CN111173570A - Method for replacing turbine blade - Google Patents
Method for replacing turbine blade Download PDFInfo
- Publication number
- CN111173570A CN111173570A CN201911388617.4A CN201911388617A CN111173570A CN 111173570 A CN111173570 A CN 111173570A CN 201911388617 A CN201911388617 A CN 201911388617A CN 111173570 A CN111173570 A CN 111173570A
- Authority
- CN
- China
- Prior art keywords
- turbine
- blade
- blades
- disc
- replacing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
-
- 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
- G01M1/34—Compensating unbalance by removing material from the body to be tested, e.g. from the tread of tyres
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/70—Disassembly methods
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a method for replacing a turbine blade, which ensures that a proper blade is installed by the modes of disassembly and decomposition, cleaning and inspection, disk body balance, blade matching, primary grinding of an excircle, assembly balance, final grinding of the excircle, locking plate installation and final inspection. Meanwhile, the implementation of the method can obviously reduce the consumption of the shipping materials caused by reworking, save the maintenance cost, obviously improve the one-time yield of turbine repair and reduce the maintenance period.
Description
Technical Field
The invention belongs to the technical field of airplane maintenance, and particularly relates to a method for replacing a turbine blade, in particular to a method for replacing a first-stage turbine blade and a second-stage turbine blade of an APS3200 type auxiliary power device.
Background
The auxiliary power device is a power device on the airplane except for a main engine, is called AuxiliaryPower Unit (APU for short) for short, is used for independently providing air conditioning bleed air and power for the airplane and simultaneously providing compressed air to assist the starting of the engine, is an important indispensable system on the airplane, and is a device on the airplane except for the main engine, and has the most complex structure and the highest precision.
APS3200 type APU is installed on air passenger A319/A320/A321 series airplane. The device can be roughly divided into an accessory gearbox, a load section and a power section. The turbine is used as a core component of the APU power section, converts heat energy of gas into self mechanical energy, and plays a key role in driving the APU to rotate by applying work. Because the turbine blade works in a high-temperature and high-pressure gas environment for a long time, the turbine blade is frequently damaged by wind erosion, ablation and the like.
An APS3200 model turbine adopts an axial flow turbine and is divided into two stages. The two stages of turbines are mutually independent and are mutually connected through the key teeth. The turbine mainly comprises a turbine disc 1, blades 2, locking plates 3 and an air seal 4, and the structure of the turbine is specifically shown in figure 1. The blade grooves are uniformly distributed on the circumference of the turbine disc and used for installing the blades. And the blades are fixed to the designated positions of the turbine disk through locking plates.
In the repair process of the APU, the turbine repair is an important link, is a complex repair work which involves a plurality of procedures and needs a plurality of large-scale equipment, and is a main index for reflecting the repair depth of the APU. The establishment of the turbine repair capability can reduce the foreign repair cost of the damaged turbine assembly, accelerate the turnover time of parts and reduce the spare part reserve fund. Turbine repairs have contributed greatly to companies over the years to reduce maintenance costs and down time.
No more than 10 plants are able to replace the model APS3200 turbine blade worldwide, typically according to the service manual provided by the APS3200 manufacturer. Although the method can complete the replacement work of the turbine blade, the turbine disk works for a long time under the environment of high temperature and high rotating speed (nearly 20000 revolutions per minute), the turbine disk has creep deformation, and the blade mounting hole of the turbine disk is gradually enlarged. Meanwhile, the turbine blade is replaced according to the process, manual experience is relied on too much, the condition that the final unbalance amount is not passed after cylindrical grinding is easily caused, the one-time yield is low, and certain difficulty is caused in actual operation. Repeated blade disassembly and assembly not only prolongs the production cycle, but also causes the waste of the locking plate.
Disclosure of Invention
The invention aims to provide a method for replacing a turbine blade, which is practical, efficient and excellent in quality, reduces time cost and material consumption, and improves the one-time yield of turbine components.
