installed in rotation on pedestal (1), quickly
It decomposes annulus (2) to be set on the outside of pedestal (1), and is equipped with gap between fast decoupled annulus (2) and pedestal (1)；Pass through fixation
Fast decoupled annulus (2) is connect by bracket foot prop (5) with fixed rack beam (6), and the fast decoupled annulus (2) is provided with
Annular groove (9).
2. a kind of engine turbine blade quick decomposing device according to claim 1, which is characterized in that described is quick
It decomposes annulus (2) to be provided with circular hole (8), be provided with bracket fixing bolt (3) on fixed bracket foot prop (5), bracket fixing bolt (3)
Fast decoupled annulus (2) is fixed on fixed bracket foot prop (5) across the circular hole (8), and by nut.
3. a kind of engine turbine blade quick decomposing device according to claim 1, which is characterized in that the fixation
Rotating handle (7) are provided on rack beam (6).
4. a kind of engine turbine blade quick decomposing device according to claim 1, which is characterized in that described is quick
The diameter for decomposing annulus (2) is identical as the diameter of engine turbine vane end faces.
5. a kind of engine turbine blade quick decomposing device according to claim 1, which is characterized in that described is quick
Annulus (2) are decomposed to be made of polytetrafluoroethylene (PTFE).
6. a kind of application method of the engine turbine blade quick decomposing device of any one described in -6 according to claim 1,
Characterized by comprising the following steps:
S1: turbo blade is placed on fast decoupled annulus (2), and the listrium of turbo blade (4) is made to be inserted into fast decoupled annulus (2)
Annular groove (9) in；
S2: it is fixed by the bracket bolt (3) and fast decoupled annulus (2) is fixed on fixed bracket foot prop (5)；
S3: the rotating handle (7) of the device is rotated, and above mentions turbo blade；Power is screwed by fixed bracket, and turbo blade is whole
Body is removed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910435718.6A CN110216623B (en) | 2019-05-23 | 2019-05-23 | Quick decomposing device and method for turbine blade of engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910435718.6A CN110216623B (en) | 2019-05-23 | 2019-05-23 | Quick decomposing device and method for turbine blade of engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110216623A true CN110216623A (en) | 2019-09-10 |
| CN110216623B CN110216623B (en) | 2024-01-02 |
Family
ID=67817868
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910435718.6A Active CN110216623B (en) | 2019-05-23 | 2019-05-23 | Quick decomposing device and method for turbine blade of engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110216623B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114762968A (en) * | 2021-01-14 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Blade retaining ring installation tool and blade retaining ring installation method |
| CN115213850A (en) * | 2021-04-15 | 2022-10-21 | 中国航发商用航空发动机有限责任公司 | Method for disassembling adjustment pad |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5390404A (en) * | 1991-07-29 | 1995-02-21 | Sensible Products, Inc. | Pulling tool |
| CN205085907U (en) * | 2015-10-30 | 2016-03-16 | 登电集团新玉煤矿 | Special dismounting device of motor fan blade |
| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
| CN108098673A (en) * | 2017-12-11 | 2018-06-01 | 中国航发沈阳发动机研究所 | Low-pressure turbine blade baffle assembling and disassembling device |
| CN208196671U (en) * | 2018-04-13 | 2018-12-07 | 宋亚斌 | It is a kind of quickly to remove draft gage |
| CN109676562A (en) * | 2018-12-19 | 2019-04-26 | 中国航发沈阳发动机研究所 | A kind of aero-engine low-pressure turbine guide vane mounting device |
-
2019
- 2019-05-23 CN CN201910435718.6A patent/CN110216623B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5390404A (en) * | 1991-07-29 | 1995-02-21 | Sensible Products, Inc. | Pulling tool |
| CN205085907U (en) * | 2015-10-30 | 2016-03-16 | 登电集团新玉煤矿 | Special dismounting device of motor fan blade |
| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
| CN108098673A (en) * | 2017-12-11 | 2018-06-01 | 中国航发沈阳发动机研究所 | Low-pressure turbine blade baffle assembling and disassembling device |
| CN208196671U (en) * | 2018-04-13 | 2018-12-07 | 宋亚斌 | It is a kind of quickly to remove draft gage |
| CN109676562A (en) * | 2018-12-19 | 2019-04-26 | 中国航发沈阳发动机研究所 | A kind of aero-engine low-pressure turbine guide vane mounting device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114762968A (en) * | 2021-01-14 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Blade retaining ring installation tool and blade retaining ring installation method |
| CN115213850A (en) * | 2021-04-15 | 2022-10-21 | 中国航发商用航空发动机有限责任公司 | Method for disassembling adjustment pad |
| CN115213850B (en) * | 2021-04-15 | 2023-08-11 | 中国航发商用航空发动机有限责任公司 | Decomposing method for adjusting pad |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110216623B (en) | 2024-01-02 |
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