CN102400721B - Replacement method of fulcrum heat-insulating screen of turbine bearing - Google Patents
Replacement method of fulcrum heat-insulating screen of turbine bearing Download PDFInfo
- Publication number
- CN102400721B CN102400721B CN201110339106.0A CN201110339106A CN102400721B CN 102400721 B CN102400721 B CN 102400721B CN 201110339106 A CN201110339106 A CN 201110339106A CN 102400721 B CN102400721 B CN 102400721B
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- rivet
- fulcrum
- heat
- heat screen
- riveted joint
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Abstract
The invention discloses a replacement method of a fulcrum heat-insulating screen of a turbine bearing, belonging to the technical field of repair of an aircraft engine. According to the method, after the fulcrum heat-insulating screen is replaced, the turbine bearing can meet the requirements in the technical documents of the engine so as to meet the use requirements of the engine. The replacement method comprises the following steps of: removing a first rivet on a rear outer installing edge, removing a second rivet on a rear inner installing edge and removing a third rivet at the tail of a rectifying supporting plate; taking down screws of the rectifying supporting plate, removing a fourth rivet on a front outer installing edge and taking down the fulcrum heat-insulating screen needing to be replaced; installing a new fulcrum heat-insulating screen, drilling rivet holes on the fulcrum heat-insulating screen and front and rear installing edges, clearing burrs, and checking the riveting size; installing the first rivet, the second rivet and the fourth rivet, using a tooling for fixing, and then riveting the fulcrum heat-insulating screen; and installing the screws, adopting argon arc welding for two-point positioning welding, and riveting the third rivet at the tail end of the rectifying supporting plate.
Description
Technical field
The invention belongs to aeroengine service technique field, particularly relate to a kind of replacing method of turbine supporting fulcrum heat screen.
Background technique
Aero-turbine supporting is the main load parts of motor rear support, has born the own wt of turbine part and has come to the rotation of low-pressure turbine, the axial stress of motor, and the load of bearing is larger.In addition, turbine supports at work, and the rectification support plate on it and fulcrum heat screen are subject to the impact of air mass flow and vibration simultaneously, causes rectification support plate and fulcrum heat screen to be prone to crackle.
At present, can only adopt the method for repeatedly carrying out repair welding to repair, but be subject to the restriction of crack length and repair welding number of times; And fulcrum heat screen and rectification support plate are injured, are fallen piece fault and cannot repair.
Summary of the invention
The problem existing for prior art, the invention provides a kind of replacing method that turbine supports fulcrum heat screen.The turbine supporting of changing after fulcrum heat screen according to the method can meet engine technology documentation requirements, reaches motor usage requirement.
To achieve these goals, the present invention adopts following technological scheme, and a kind of replacing method of turbine supporting fulcrum heat screen, comprises the steps:
Step 1: the first rivet after removing on outer mounting edge;
Step 2: the second rivet in after removing on mounting edge;
Step 3: the 3rd rivet of removing rectification support plate tail end;
Step 4: the screw that takes off rectification support plate;
Step 5: the 4th rivet before removing on outer mounting edge;
Step 6: under the fulcrum heat screen that needs are changed divides;
Step 7: new fulcrum heat screen is installed;
Step 8: bore the rivet hole on fulcrum heat screen and forward and backward mounting edge, deburr, checks riveted joint size;
Step 9: first, second and the 4th rivet are installed, are fixed by frock, then rivet fulcrum heat screen;
Step 10: mounting screw, and adopt argon arc welding two point location welding;
Step 11: the 3rd rivet of riveted joint rectification support plate tail end.
The concrete grammar of the inspection riveted joint size described in step 8 is as follows:
Judge whether rivet diameter d meets: 4.0mm≤d≤4.5mm;
After riveted joint, whether the die diameter d 1 of rivet meets: d1=6.0 ± 0.4mm;
After riveted joint, whether the die height h1 of rivet meets: h1 >=1.6mm;
If above-mentioned three conditions all meet, judge that riveted joint size is qualified.
Beneficial effect of the present invention:
Use replacing method of the present invention, can not be subject to the restriction of fulcrum heat screen crack length and repair welding number of times; And, piece fault is injured, fallen to fulcrum heat screen and can directly change fulcrum heat screen, saved the cost of production of integral replacing turbine supporting.Turbine supporting fulcrum heat screen can meet engine turbine supporting technology documentation requirements after changing, and reaches motor usage requirement, for the eliminating of the fault of turbine supporting is from now on laid a good foundation.
Accompanying drawing explanation
Fig. 1 is the structural representation of one embodiment of the present of invention;
Fig. 2 is the C-C sectional view of Fig. 1;
In figure, 1-fulcrum heat screen, outer mounting edge before 2-, 3-the 4th rivet, 4-the first rivet, outer mounting edge after 5-, 6-the 3rd rivet, 7-rectification support plate, interior mounting edge after 8-, 9-the second rivet, 10-screw.