The above object of the present invention can be achieved by the following technical solutions: a method of replacing a turbine blade comprising the steps of:
(1) disassembling and decomposing: all blades and locking plates on the turbine are dismounted in a manner of dismounting the locking plates of the turbine;
(2) cleaning and checking: cleaning and checking the detached turbine disc to ensure that the turbine disc is usable;
(3) balancing the disc body: carrying out disk body balance on an available turbine disk by using a balancing machine, and recording the unbalance amount of the turbine disk;
(4) blade matching: marking a blade mounting groove on a turbine disc, randomly selecting a brand new blade, performing gap matching between the blade and the blade mounting groove, selecting a set of proper blades, and recording marks of the blade mounting groove proper to the blades;
(5) primary grinding of the excircle: sequentially installing the marked blades into corresponding turbine disk blade installation grooves, grinding the outer diameter of the turbine blade by using a cylindrical grinder, and reserving a small amount of allowance when the outer diameter of the turbine blade actually reaches a specified value;
(6) balancing the components: ensuring that the corresponding relation between the grinded turbine disc and the blade is unchanged, placing the turbine assembly on a balancing machine, and enabling the unbalance amount of the turbine assembly to reach a specified range by readjusting the position of the blade on the blade mounting groove;
(7) and (3) final grinding of the excircle: keeping the positions of the turbine disc and the blades unchanged after the turbine assembly is balanced, mounting the turbine assembly on the cylindrical grinder again, and grinding the outer diameter of the turbine blade to a specified size;
(8) and (3) mounting the locking plate: a brand new locking plate is sequentially arranged between the turbine disc and the blade, and the blade is fixed on the turbine disc through the locking plate;
(9) and (4) final inspection: and (3) placing the assembled turbine assembly on a balancing machine, and carrying out unbalance amount verification on the assembly to ensure that the unbalance amount is within a specified value.
In the method for replacing a turbine blade described above:
preferably, the inspection of the removed turbine disk in step (2) is to perform a fluorescent inspection and an internal eddy current inspection of the surface of the turbine disk to ensure that the turbine disk is usable.
Preferably, in the step (4), the gap between the blade and the blade mounting groove is matched, so that the proper gap between the blade and the blade mounting groove is ensured, and the gap size requires that the circumferential movable gap after the blade is mounted on the turbine disk does not exceed 1 mm.
Preferably, when the marked blades are sequentially installed in the blade installation grooves of the corresponding turbine disc in the step (5), locking plates are not installed, the outer diameter of the turbine blade is ground by using a cylindrical grinder, and the range which actually reaches above a specified value and reserves a small part of allowance is as follows: the final outer diameter of the turbine assembly is in the range of 178.65-178.70 mm.
Preferably, the unbalance amount of the turbine assembly in the step (6) is within a specified range of 10 gmm.
Preferably, the outer diameter of the turbine blade is ground in the step (7) until the final outer diameter of the turbine assembly is within a specified size of 177.95-178.00 mm.
Preferably, in the step (8), the blade is fixed on the turbine disk by bending the locking plate, and the bent part of the locking plate is ensured to be tightly attached to the surface of the turbine disk.
Preferably, the amount of unbalance in step (9) is in the range of 10 gmm.
Compared with the prior art, the invention has the following advantages:
(1) the process has strong universality and can be suitable for all turbine balance type work;
(2) the invention has perfect flow, is scientific and effective, and saves a large amount of labor cost and time cost;
(3) according to the invention, the clearance fit between the blade and the turbine disc is increased, and the condition that the assembly is unbalanced after grinding in the traditional mode is avoided through the form of primary grinding, balancing and final grinding of the excircle, so that the blade is prevented from being disassembled and replaced due to unbalance, and the quality of the turbine assembly and the first finished product rate of repair can be improved;
(4) according to the process, in the process of replacing the first-stage and second-stage turbine blades of the APS3200APU, a large amount of time consumed by repeatedly replacing the blades for balancing attempts is avoided, and the consumption of sailing materials caused by reworking is reduced.
Drawings
FIG. 1 is a schematic diagram of the turbine structure of the prior art;
FIG. 2 is a flow chart illustrating a method for turbine blade replacement in accordance with an embodiment of the present invention.
