CN111173570B - A method of replacing turbine blades - Google Patents
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- CN111173570B CN111173570B CN201911388617.4A CN201911388617A CN111173570B CN 111173570 B CN111173570 B CN 111173570B CN 201911388617 A CN201911388617 A CN 201911388617A CN 111173570 B CN111173570 B CN 111173570B
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- 238000001514 detection method Methods 0.000 claims description 2
- 230000008439 repair process Effects 0.000 abstract description 12
- 238000012423 maintenance Methods 0.000 abstract description 7
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- 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
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- 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
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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 imbalance
- G01M1/34—Compensating imbalance by removing material from the body to be tested, e.g. from the tread of tyres
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- 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
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- 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
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- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
本发明公开了一种涡轮叶片的更换方法，该方法通过拆卸分解、清洗检查、盘体平衡、叶片匹配、初磨外圆、组件平衡、终磨外圆、锁片安装、最终检验的方式，保证安装合适的叶片，该方法通过选择叶片的配合间隙范围、质量范围、模拟平衡及适当的平衡验证，使涡轮叶片的修理效率与质量得到显著提高。同时该方法的实施可显著减少返工造成的航材耗费，节约维修成本，显著提高涡轮修理的一次成品率，减少维修周期。
The invention discloses a method for replacing turbine blades. The method adopts the methods of disassembly and decomposition, cleaning and inspection, disk body balance, blade matching, initial grinding outer circle, component balance, final grinding outer circle, locking piece installation, and final inspection. To ensure the installation of suitable blades, the method can significantly improve the repair efficiency and quality of turbine blades by selecting the matching clearance range, mass range, simulated balance and proper balance verification of the blade. At the same time, the implementation of the method can significantly reduce the consumption of aviation materials caused by rework, save maintenance costs, significantly improve the one-time yield of turbine repair, and reduce maintenance cycles.
Description
技术领域technical field
本发明属于飞机维修技术领域，具体涉及一种涡轮叶片的更换方法，尤其是APS3200型辅助动力装置一、二级涡轮叶片的更换方法。The invention belongs to the technical field of aircraft maintenance, in particular to a method for replacing turbine blades, in particular to a method for replacing primary and secondary turbine blades of an APS3200 auxiliary power unit.
背景技术Background technique
辅助动力装置是飞机上除主发动机外的一台动力装置，英文名称AuxiliaryPower Unit，简称APU，它的作用是独立的为飞机提供空调引气和电源，同时提供压缩空气辅助发动机启动，是飞机上一个重要的不可或缺的系统，是飞机上除主发动机外，结构最复杂，精密度最高的装置。The auxiliary power unit is a power unit other than the main engine on the aircraft. The English name is Auxiliary Power Unit, or APU for short. Its function is to independently provide air-conditioning bleed air and power supply for the aircraft, and at the same time provide compressed air to assist the engine to start. An important and indispensable system is the device with the most complex structure and the highest precision except the main engine on the aircraft.
APS3200型APU安装于空客A319/A320/A321系列飞机。其大致可分为附件齿轮箱、负载段、动力段三部分。涡轮作为APU动力段的核心部件，将燃气的热能转化为自身的机械能，起到了做功带动APU转动的关键作用。由于其长期工作在高温高压的燃气环境中，涡轮叶片多发生风蚀、烧蚀等损伤。APS3200 APU is installed on Airbus A319/A320/A321 series aircraft. It can be roughly divided into three parts: accessory gearbox, load section and power section. As the core component of the APU power section, the turbine converts the thermal energy of the gas into its own mechanical energy, and plays a key role in driving the APU to rotate. Due to the long-term work in the high temperature and high pressure gas environment, the turbine blades are often damaged by wind erosion and ablation.
