CN111745222A

CN111745222A - Reaming cutter and reaming method for nine-stage grated disc pressure-equalizing hole of aero-engine

Info

Publication number: CN111745222A
Application number: CN202010651238.6A
Authority: CN
Inventors: 高明; 谢东; 王建飞; 张容珲; 曾书林; 张彦博; 黄向荣; 方洲; 杨海东
Original assignee: No 5719 Factory of PLA
Current assignee: No 5719 Factory of PLA
Priority date: 2020-07-08
Filing date: 2020-07-08
Publication date: 2020-10-09

Abstract

The invention relates to the field of cutter equipment, in particular to a reaming cutter and a reaming method for nine-stage slotted tooth disc pressure-sharing holes of an aeroengine, which can improve the surface quality of the reamed pressure-sharing holes and effectively prevent eddy current flaw detection alarm after reaming. The technical scheme adopted by the invention for solving the technical problems is as follows: a reaming cutter for nine-stage slotted comb disc pressure-sharing holes of an aeroengine comprises a blade part and a handle part, wherein the blade of the blade part is a left-handed spiral blade, and the blade part is made of H10F hard alloy. According to the invention, through the targeted improvement on the cutter, the surface quality of the reamed equalizing hole is greatly improved, so that the eddy current flaw detection alarm after reaming is effectively avoided, the rejection rate in the repair process of the nine-grade slotted tooth plate is also effectively reduced, the quality of the reamed equalizing hole of the high-fault workpiece, namely the nine-grade slotted tooth plate, is improved, and the repair quality is more stable and controllable.

Description

Reaming cutter and reaming method for nine-stage grated disc pressure-equalizing hole of aero-engine

Technical Field

The invention relates to the field of cutter equipment, in particular to a reaming cutter and a reaming method for a nine-stage grated disc pressure-equalizing hole of an aero-engine.

Background

The nine-stage grate disc of the aero-engine is a key part of the aero-engine, the working environment is severe, the stress condition is complex, the fault damage is serious, and particularly, the hole edge crack fault of the pressure equalizing hole is the most prominent. According to the requirement of repair technical documents, when the service life of the engine is longer than 1000 hours after the engine is repaired, in order to remove a stress concentration layer at the edge of the pressure equalizing hole and a material tissue defect layer formed after the engine works, the nine-stage labyrinth plate 32 pressure equalizing holes are subjected to hole expanding and hole edge chamfering (spot facing). However, the problems of high eddy current flaw detection signal value and even alarm after reaming and reaming of the pressure equalizing hole exist for a long time, the product quality safety is greatly threatened, and the nine-stage slotted tooth disc is occasionally scrapped.

Disclosure of Invention

The invention aims to solve the technical problem of providing a reaming cutter and a reaming method for nine-stage slotted tooth disc pressure-sharing holes of an aeroengine, which can improve the surface quality of the pressure-sharing holes after reaming and further effectively prevent eddy current flaw detection alarm after reaming.

The technical scheme adopted by the invention for solving the technical problems is as follows: a reaming cutter for nine-stage slotted comb disc pressure-sharing holes of an aeroengine comprises a blade part and a handle part, wherein the blade of the blade part is a left-handed spiral blade, and the blade part is made of H10F hard alloy.

Further, the number of cutting edges of the blade portion was 6.

Further, the length of the straight edge part of the knife edge part is 30 mm.

Furthermore, the cutting edge feed chamfer is two sections of chamfers.

Further, the tool shank portion is of an integral tool shank structure.

Further, the cross section of the tail section of the handle part of the tool handle part is rectangular.

Further, in the reaming method of the reaming tool for the uniform pressure hole of the nine-stage fluted disc of the aeroengine, when the hole with the phi 5.0mm is reamed, the hole with the phi 5.0mm is reamed to the phi 5.1mm from the phi 5.0mm, and then the hole with the phi 5.1mm is reamed to the phi 5.2mm from the phi 5.1 mm.

The invention has the beneficial effects that: the existing cutter often has the following problems when in use: before repairing the nine-stage grated disk, no abnormity occurs in fluorescence and eddy current flaw detection, but after using the existing cutter to carry out pressure equalizing hole reaming, spot facing and polishing repairing, the eddy current flaw detection signal value is high, but the fluorescence flaw detection has no abnormity problem, the problem greatly threatens the product quality safety, and occasionally the nine-stage grated disk is scrapped. According to the invention, through the targeted improvement on the cutter, the surface quality of the reamed equalizing hole is greatly improved, so that the eddy current flaw detection alarm after reaming is effectively avoided, the rejection rate in the repair process of the nine-grade slotted tooth plate is also effectively reduced, the quality of the reamed equalizing hole of the high-fault workpiece, namely the nine-grade slotted tooth plate, is improved, and the repair quality is more stable and controllable.

Drawings

Fig. 1 is a schematic structural view of the present invention.

Fig. 2 is a sectional view a-a of fig. 1.

Fig. 3 is a sectional view B-B of fig. 1.