Detailed Description
Example 1
As shown in fig. 2, the method for replacing a turbine blade according to the present embodiment includes the following steps:
(1) disassembling and decomposing: all blades and locking plates on the turbine are dismounted in a manner of dismounting the locking plates of the turbine;
the concrete operation process recommendation is as follows: the locking piece is unfolded to detach the blade, the turbine disk is positioned on a turbine support (a conventional support workpiece for supporting the turbine disk, a universal tool and only provides support for the turbine), when the turbine disk is positioned, the rear edge of the blade faces upwards, and the turbine disk must be stably contacted with the turbine support. The blade and locking plate are removed from the rear end with a punch (a common tool, with a flat head, similar to a screwdriver, typically a brass punch or an aluminum punch) that gently strikes the locking plate to a point completely clear of the turbine surface and aligned with the blade mounting slot, typically with blade wear occurring on all blades, and therefore typically requires replacement of all blades.
(2) Cleaning and checking: cleaning and checking the detached turbine disc to ensure that the turbine disc is usable;
the concrete operation process recommendation is as follows: and carrying out fluorescent flaw detection inspection and internal eddy current inspection on the surface of the detached turbine disk to ensure that the turbine disk is usable.
(3) Balancing the disc body: carrying out disk body balance on an available turbine disk by using a balancing machine, and recording the unbalance amount of the turbine disk;
in order to ensure the smooth operation of the turbine, the turbine usually needs to be balanced before being installed, and the unbalance amount and the angle of the turbine disc are recorded (the balancer outputs the unbalance angle while measuring the unbalance amount). Balancing of the turbine usually means to be mounted on a corresponding tool (a general tool for supporting the turbine), and rotating (usually 1000 rpm) the turbine by a balancing machine (a conventional balancing machine such as SCHENCK HM1 model 1 BU), using a balancing machine motor and a belt to rotate, since the tool is provided when balancing the turbine, in order to remove the unbalance amount of the tool itself, the tool is usually rotated 180 degrees relative to the mounting position to remove the unbalance amount of the tool, this method is the basic work of balancing, commonly called compensation, wherein the mark of the "0" position is 180 degrees from the cursor attached to the tool, and the torque value of the tightening tool nut is 310 in.lb.
Wherein the turbine disk must ensure a midpoint, contact surface of the turbine disk and balance the finish of the tooling surface.
(4) Blade matching: marking a blade mounting groove on a turbine disc, randomly selecting a brand new blade, performing gap matching between the blade and the blade mounting groove, selecting a set of proper blades, and recording marks of the blade mounting groove proper to the blades;
the concrete operation process recommendation is as follows: the blade mounting groove on the turbine disc after will balancing is numbered, selects brand-new turbine blade at random, matches its blade mounting groove on with the turbine disc in proper order, and the clearance of blade mounting groove and blade can not too loose nor too tight, requires that the blade install on the turbine disc after the circumferential clearance be no longer than 1 millimeter to mark the serial number with its complex blade mounting groove on the blade.
(5) Primary grinding of the excircle: sequentially installing the marked blades into corresponding turbine disk blade installation grooves, grinding the outer diameter of the turbine blade by using a cylindrical grinder, and reserving a small amount of allowance when the outer diameter of the turbine blade actually reaches a specified value;
the concrete operation process recommendation is as follows: and according to the corresponding relation between the blades and the blade mounting grooves, the blades are sequentially mounted in the blade mounting grooves of the turbine disc. Note that the locking tab is not installed at this time. And grinding the length of the blade by using a cylindrical grinding machine to enable the final outer diameter of the turbine assembly to be in the range of 178.65-178.70 mm.
(6) Balancing the components: ensuring that the corresponding relation between the grinded turbine disc and the blade is unchanged, placing the turbine assembly on a balancing machine, and enabling the unbalance amount of the turbine assembly to reach a specified range by readjusting the position of the blade on the blade mounting groove;
the concrete operation process recommendation is as follows: the corresponding relation between the grinded turbine disc and the blades is ensured to be unchanged, the turbine assembly is placed on a balancing machine, and the unbalance amount of the turbine assembly is within a specified range by changing the relative positions of the blades. The method for exchanging the relative positions of the blades can be realized by manually adjusting the blades from one position of the blade mounting groove to other suitable positions, so that the unbalance amount of the turbine assembly can reach a specified range of 10gmm, a conventional calculation software (obtained data is recorded into Excel) can be designed, the weight of each blade and the unbalance amount of a turbine disk are input into the calculation software by weighing the blades, the relative position of the blades and the turbine disk when the theoretical unbalance amount of the turbine assembly is minimum is planned through the calculation of the software, and the unbalance amount of the assembly is adjusted to a specified requirement of 10gmm through the method for exchanging the positions of the blades.