APS3200型号涡轮采用轴流式涡轮，分为两级。两级涡轮相互独立，通过键齿相互连接。涡轮主要由涡轮盘1、叶片2、锁片3和气封严4组成，其结构具体如图1所示。涡轮盘周向均匀分布叶片槽，用于叶片的安装。并通过锁片将叶片固定到涡轮盘的指定位置。APS3200 model turbine adopts axial flow turbine, which is divided into two stages. The two-stage turbines are independent of each other and are connected to each other by key teeth. The turbine is mainly composed of a
在APU的修理过程中，涡轮修理是一个重要环节，是一个涉及多个工序、需要多个大型设备的复杂修理工作，也是体现APU修理深度的一个主要指标。涡轮修理能力的建立，可降低损伤涡轮组件的国外送修费用，加快零件的周转时间，降低备件储备资金。多年来，涡轮修理为公司降低维修成本、减少停场时间做出了很大的贡献。In the repair process of APU, turbine repair is an important link. It is a complex repair work involving multiple processes and requires multiple large-scale equipment. It is also a major indicator of the depth of APU repair. The establishment of turbine repair capability can reduce the overseas repair cost of damaged turbine components, speed up the turnaround time of parts, and reduce spare parts reserve funds. Over the years, turbine repairs have contributed significantly to reducing maintenance costs and downtime for the company.
全球能够进行APS3200型号涡轮叶片更换的厂家不超过10家，一般按照APS3200生产厂家提供的维修手册进行更换。此方法虽能完成涡轮叶片的更换工作，但由于涡轮盘长期工作在高温高转速(近20000转/分钟)的环境下，涡轮盘存在蠕变，其叶片安装孔会逐渐变大。同时，按照此流程进行涡轮叶片更换，过多依赖于人工经验，极易出现外圆磨削后最终检验不平衡量不通过的情况，一次性成品率低，在实际操作中具有一定的困难。反复拆装叶片不仅延长生产周期，而且造成了锁片的浪费。There are no more than 10 manufacturers that can replace APS3200 turbine blades in the world, and they are generally replaced according to the maintenance manual provided by the APS3200 manufacturer. Although this method can complete the replacement of turbine blades, due to the long-term operation of the turbine disk in the environment of high temperature and high speed (nearly 20,000 rpm), the turbine disk has creep, and the blade mounting hole will gradually become larger. At the same time, the replacement of turbine blades according to this process relies too much on manual experience, and it is very easy to fail the final inspection of the unbalanced amount after cylindrical grinding. The one-time yield is low, and there are certain difficulties in actual operation. Repeated disassembly and assembly of the blades not only prolongs the production cycle, but also causes waste of the locking pieces.
发明内容SUMMARY OF THE INVENTION
本发明的目的在于提供一种涡轮叶片的更换方法，该方法实用高效、质量优良，降低了时间成本与航材耗费，提高了涡轮组件的一次成品率。The purpose of the present invention is to provide a turbine blade replacement method, which is practical, efficient, and of good quality, reduces time cost and aviation material consumption, and improves the primary yield of turbine components.
本发明的上述目的可以通过以下技术方案来实现：一种涡轮叶片的更换方法，包括以下步骤：The above object of the present invention can be achieved through the following technical solutions: a method for replacing turbine blades, comprising the following steps:
(1)拆卸分解：通过拆卸涡轮锁片的方式，拆下涡轮上的全部叶片与锁片；(1) Disassembly and decomposition: Remove all the blades and locking plates on the turbine by disassembling the turbine locking plate;
(2)清洗检查：将拆下的涡轮盘进行清洗与检查，确保涡轮盘可用；(2) Cleaning and inspection: Clean and inspect the removed turbine disk to ensure that the turbine disk is available;
(3)盘体平衡：利用平衡机对可用的涡轮盘进行盘体平衡，记录涡轮盘的不平衡量；(3) Disc balance: use a balancing machine to balance the available turbine discs, and record the unbalance of the turbine discs;
(4)叶片匹配：对涡轮盘上的叶片安装槽进行标记，随机选取全新叶片，进行叶片与叶片安装槽之间的间隙匹配，选择出一套合适的叶片，并在叶片上记录与其合适的叶片安装槽的标记；(4) Blade matching: mark the blade installation groove on the turbine disk, randomly select a new blade, match the gap between the blade and the blade installation groove, select a suitable set of blades, and record the appropriate blade on the blade The marking of the blade mounting slot;
