CN110216623B - Quick decomposing device and method for turbine blade of engine - Google Patents
Quick decomposing device and method for turbine blade of engine Download PDFInfo
- Publication number
- CN110216623B CN110216623B CN201910435718.6A CN201910435718A CN110216623B CN 110216623 B CN110216623 B CN 110216623B CN 201910435718 A CN201910435718 A CN 201910435718A CN 110216623 B CN110216623 B CN 110216623B
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- Prior art keywords
- quick
- ring
- fixed support
- decomposing
- turbine blade
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Links
- 238000000034 method Methods 0.000 title claims description 5
- 238000000354 decomposition reaction Methods 0.000 claims description 15
- -1 polytetrafluoroethylene Polymers 0.000 claims description 5
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 5
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 5
- 238000002679 ablation Methods 0.000 description 2
- 230000000052 comparative effect Effects 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
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002737 fuel gas Substances 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
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a quick-decomposing device for turbine blades of an engine, which comprises a base, a fixed support beam, a quick-decomposing ring and a fixed support foot rest, wherein the fixed support beam is rotatably arranged on the base, the quick-decomposing ring is sleeved on the outer side of the base, and a gap is arranged between the quick-decomposing ring and the base; the quick-decomposing ring is connected with the fixed support cross beam through the fixed support foot rest, and the lower surface of the quick-decomposing ring is provided with the ring groove.
Description
Technical Field
The invention relates to the technical field of engine maintenance, in particular to a quick decomposing device for turbine blades of an engine.
Background
The turbine component of the aeroengine mainly comprises turbine blades and turbine rotor blades, and the turbine rotor blades are used for converting kinetic energy and heat energy of engine fuel gas into rotary mechanical work and driving other accessories such as a compressor and the like, and the turbine rotor blades are used as components with the largest thermal load and power load in the engine, so that faults such as ablation, cracks and the like are easy to generate in the working process of the engine, and the faults such as cracks, ablation, abrasion and the like of the turbine rotor blades are required to be checked regularly. When the engine is overhauled, the turbine rotor blade is required to be disassembled for inspection and the like.
Because the turbine rotor blades are arranged at the outer circumference of the turbine blades, the gap between two adjacent turbine rotor blades is very small, and meanwhile, the edge plates of the turbine rotor blades are restrained with the mortises of the turbine blades at an angle of about 10 degrees, so that the turbine rotor blades are difficult to disassemble. At present, a plastic hammer is mainly used for lightly knocking the blade tip of a turbine rotor inwards along the radial direction, the carbon deposition of the turbine rotor blades is loosened, one turbine rotor blade is pulled out backwards by hand, a gap is formed between the blade tip and a flange plate of an adjacent turbine rotor blade, and the next turbine rotor blade (in the rear view and anticlockwise direction) is pulled out backwards by hand. The turbine rotor blades are sequentially plucked out in this order until one turbine rotor blade is completely plucked out. The turbine rotor blade is knocked loose and then detached, so that the turbine rotor blade is easy to damage, the detachment process is complex, and the detachment efficiency is low.
Disclosure of Invention
In order to solve the problems, the invention provides a quick-decomposing device for turbine blades of an engine, which comprises a base, a fixed support beam, a quick-decomposing ring and a fixed support foot rest, wherein the fixed support beam is rotatably arranged on the base, the quick-decomposing ring is sleeved outside the base, and a gap is arranged between the quick-decomposing ring and the base; the quick-decomposing ring is connected with the fixed support cross beam through the fixed support foot rest, and the quick-decomposing ring is provided with a ring groove.
The quick-decomposing ring is provided with a round hole, a support fixing bolt is arranged on the fixed support foot rest, and the support fixing bolt penetrates through the round hole and fixes the quick-decomposing ring on the fixed support foot rest through a nut.
The fixed support beam is provided with a rotary handle.
The diameter of the quick-decomposition ring is the same as the diameter of the end face of the turbine blade of the engine.
The quick-decomposing ring is made of polytetrafluoroethylene.
The invention has the beneficial effects that: (1) The quick-decomposing ring is made of polytetrafluoroethylene, and when the turbine rotor blade is disassembled, polytetrafluoroethylene materials are softer, so that damage to the turbine blade can be avoided.
(2) The size of the quick-speed decomposing ring is consistent with the size of the end face of a turbine blade disc of the engine, and the flange plate of each turbine rotor blade on the turbine blade can be installed in the ring groove of the quick-speed decomposing ring.
(3) This quick decomposition device of engine turbine rotor blade takes down the turbine blade on the turbine blade as a whole through fixed bolster screwing force, overcomes the frictional force between turbine blade tongue-and-groove and the turbine rotor blade and pulls out turbine rotor blade from the turbine blade tongue-and-groove is whole, has prevented to strike the blade damage that the blade split caused in the past.