Preferably, the blades are mounted in a clockwise direction as viewed from the rear to the front of the turbine disk.
(7) And (3) final grinding of the excircle: and (4) keeping the position of the turbine disk and the blade (the position of the blade is the position relationship of the blade readjusted in the step (6)) unchanged after the turbine assembly is balanced, and mounting the turbine assembly on the cylindrical grinding machine again to grind the outer diameter of the turbine blade until the final outer diameter of the turbine assembly is within the specified size of 177.95-178.00 mm.
(8) And (3) mounting the locking plate: a brand new locking plate is sequentially arranged between the turbine disc and the blade, and the blade is fixed on the turbine disc through the locking plate;
the concrete operation process recommendation is as follows: keep blade and turbine dish position unchangeable this moment, place turbine assembly on supporting, install the locking plate between every blade and turbine dish in proper order, through the mode of buckling the locking plate, utilize aluminium punching pin or copper punching pin to buckle the both ends of all locking plates, fix turbine blade on the turbine dish, ensure that the locking plate is buckled partly and is hugged closely turbine dish surface.
After the locking piece was mounted and bent, the locking piece was inspected for cracks.
(9) And (4) final inspection: and (3) placing the assembled turbine assembly on a balancing machine, and carrying out unbalance verification on the assembly to ensure that the unbalance of the turbine assembly is within a 10gmm specified value.
The position, the axial clearance and the like of the blade can be further checked, the distance from the surface of the blade trailing edge disc to the surface of the blade is preferably 0-0.38 mm, and the axial movable clearance of the blade is preferably 0-0.05 mm.
According to the turbine blade replacing method, through the modes of disassembling, cleaning, checking, balancing a disk body, matching blades, primarily grinding an excircle, balancing an assembly, finally grinding the excircle, installing locking plates and finally checking, proper blades are guaranteed to be installed, the unbalance amount of the turbine disk and the quality of each blade are comprehensively utilized, after balance is simulated, a reasonable blade installing scheme is matched according to the data, balance efficiency can be improved, and blade replacing work is finally completed. Compared with the existing method which simply depends on manual experience to replace the blades, the existing method has the advantages that on one hand, the blades are more, the balancing process time is long, the balancing efficiency is seriously influenced, on the other hand, the repeated disassembly and balancing of the blades can cause abrasion to the turbine disc and the blades, and the damage and the waste of aviation materials are caused. Therefore, the method of the invention remarkably improves the turbine repair efficiency and quality after the process is improved by selecting the fit clearance range, the quality range, the simulation balance and the proper balance verification of the blade. The implementation of the method obviously reduces the consumption of the shipping materials caused by reworking, saves the maintenance cost, obviously improves the one-time yield of turbine repair and reduces the maintenance period.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (8)
1. A method for replacing a turbine blade, comprising the steps of:
(1) disassembling and decomposing: all blades and locking plates on the turbine are dismounted in a manner of dismounting the locking plates of the turbine;
(2) cleaning and checking: cleaning and checking the detached turbine disc to ensure that the turbine disc is usable;
(3) balancing the disc body: carrying out disk body balance on an available turbine disk by using a balancing machine, and recording the unbalance amount of the turbine disk;
(4) blade matching: marking a blade mounting groove on a turbine disc, randomly selecting a brand new blade, performing gap matching between the blade and the blade mounting groove, selecting a set of proper blades, and recording marks of the blade mounting groove proper to the blades;
(5) primary grinding of the excircle: sequentially installing the marked blades into corresponding turbine disk blade installation grooves, grinding the outer diameter of the turbine blade by using a cylindrical grinder, and reserving a small amount of allowance when the outer diameter of the turbine blade actually reaches a specified value;
(6) balancing the components: ensuring that the corresponding relation between the grinded turbine disc and the blade is unchanged, placing the turbine assembly on a balancing machine, and enabling the unbalance amount of the turbine assembly to reach a specified range by readjusting the position of the blade on the blade mounting groove;
(7) and (3) final grinding of the excircle: keeping the positions of the turbine disc and the blades unchanged after the turbine assembly is balanced, mounting the turbine assembly on the cylindrical grinder again, and grinding the outer diameter of the turbine blade to a specified size;
(8) and (3) mounting the locking plate: a brand new locking plate is sequentially arranged between the turbine disc and the blade, and the blade is fixed on the turbine disc through the locking plate;
(9) and (4) final inspection: and (3) placing the assembled turbine assembly on a balancing machine, and carrying out unbalance amount verification on the assembly to ensure that the unbalance amount is within a specified value.