(5)初磨外圆：将标记的叶片依次安装到对应的涡轮盘叶片安装槽内，使用外圆磨床对涡轮叶片的外径进行磨削，实际达到规定值以上并预留少部分余量；(5) Initial grinding of the outer circle: Install the marked blades into the corresponding turbine disk blade installation grooves in sequence, and use an outer cylindrical grinder to grind the outer diameter of the turbine blades, and the actual value is above the specified value and a small margin is reserved. ;
(6)组件平衡：确保磨削后的涡轮盘与叶片对应关系不变，将涡轮组件放在平衡机上，通过重新调整叶片在叶片安装槽上的位置，使涡轮组件不平衡量达到规定范围内；(6) Component balance: ensure that the corresponding relationship between the ground turbine disk and the blade remains unchanged, place the turbine component on the balancer, and readjust the position of the blade on the blade installation slot to make the turbine component unbalance within the specified range;
(7)终磨外圆：保持涡轮组件平衡后涡轮盘与叶片位置不变，再次将涡轮组件安装到外圆磨床上，将涡轮叶片的外径磨削到规定尺寸；(7) Final grinding of the outer circle: after keeping the turbine assembly balanced, the position of the turbine disk and the blade remains unchanged, and the turbine assembly is installed on the outer cylindrical grinder again, and the outer diameter of the turbine blade is ground to the specified size;
(8)锁片安装：依次在涡轮盘与叶片之间安装全新锁片，将叶片通过锁片固定在涡轮盘上；(8) Locking piece installation: Install a new locking piece between the turbine disk and the blade in turn, and fix the blade on the turbine disk through the locking piece;
(9)最终检验：将组装好的涡轮组件放在平衡机上，对组件进行不平衡量验证，确保不平衡量在规定数值内。(9) Final inspection: Put the assembled turbine components on the balancing machine, and verify the unbalance of the components to ensure that the unbalance is within the specified value.
在上述涡轮叶片的更换方法中：In the above-mentioned replacement method of turbine blades:
优选的，步骤(2)中将拆下的涡轮盘进行检查是指对涡轮盘表面进行荧光探伤检查和内部涡流检查，确保涡轮盘可用。Preferably, inspecting the disassembled turbine disk in step (2) refers to performing fluorescent flaw detection and internal eddy current inspection on the surface of the turbine disk to ensure that the turbine disk is available.
优选的，步骤(4)中进行叶片与叶片安装槽之间的间隙匹配，确保叶片与叶片安装槽之间间隙合适，所述间隙尺寸要求叶片安装到涡轮盘上后周向活动间隙不超过1毫米。Preferably, in step (4), the gap between the blade and the blade installation groove is matched to ensure that the gap between the blade and the blade installation groove is appropriate, and the size of the gap requires that the circumferential movable clearance of the blade after being installed on the turbine disk does not exceed 1 mm.
优选的，步骤(5)中将标记的叶片依次安装到对应的涡轮盘的叶片安装槽内时先不安装锁片，使用外圆磨床对涡轮叶片的外径进行磨削，实际达到规定值以上并预留少部分余量的范围是：使涡轮组件的最终外径在178.65～178.70毫米范围内。Preferably, in step (5), when the marked blades are sequentially installed into the blade installation grooves of the corresponding turbine disks, the locking pieces are not installed first, and the outer diameter of the turbine blades is ground by a cylindrical grinder, and the outer diameter of the turbine blades actually reaches the specified value or more. The range with a small margin reserved is: the final outer diameter of the turbine assembly is in the range of 178.65-178.70 mm.
优选的，步骤(6)中使涡轮组件不平衡量达到10gmm的规定范围内。Preferably, in step (6), the unbalanced amount of the turbine assembly is within a specified range of 10 gmm.
优选的，步骤(7)中将涡轮叶片的外径磨削到涡轮组件的最终外径在177.95～178.00毫米的规定尺寸内。Preferably, in step (7), the outer diameter of the turbine blade is ground to a specified size that the final outer diameter of the turbine assembly is 177.95-178.00 mm.