(4) Through the application of quick decomposition ring, can take off the blade on the turbine blade as a whole, split efficiency improves to 2 ~ 5min from 60min, avoids the damage that blade on the turbine blade knocked and caused.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of a quick-release ring according to the present invention;
FIG. 3 is a split schematic of a turbine rotor in a comparative example;
in the figure, the base is 1-, the ring is 2-quick-disassembly, the fixing bolts are 3-support, the support frame is 4-turbine blades A, the support frame is 5-support, the cross beam is 6-support, the rotating handle is 7-, the round hole is 8-round, the ring groove is 9-, the tongue groove of the turbine blades is 10-, the edge plate of the turbine rotor blades is 11-and the turbine blades are 12-.
Detailed Description
For a clearer understanding of technical features, objects, and effects of the present invention, a specific embodiment of the present invention will be described with reference to the accompanying drawings.
As shown in fig. 1, the quick-decomposing device for the turbine rotor blade of the engine comprises a base 1, a quick-decomposing ring 2, a bracket fixing bolt 3, a fixed bracket foot rest 5, a fixed bracket cross beam 6 and a rotating handle 7.
As shown in fig. 1 and 2, the base 1 penetrates through an inner hole of the quick-release ring 2 and is in rotary connection with a bracket beam 6, and a rotary handle 7 is arranged on the bracket beam 6; one end of the fixed support foot rest 5 is detachably connected to the fixed support cross beam 6, and the other end of the fixed support foot rest is connected with the detachable quick-decomposing ring 2. The size of the quick-decomposition ring 2 is consistent with the size of the end face of the turbine blade of the engine, the quick-decomposition ring 2 is provided with a ring groove 9, and the edge plate of each turbine blade A4 on the turbine blade can be arranged in the ring groove 9. The quick-decomposing ring 2 is made of polytetrafluoroethylene.
As shown in fig. 1 and 2, the quick-decomposition ring 2 is provided with four circular holes 8 distributed in annular array, the fixed support foot rest 5 is connected with a support fixing bolt 3, the support fixing bolt 3 passes through the circular holes 8, and the quick-decomposition ring 2 is fixed on the fixed support foot rest 5 through nuts of bolts, so that the fixed support foot rest 5 and the quick-decomposition ring 2 form a unified whole.
When the turbine rotor blade is disassembled, the quick-disassembly circular ring 2 is aligned to the edge plate of each turbine blade A4 on the turbine blade, the edge plate of each turbine blade A4 is inserted into the circular ring groove 9 of the quick-disassembly circular ring 2, and the bracket fixing bolts 3 on the bracket foot rest 5 penetrate through the circular holes 8 on the quick-disassembly circular ring 2 and fix the quick-disassembly circular ring 2 through nuts. The fixed support cross beam 6 forms a unified whole with the quick-release ring 2 through the fixed support foot rest 5, the rotating handle 7 is rotated, and the turbine blade A4 on the turbine blade is integrally taken down through the tightening force of the fixed support.
Comparative examples:
as shown in fig. 3, the plastic hammer lightly strikes the turbine rotor blade tip radially inward, shakes the turbine blades B12, manually dials a blade B12 slightly backward along the turbine blade slot 10, gaps between the turbine rotor blade rim plate 11 and the adjacent turbine rotor blade rim plate 11, and manually dials the next blade B12 slightly backward (backward view, counterclockwise direction). The turbine blades B12 are sequentially plucked out in this order until each turbine blade B12 is completely plucked out.
Claims (3)
1. The quick-decomposing device for the turbine blade of the engine is characterized by comprising a base (1), a fixed support beam (6), a quick-decomposing ring (2) and a fixed support foot rest (5), wherein the fixed support beam (6) is rotatably arranged on the base (1), the quick-decomposing ring (2) is sleeved outside the base (1), and a gap is arranged between the quick-decomposing ring (2) and the base (1); the quick-decomposition ring (2) is connected with the fixed support cross beam (6) through the fixed support foot rest (5), the quick-decomposition ring (2) is provided with the circular groove (9), the quick-decomposition ring (2) is provided with the round hole (8), the fixed support foot rest (5) is provided with the support fixing bolt (3), the support fixing bolt (3) passes the round hole (8) to fix the quick-decomposition ring (2) on the fixed support foot rest (5) through the nut, the diameter of the quick-decomposition ring (2) be the same with the diameter of the turbine blade end face of the engine, the edge plate of each turbine rotor blade on the turbine blade of the engine can be installed in the circular groove (9) of the quick-decomposition ring (2), the fixed support cross beam (6) on be provided with twist grip (7).
2. The rapid disassembly device for engine turbine blades according to claim 1, wherein the rapid disassembly ring (2) is composed of polytetrafluoroethylene.
3. A method of using the rapid engine turbine blade decomposition apparatus according to any one of claims 1-2, comprising the steps of:
s1: placing the turbine blade on the quick-release ring (2) to enable the edge plate of the turbine blade (4) to be inserted into the ring groove (9) of the quick-release ring (2);
s2: the quick-decomposing ring (2) is fixed on a fixed support foot rest (5) through a support fixing bolt (3);
s3: rotating a rotating handle (7) of the device and lifting up the turbine blades; the turbine blade is integrally taken down by the screwing force of the fixing support.
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 CN110216623A (en) | 2019-09-10 |
| CN110216623B true CN110216623B (en) | 2024-01-02 |
Family
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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) |
Families Citing this family (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 |
| 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 |
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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110216623A (en) | 2019-09-10 |
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