Embodiment
From the turbine supporting that seriously cannot repair because of the damage of fulcrum heat screen, choose 1, apply the replacing that replacing method of the present invention is carried out turbine supporting fulcrum heat screen, comprise the steps:
Step 1: the first rivet after removing on outer mounting edge;
Step 2: the second rivet in after removing on mounting edge;
Step 3: the 3rd rivet of removing rectification support plate tail end;
Step 4: the screw that takes off rectification support plate;
Step 5: the 4th rivet before removing on outer mounting edge;
Step 6: under the fulcrum heat screen that needs are changed divides;
Step 7: new fulcrum heat screen is installed, and check measurement gap and tip dimensions, referring to table 1;
Step 8: bore the rivet hole on fulcrum heat screen and forward and backward mounting edge, deburr, checks riveted joint size;
The concrete grammar of described inspection riveted joint size is as follows:
Judge whether rivet diameter d meets: 4.0mm≤d≤4.5mm; After riveted joint, whether the die diameter d 1 of rivet meets: d1=6.0 ± 0.4mm; After riveted joint, whether the die height h1 of rivet meets: h1 >=1.6mm; If above-mentioned three conditions all meet, judge that riveted joint size is qualified;
Step 9: first, second and the 4th rivet are installed, are fixed by frock, then rivet fulcrum heat screen;
Step 10: mounting screw, and adopt argon arc welding two point location welding;
Step 11: the 3rd rivet of riveted joint rectification support plate tail end;
Step 12: dress watch, submit check to.
Measurement clearance and tip dimensions before table 1 fulcrum heat screen decomposes
Measurement clearance and tip dimensions after table 2 fulcrum heat screen is changed
Conclusion: by the turbine bearing assembly contrast situation before decomposing, after replacing, part deformation is less, meets design drawing requirement.
Test run checking:
Apply replacing method of the present invention and carry out after the replacing of turbine supporting fulcrum heat screen, by after bench test drive, to turbine, supporting requires to carry out visual examination, visual examination is qualified.
Under component states, according to specification of technical file, Bearing Casing is carried out to jitter values measurement, measurement result: jitter values is 0.1, meets documentation requirements.
Conclusion: turbine supporting fulcrum heat screen can meet technical requirements after changing, and changes technological method feasible, can be used for produced on-site.
Claims (2)
1. a replacing method for turbine supporting fulcrum heat screen, is characterized in that, comprises the steps:
Step 1: the first rivet after removing on outer mounting edge;
Step 2: the second rivet in after removing on mounting edge;
Step 3: the 3rd rivet of removing rectification support plate tail end;
Step 4: the screw that takes off rectification support plate;
Step 5: the 4th rivet before removing on outer mounting edge;
Step 6: under the fulcrum heat screen that needs are changed divides;
Step 7: new fulcrum heat screen is installed;
Step 8: bore the rivet hole on fulcrum heat screen and forward and backward mounting edge, deburr, checks riveted joint size;
Step 9: first, second and the 4th rivet are installed, are fixed by frock, then rivet fulcrum heat screen;
Step 10: mounting screw, and adopt argon arc welding two point location welding;
Step 11: the 3rd rivet of riveted joint rectification support plate tail end.
2. a kind of turbine according to claim 1 supports the replacing method of fulcrum heat screen, it is characterized in that the concrete grammar of the inspection riveted joint size described in step 8 is as follows:
Judge whether rivet diameter d meets: 4.0mm≤d≤4.5mm;
After riveted joint, whether the die diameter d 1 of rivet meets: d1=6.0 ± 0.4mm;
After riveted joint, whether the die height h1 of rivet meets: h1 >=1.6mm;
If above-mentioned three conditions all meet, judge that riveted joint size is qualified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110339106.0A CN102400721B (en) | 2011-11-01 | 2011-11-01 | Replacement method of fulcrum heat-insulating screen of turbine bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110339106.0A CN102400721B (en) | 2011-11-01 | 2011-11-01 | Replacement method of fulcrum heat-insulating screen of turbine bearing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102400721A CN102400721A (en) | 2012-04-04 |
| CN102400721B true CN102400721B (en) | 2014-04-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110339106.0A Expired - Fee Related CN102400721B (en) | 2011-11-01 | 2011-11-01 | Replacement method of fulcrum heat-insulating screen of turbine bearing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102400721B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106593654A (en) * | 2016-12-23 | 2017-04-26 | 贵州黎阳航空动力有限公司 | Thermal insulation device for gas turbine |
| CN106437884A (en) * | 2016-12-24 | 2017-02-22 | 贵州黎阳航空动力有限公司 | Long-service-life turbine bearing structure for gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3269700A (en) * | 1964-12-07 | 1966-08-30 | United Aircraft Corp | Heat shield for turbine strut |
| CN1818527A (en) * | 2005-02-07 | 2006-08-16 | 西门子公司 | Heat shield |
| JP4172913B2 (en) * | 1998-03-19 | 2008-10-29 | シーメンス アクチエンゲゼルシヤフト | Combustor wall segment and combustor |
| CN101922728A (en) * | 2009-06-09 | 2010-12-22 | 西门子公司 | Heat shield member arrangement and method for assembling a heat shield member |
| CN102066840A (en) * | 2008-06-12 | 2011-05-18 | 西门子公司 | Heat shield arrangement |
-
2011
- 2011-11-01 CN CN201110339106.0A patent/CN102400721B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3269700A (en) * | 1964-12-07 | 1966-08-30 | United Aircraft Corp | Heat shield for turbine strut |
| JP4172913B2 (en) * | 1998-03-19 | 2008-10-29 | シーメンス アクチエンゲゼルシヤフト | Combustor wall segment and combustor |
| CN1818527A (en) * | 2005-02-07 | 2006-08-16 | 西门子公司 | Heat shield |
| CN102066840A (en) * | 2008-06-12 | 2011-05-18 | 西门子公司 | Heat shield arrangement |
| CN101922728A (en) * | 2009-06-09 | 2010-12-22 | 西门子公司 | Heat shield member arrangement and method for assembling a heat shield member |
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| Publication number | Publication date |
|---|---|
| CN102400721A (en) | 2012-04-04 |
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| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
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| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140402 Termination date: 20201101 |