优选的，步骤(8)中通过弯折锁片的方式将叶片固定叶片在涡轮盘上，并确保锁片弯折部分紧贴涡轮盘表面。Preferably, in step (8), the blade is fixed on the turbine disk by bending the locking piece, and it is ensured that the bent part of the locking piece is close to the surface of the turbine disk.
优选的，步骤(9)中不平衡量在10gmm的范围内。Preferably, the unbalanced amount in step (9) is in the range of 10 gmm.
与现有技术相比，本发明具有以下优点：Compared with the prior art, the present invention has the following advantages:
(1)本发明流程具有极强的普适性，可适用于所有的涡轮平衡类工作；(1) The process of the present invention has strong universality and can be applied to all turbine balance work;
(2)本发明流程完善，科学有效，节约大量人工成本和时间成本；(2) the process of the present invention is perfect, scientific and effective, and saves a lot of labor costs and time costs;
(3)本发明增加了叶片与涡轮盘间隙配合，通过初磨外圆-平衡-终磨外圆的形式，避免了传统方式磨削后发现组件不平衡情况的发生，避免了由于不平衡导致的叶片拆换，可提高涡轮组件质量与修理的一次成品率；(3) The present invention increases the clearance fit between the blade and the turbine disk, and avoids the occurrence of unbalanced components after grinding in the traditional way, and avoids the occurrence of unbalanced It can improve the quality of turbine components and the one-time yield of repairs;
(4)本发明流程在APS3200APU一二级涡轮叶片更换过程中，避免了反复更换叶片进行平衡尝试所消耗的大量时间，并且减少了返工造成的航材耗费。(4) The process of the present invention in the process of replacing the first and second stage turbine blades of the APS3200APU, avoids a lot of time consumed by repeatedly replacing the blades for balancing attempts, and reduces the cost of aviation materials caused by rework.
附图说明Description of drawings
图1是背景技术中图涡轮结构组成示意图；Fig. 1 is the schematic diagram of turbine structure composition in the background technology;
图2是本发明具体实施方式中涡轮叶片更换方法的流程示意图。FIG. 2 is a schematic flowchart of a turbine blade replacement method in a specific embodiment of the present invention.
具体实施方式Detailed ways
实施例1Example 1
如图2所示，本实施例提供的涡轮叶片的更换方法，包括以下步骤：As shown in FIG. 2 , the method for replacing turbine blades provided in this embodiment includes the following steps:
(1)拆卸分解：通过拆卸涡轮锁片的方式，拆下涡轮上的全部叶片与锁片；(1) Disassembly and decomposition: Remove all the blades and locking plates on the turbine by disassembling the turbine locking plate;
具体操作过程推荐是：展开锁片拆卸叶片，定位涡轮盘在涡轮支撑(一种用于支撑涡轮盘的常规支撑工件，通用工具，只是为涡轮提供支撑)上，定位涡轮盘时，叶片后缘向上，涡轮盘必须与涡轮支撑稳定接触。用冲子(通用工具，头部为扁平形，类似螺丝刀，一般是黄铜冲子或铝冲子)轻轻将锁片敲打至完全从涡轮表面分开且与叶片安装槽对成一条直线，用冲子从后端拆下叶片与锁片，通常叶片磨损发生在所有叶片上，因此通常需要更换所有的叶片。The specific operation process is recommended as follows: unfold the locking plate to remove the blade, position the turbine disk on the turbine support (a conventional support workpiece used to support the turbine disk, a general tool, just to provide support for the turbine), when positioning the turbine disk, the trailing edge of the blade Up, the turbine disk must be in stable contact with the turbine support. Use a punch (general purpose tool with a flat head, similar to a screwdriver, usually a brass punch or an aluminum punch) to lightly tap the cleat until it is completely separated from the turbine surface and aligned with the blade mounting groove. The punch removes the vanes and cleats from the rear, and usually vane wear occurs on all vanes, so all vanes usually need to be replaced.