Fig. 4 is a cross-sectional view C-C of fig. 1.

Labeled as: the tool shank part 1, the blade part 2, the cutting edge 21, the shank part end section 3 and the shank part end section cross section 31.

Detailed Description

The invention is further described below with reference to the accompanying drawings.

The reaming tool for the nine-stage grated disc pressure equalizing hole of the aero-engine as shown in fig. 1, fig. 2, fig. 3 and fig. 4 comprises a blade part 2 and a tool shank part 1, wherein the cutting edge of the blade part 2 is a left-handed spiral cutting edge, and the blade part 2 is made of H10F hard alloy.

The invention aims at the problems that after the existing cutter is subjected to pressure equalizing reaming, spot facing and polishing repair, the eddy current flaw detection signal value is high, but the fluorescence flaw detection is not abnormal, and the cutter is pertinently improved. The improved cutter successfully solves the problems that no abnormality exists before the nine-stage perforated disk is repaired and the eddy current flaw detection signal value is high and is stopped or scrapped after the nine-stage perforated disk is repaired, thereby effectively reducing the scrappage rate in the repairing process of the nine-stage perforated disk, improving the quality of the reaming of the high-pressure workpiece equalizing hole of the nine-stage perforated disk, and ensuring that the repairing quality is more stable and controllable. The cutting edge of the blade part 2 is a left-handed spiral cutting edge, so that the cutting material can be discharged conveniently, and the cutting material is prevented from scratching the inner wall. The material of the blade part 2 is H10F hard alloy by improving the cutting performance, so that the blade is more suitable for cutting high-temperature alloy and powder alloy.

In order to improve the cutting stability and the surface quality, the following scheme is preferred: the number of the cutting edges 21 of the blade part 2 is 6. As shown in fig. 3, the 6-edge cutting edge 21 can make the cutting more uniform and stable, and ensure the cutting quality. In addition, in order to realize the longer distance feeding, the straight edge of the rear section can be used for further slightly finishing the cylindrical surface so as to achieve the purpose of improving the surface quality, and the length of the straight edge part of the cutting edge part 2 can be selected to be 30 mm. In order to enable the cutting amount to be more smoothly transited, the cutting edge feed chamfer is preferably two sections of chamfers. In order to improve the precision and stability of the tool, the tool shank 1 is preferably of an integral tool shank structure, and in addition, in order to improve the stability in use, the cross section of the tool shank end section 3 of the tool shank 1 is preferably rectangular.

In addition, during actual cutting, the following optimized reaming process improvement is preferably carried out on the reaming groups, namely: when a hole with the phi of 5.0mm is reamed, the hole is reamed from the phi of 5.0mm to the phi of 5.1mm, and then is reamed from the phi of 5.1mm to the phi of 5.2 mm. The overall cutting quality is improved by reducing the amount of one cutting.

According to the invention, through the targeted improvement on the cutter, the surface quality of the reamed hole of the pressure equalizing hole is greatly improved, so that the eddy current flaw detection alarm after reaming is effectively avoided, the rejection rate in the repair process of the nine-grade slotted tooth disc is also effectively reduced, the quality of the reamed hole of the pressure equalizing hole of the high-fault workpiece, which is the nine-grade slotted tooth disc, is improved, the technical advantage is very obvious, and the market popularization prospect is very wide.

Claims

1. A reaming cutter that is used for nine grades of labyrinth disc pressure-sharing holes of aeroengine, its characterized in that: the utility model discloses a knife edge portion of cutting tool, including cutting edge portion (2) and handle of a knife portion (1), the blade of cutting edge portion (2) is levogyration spiral blade, and cutting edge portion (2) material is H10F carbide.

2. The reaming tool for the nine-stage grated disc pressure equalizing hole of the aircraft engine according to claim 1, characterized in that: the number of the cutting edges (21) of the blade part (2) is 6.

3. The reaming tool for the nine-stage grated disc pressure equalizing hole of the aircraft engine according to claim 1, characterized in that: the length of the straight edge part of the knife edge part (2) is 30 mm.

4. The reaming tool for the nine-stage grated disc pressure equalizing hole of the aircraft engine according to claim 1, characterized in that: the cutting edge feed chamfer is two sections of chamfers.

5. The reaming tool for the nine-stage grated disc pressure equalizing hole of the aircraft engine according to claim 1, characterized in that: the knife handle part (1) is of an integral knife handle structure.

6. The reaming tool for the nine-stage grated disc pressure equalizing hole of the aircraft engine according to claim 5, characterized in that: the cross section of the tail section (3) of the handle part of the knife handle (1) is rectangular.

7. A reaming method by using the reaming cutter for the nine-stage grated disc pressure equalizing hole of the aero-engine as set forth in claim 1, wherein: when a hole with the phi of 5.0mm is reamed, the hole is reamed from the phi of 5.0mm to the phi of 5.1mm, and then is reamed from the phi of 5.1mm to the phi of 5.2 mm.