2. The method for replacing a turbine blade according to claim 1, wherein: the step (2) of inspecting the detached turbine disk means that the surface of the turbine disk is subjected to fluorescent flaw detection and internal eddy current inspection to ensure that the turbine disk is usable.
3. The method for replacing a turbine blade according to claim 1, wherein: and (4) matching the clearance between the blade and the blade mounting groove in the step (4) to ensure that the clearance between the blade and the blade mounting groove is proper, wherein the size of the clearance requires that the circumferential movable clearance of the blade mounted on the turbine disk is not more than 1 mm.
4. The method for replacing a turbine blade according to claim 1, wherein: and (5) when the marked blades are sequentially installed in the blade installation grooves of the corresponding turbine discs, the locking plates are not installed, the outer diameter of the turbine blades is ground by using a cylindrical grinder, and the range of actually reaching the specified value and reserving a small part of allowance is as follows: the final outer diameter of the turbine assembly is in the range of 178.65-178.70 mm.
5. The method for replacing a turbine blade according to claim 1, wherein: and (6) enabling the unbalance amount of the turbine assembly to reach the specified range of 10 gmm.
6. The method for replacing a turbine blade according to claim 1, wherein: and (7) grinding the outer diameter of the turbine blade to the final outer diameter of the turbine assembly within the specified size of 177.95-178.00 mm.
7. The method for replacing a turbine blade according to claim 1, wherein: and (8) fixing the blades on the turbine disc by bending the locking plates, and ensuring that the bent parts of the locking plates are tightly attached to the surface of the turbine disc.
8. The method for replacing a turbine blade according to claim 1, wherein: the amount of unbalance in step (9) is in the range of 10 gmm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911388617.4A CN111173570B (en) | 2019-12-30 | 2019-12-30 | Method for replacing turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911388617.4A CN111173570B (en) | 2019-12-30 | 2019-12-30 | Method for replacing turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111173570A true CN111173570A (en) | 2020-05-19 |
| CN111173570B CN111173570B (en) | 2022-10-25 |
Family
ID=70646447
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911388617.4A Active CN111173570B (en) | 2019-12-30 | 2019-12-30 | Method for replacing turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111173570B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113062777A (en) * | 2021-06-03 | 2021-07-02 | 中国航发上海商用航空发动机制造有限责任公司 | Performance debugging method of booster stage and turbofan engine |
| CN113118924A (en) * | 2021-06-17 | 2021-07-16 | 中国航发上海商用航空发动机制造有限责任公司 | Rotor blade changing method |
| CN114055102A (en) * | 2021-10-20 | 2022-02-18 | 中国航发四川燃气涡轮研究院 | Single turbine blade tip machining method |
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1162722A (en) * | 1980-03-19 | 1984-02-28 | Joel H Cohen | Method and replacement member for repairing a gas turbine engine vane assembly |
| JPH07150903A (en) * | 1993-12-01 | 1995-06-13 | Ishikawajima Harima Heavy Ind Co Ltd | Total number of turbine moving blade replacing method |
| US20050091848A1 (en) * | 2003-11-03 | 2005-05-05 | Nenov Krassimir P. | Turbine blade and a method of manufacturing and repairing a turbine blade |
| CN202756026U (en) * | 2012-06-11 | 2013-02-27 | 湖南航翔燃气轮机有限公司 | Locking mechanism of turbine blades |
| 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 |
-
2019