(2)清洗检查：将拆下的涡轮盘进行清洗与检查，确保涡轮盘可用；(2) Cleaning and inspection: Clean and inspect the removed turbine disk to ensure that the turbine disk is available;
具体操作过程推荐是：对拆下的涡轮盘表面进行荧光探伤检查和内部涡流检查，确保涡轮盘可用。The specific operation process is recommended as follows: perform fluorescent inspection and internal eddy current inspection on the surface of the removed turbine disk to ensure that the turbine disk is usable.
(3)盘体平衡：利用平衡机对可用的涡轮盘进行盘体平衡，记录涡轮盘的不平衡量；(3) Disc balance: use a balancing machine to balance the available turbine discs, and record the unbalance of the turbine discs;
为了保证涡轮的运转平稳，涡轮在装机前通常需要进行平衡工作，并记录涡轮盘的不平衡量及角度(平衡机在测量出不平衡量的同时还会输出不平衡角度)。涡轮的平衡通常是指将安装到相应的工装(通用工具，用于支撑涡轮)上，通过平衡机(常规平衡机如SCHENCK HM1BU型号的平衡机)，利用平衡机电机及皮带带转涡轮旋转(通常1000转/min)，由于在平衡涡轮时带有工装，为了去除工装本身的不平衡量，通常采用将工装相对安装位置旋转180度的做法去除工装的不平衡量，此种方法为平衡工作的基础工作，俗称补偿，其中“0”位标记与贴在工装上的光标成180°，磅紧工装螺帽力矩值为310in.lb。In order to ensure the smooth operation of the turbine, the turbine usually needs to be balanced before being installed, and the unbalance and angle of the turbine disk are recorded (the balance machine will output the unbalance angle while measuring the unbalance). The balance of the turbine usually means that it will be installed on the corresponding tool (general tool, used to support the turbine), through the balancer (conventional balancer such as the balancer of the SCHENCK HM1BU model), using the balancer motor and belt to rotate the turbine to rotate ( Usually 1000 rpm), due to the tooling when balancing the turbine, in order to remove the unbalance of the tooling itself, the unbalance of the tooling is usually removed by rotating the tooling 180 degrees relative to the installation position. This method is the basis for balancing work. Work, commonly known as compensation, where the "0" bit mark is 180° to the cursor attached to the tooling, and the torque value of the tooling nut is 310in.lb.
其中涡轮盘必须确保定中点、涡轮盘的接触面和平衡工装表面的光洁度。Among them, the turbine disk must ensure the center point, the contact surface of the turbine disk and the smoothness of the balance tool surface.
(4)叶片匹配：对涡轮盘上的叶片安装槽进行标记，随机选取全新叶片，进行叶片与叶片安装槽之间的间隙匹配，选择出一套合适的叶片，并在叶片上记录与其合适的叶片安装槽的标记；(4) Blade matching: mark the blade installation groove on the turbine disk, randomly select a new blade, match the gap between the blade and the blade installation groove, select a suitable set of blades, and record the appropriate blade on the blade The marking of the blade mounting slot;
具体操作过程推荐是：将平衡后的涡轮盘上的叶片安装槽进行编号，随机选取全新的涡轮叶片，将其与涡轮盘上的叶片安装槽依次进行匹配，叶片安装槽与叶片的间隙不能太松也不能太紧，要求叶片安装到涡轮盘上后周向活动间隙不超过1毫米，并在叶片上标注与之配合的叶片安装槽的序号。The specific operation process is recommended as follows: number the blade installation grooves on the balanced turbine disk, randomly select new turbine blades, and match them with the blade installation grooves on the turbine disk in turn. The gap between the blade installation groove and the blade should not be too large. The looseness should not be too tight. It is required that the circumferential movement clearance of the blade should not exceed 1 mm after being installed on the turbine disk, and the serial number of the blade installation slot to be matched with it should be marked on the blade.
(5)初磨外圆：将标记的叶片依次安装到对应的涡轮盘叶片安装槽内，使用外圆磨床对涡轮叶片的外径进行磨削，实际达到规定值以上并预留少部分余量；(5) Initial grinding of the outer circle: Install the marked blades into the corresponding turbine disk blade installation grooves in sequence, and use an outer cylindrical grinder to grind the outer diameter of the turbine blades, and the actual value is above the specified value and a small margin is reserved. ;
具体操作过程推荐是：按照叶片与叶片安装槽的对应关系，将叶片依次安装到涡轮盘的叶片安装槽内。注意，此时不要安装锁片。利用外圆磨床将叶片的长度磨削，使涡轮组件的最终外径在178.65～178.70毫米范围内。The specific operation process is recommended as follows: according to the corresponding relationship between the blades and the blade installation grooves, the blades are sequentially installed into the blade installation grooves of the turbine disk. Note, do not install cleats at this time. Grind the length of the blades using a cylindrical grinder so that the final outer diameter of the turbine assembly is in the range of 178.65 to 178.70 mm.
(6)组件平衡：确保磨削后的涡轮盘与叶片对应关系不变，将涡轮组件放在平衡机上，通过重新调整叶片在叶片安装槽上的位置，使涡轮组件不平衡量达到规定范围内；(6) Component balance: ensure that the corresponding relationship between the ground turbine disk and the blade remains unchanged, place the turbine component on the balancer, and readjust the position of the blade on the blade installation slot to make the turbine component unbalance within the specified range;
具体操作过程推荐是：确保磨削后的涡轮盘与叶片对应关系不变，将涡轮组件放在平衡机上，通过调换叶片相对位置的方式，使涡轮组件不平衡量达到规定范围内。其中调换叶片相对位置的方式具体可以通过人工调整，将叶片从叶片安装槽的其中一个位置调整到其它合适位置，从而可以使涡轮组件不平衡量达到10gmm的规定范围内，也可以采用设计一款常规的计算软件(将获得数据录入Excel)，将称重叶片在计算软件中输入每个叶片的重量及涡轮盘不平衡量，通过软件的计算，规划出涡轮组件理论不平衡量最小时叶片与涡轮盘的相对位置，并通过调换叶片位置方式将组件不平衡量调整至10gmm的规定要求。The specific operation process is recommended as follows: ensure that the corresponding relationship between the ground turbine disk and the blades remains unchanged, place the turbine assembly on the balancer, and change the relative position of the blades to make the turbine assembly unbalance within the specified range. The way of exchanging the relative position of the blade can be adjusted manually, and the blade can be adjusted from one position of the blade installation groove to another suitable position, so that the unbalance of the turbine assembly can reach the specified range of 10gmm, or a conventional design can be used. The calculation software (the data obtained will be entered into Excel), input the weight of each blade and the unbalance of the turbine disc into the calculation software of the weighing blade, and through the calculation of the software, plan the relationship between the blade and the turbine disc when the theoretical unbalance of the turbine component is the smallest. relative position, and adjust the unbalance of the component to the specified requirement of 10gmm by exchanging the blade position.
推荐的，安装叶片的顺序为涡轮盘从后向前看顺时针方向。The recommended order for installing the blades is clockwise from the rear to the front of the turbine disk.
(7)终磨外圆：保持涡轮组件平衡后涡轮盘与叶片位置(此处叶片位置为步骤(6)中重新调整后的叶片位置关系)不变，再次将涡轮组件安装到外圆磨床上，将涡轮叶片的外径磨削到涡轮组件的最终外径在177.95～178.00毫米的规定尺寸内。(7) Final grinding of the outer circle: After keeping the balance of the turbine assembly, the position of the turbine disk and the blade (here the blade position is the positional relationship of the blade after readjustment in step (6)) remains unchanged, and the turbine assembly is installed on the outer cylindrical grinder again. , grind the outer diameter of the turbine blade to the specified size of the final outer diameter of the turbine assembly of 177.95-178.00 mm.
(8)锁片安装：依次在涡轮盘与叶片之间安装全新锁片，将叶片通过锁片固定在涡轮盘上；(8) Locking piece installation: Install a new locking piece between the turbine disk and the blade in turn, and fix the blade on the turbine disk through the locking piece;
具体操作过程推荐是：保持此时叶片与涡轮盘位置不变，将涡轮组件放置在支撑上，依次在每片叶片与涡轮盘之间安装锁片，通过弯折锁片的方式，利用铝冲子或铜冲子对所有锁片的两端进行弯折，将涡轮叶片固定在涡轮盘上，确保锁片弯折部分紧贴涡轮盘表面。The specific operation process is recommended as follows: keep the position of the blade and the turbine disk unchanged at this time, place the turbine assembly on the support, install the locking piece between each blade and the turbine disk in turn, and use the aluminum punch by bending the locking piece. Bend the two ends of all the locking pieces with a steel or copper punch, fix the turbine blades on the turbine disc, and ensure that the bent part of the locking pieces is close to the surface of the turbine disc.
在安装锁片并弯曲成型后，检查锁片有无裂纹。After the cleat is installed and bent into shape, inspect the cleat for cracks.
(9)最终检验：将组装好的涡轮组件放在平衡机上，对组件进行不平衡量验证，确保涡轮组件的不平衡量在10gmm规定数值内。(9) Final inspection: Put the assembled turbine assembly on the balancing machine, and verify the unbalance of the assembly to ensure that the unbalance of the turbine assembly is within the specified value of 10gmm.
还可以进一步检查叶片位置、轴向间隙等，叶片后缘盘表面到叶片表面距离要在0～0.38mm、叶片轴向活动间隙要在0～0.05mm为佳。It is also possible to further check the blade position, axial clearance, etc. The distance from the blade trailing edge disc surface to the blade surface should be 0-0.38mm, and the axial movable clearance of the blade should be 0-0.05mm.
本申请中的涡轮叶片更换方法，通过拆卸分解、清洗检查、盘体平衡、叶片匹配、初磨外圆、组件平衡、终磨外圆、锁片安装、最终检验的方式，保证安装合适的叶片，综合利用涡轮盘的不平衡量及每个叶片的质量，模拟平衡后，根据这些数据匹配出合理的叶片安装方案，可提高平衡效率，最终完成叶片更换工作。与现有方法中单纯依赖人工经验的方式更换叶片相比，现有方法中，一方面，由于叶片较多，平衡工艺时间长，严重影响平衡效率，另一方面，反复拆卸叶片进行平衡会对涡轮盘及叶片造成磨损，损坏浪费航材。因此，本发明方法通过选择叶片的配合间隙范围、质量范围、模拟平衡及适当的平衡验证，使流程改进后的涡轮修理效率与质量得到显著提高。该方法的实施显著减少了返工造成的航材耗费，节约维修成本，显著提高了涡轮修理的一次成品率，减少维修周期。The turbine blade replacement method in this application ensures that the appropriate blades are installed through the methods of disassembly and decomposition, cleaning and inspection, disc balance, blade matching, initial grinding outer circle, component balance, final grinding outer circle, locking piece installation, and final inspection. , comprehensively utilize the unbalance of the turbine disk and the quality of each blade. After simulating the balance, a reasonable blade installation scheme is matched according to these data, which can improve the balance efficiency and finally complete the blade replacement work. Compared with the existing method, which relies solely on manual experience to replace the blades, in the existing method, on the one hand, due to the large number of blades, the balancing process takes a long time, which seriously affects the balancing efficiency. Turbine discs and blades cause wear, damage and waste of aviation materials. Therefore, the method of the present invention significantly improves the repair efficiency and quality of the turbine after the process improvement by selecting the fit clearance range, mass range, simulated balance and proper balance verification of the blades. The implementation of the method significantly reduces the consumption of aviation materials caused by rework, saves maintenance costs, significantly improves the one-time yield of turbine repair, and reduces maintenance cycles.
对所公开的实施例的上述说明，使本领域专业技术人员能够实现或使用本发明。对这些实施例的多种修改对本领域的专业技术人员来说将是显而易见的，本文中所定义的一般原理可以在不脱离本发明的精神或范围的情况下，在其它实施例中实现。因此，本发明将不会被限制于本文所示的这些实施例，而是要符合与本文所公开的原理和新颖特点相一致的最宽的范围。The above description of the disclosed embodiments enables 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 implemented in 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.
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