- 2019-12-30 CN CN201911388617.4A patent/CN111173570B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1162722A (en) * | 1980-03-19 | 1984-02-28 | Joel H Cohen | Method and replacement member for repairing a gas turbine engine vane assembly |
| JPH07150903A (en) * | 1993-12-01 | 1995-06-13 | Ishikawajima Harima Heavy Ind Co Ltd | Total number of turbine moving blade replacing method |
| US20050091848A1 (en) * | 2003-11-03 | 2005-05-05 | Nenov Krassimir P. | Turbine blade and a method of manufacturing and repairing a turbine blade |
| CN202756026U (en) * | 2012-06-11 | 2013-02-27 | 湖南航翔燃气轮机有限公司 | Locking mechanism of turbine blades |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 韩小丽等: "汽轮机叶片更换方案的研究", 《东北电力技术》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113062777A (en) * | 2021-06-03 | 2021-07-02 | 中国航发上海商用航空发动机制造有限责任公司 | Performance debugging method of booster stage and turbofan engine |
| CN113118924A (en) * | 2021-06-17 | 2021-07-16 | 中国航发上海商用航空发动机制造有限责任公司 | Rotor blade changing method |
| CN113118924B (en) * | 2021-06-17 | 2021-09-03 | 中国航发上海商用航空发动机制造有限责任公司 | Rotor blade changing method |
| CN114055102A (en) * | 2021-10-20 | 2022-02-18 | 中国航发四川燃气涡轮研究院 | Single turbine blade tip machining method |
| CN114055102B (en) * | 2021-10-20 | 2023-03-07 | 中国航发四川燃气涡轮研究院 | Single turbine blade tip machining method |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111173570B (en) | 2022-10-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111173570B (en) | Method for replacing turbine blade | |
| EP2866969B1 (en) | Repair of a shrouded blade | |
| US7685876B2 (en) | Methods and systems for balancing a rotatable member | |
| EP2025865B1 (en) | Fan outlet guide vane shroud insert repair | |
| CN102828782B (en) | In order to repair the method and apparatus of turbine rotor wheel | |
| US20110110783A1 (en) | Trunnion hole repair utilizing interference fit inserts | |
| CN105784380B (en) | Aero-engine compressor rotor blade system fault detection method | |
| CN112024750B (en) | Double-layer thin-wall sheet metal casing shape correction and heat treatment setting clamp and method | |
| US7970555B2 (en) | Method for developing a repair process to correct a deformed gas turbine engine component | |
| US8291589B2 (en) | Method for establishing a location of an elevated stress region | |
| US8122601B2 (en) | Methods for correcting twist angle in a gas turbine engine blade | |
| CN109489957B (en) | A switching structure that is used for experimental area stress of rim plate to cut apart groove | |
| JP2009041449A (en) | Repair method for gas turbine rotor vane | |
| CN111734496B (en) | Centrifugal impeller assembly of aviation turbine starter and assembly method of centrifugal impeller assembly | |
| EP3719256A1 (en) | Aircraft component repair system and process | |
| EP3719721A1 (en) | Aircraft component repair scheduling system and process | |
| CN210414064U (en) | Rapid repairing device for abrasion fault of blisk core hole | |
| US10711612B2 (en) | Method for manufacturing a rotor for a turbine engine high-pressure compressor | |
| EP3591174B1 (en) | Aircraft component qualification system and process including variation modelling | |
| CN109852749B (en) | Scraping and matching method for thrust bearing thrust shoe of blast furnace gas turbine set | |
| US9249976B2 (en) | Method for servicing a combustor cap assembly for a turbine | |
| CN106493565B (en) | Process method for overhauling and reassembling wheel-mounted brake disc of motor train unit | |
| CN112705905B (en) | Method for repairing BP-14 main reducer driven spiral bevel gear assembly | |
| CN220452311U (en) | Frock convenient to large-scale unipolar centrifugal compressor adjustment thrust clearance | |
| CN115655922A (en) | Sealing labyrinth disc strength test structure connected by disc edge positioning bolt |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |