CN110774215B - Overlock device of aero-engine circumferential sealing device and overlock method thereof - Google Patents
Overlock device of aero-engine circumferential sealing device and overlock method thereof Download PDFInfo
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- CN110774215B CN110774215B CN201911236189.3A CN201911236189A CN110774215B CN 110774215 B CN110774215 B CN 110774215B CN 201911236189 A CN201911236189 A CN 201911236189A CN 110774215 B CN110774215 B CN 110774215B
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- circumferential sealing
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- 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
- B25B27/0028—Tools for removing or installing seals
Abstract
The invention discloses an aeroengine circumference sealing device overlock and a using method thereof.A sliding ball head is adjusted at a position of a stepped groove-shaped hole of a base according to graphite compression quantity required by a sealing device, and a bolt is screwed for fixing; one side of the circumferential sealing device, which is required to be subjected to edge locking, faces upwards, the sleeve is sleeved with the sleeve with the opening of the sleeve facing downwards, the sleeve is arranged in the annular boss of the base in an overturning manner, and the opening positions correspond to each other; the wrench rod is rotated to drive the pressure plate to move downwards, so that the circumferential sealing device is extruded downwards, the edge of the shell is extruded into a corresponding lock seaming mode, and the shape and the amplitude of the lock seaming at the position 3 are the same. The scheme of this embodiment, through the removal of adjustable slip bulb radial position, and pour the cutting ferrule mounting means into to effectively guarantee to extrude the lockstitching a border form that corresponds with circumference sealing device casing edge, and the shape and the range of lockstitching a border are the same, do not have the difference, thereby effectively guaranteed the standardization and the controllability of circumference sealing device lockstitching a border.
Description
Technical Field
The invention belongs to the field of mechanical manufacturing engineering, and relates to an edge locking device of a circumferential sealing device of an aero-engine and an edge locking method thereof.
Background
The circumference sealing device is widely applied to the sealing design of a main bearing cavity of an aircraft engine, a graphite assembly is arranged in the circumference sealing device, and the circumference sealing device is limited by multipoint bending of the edge of a shell. After the aircraft engine runs for a period of time, the graphite assembly arranged in the circumferential sealing device is worn and even broken frequently, and a new graphite assembly needs to be replaced and the bending and edge locking are carried out again. The overlock mode that adopts at present often has two kinds, one is behind the fixed circumference sealing device, strikes the casing edge of bending through soft plug and carries out the overlock, one is for carrying out the lock limit of buckling a pair of casing edge one by one through stretching and lowering the mechanism, and two kinds of operating methods are all inefficient, waste time and energy, and the range of buckling of each lockstitch department of same circumference sealing device is uncontrolled to lead to the fact uncontrolled influence to circumference sealing device most crucial parameter graphite compression volume, seriously influenced engine assembly's quality and efficiency.
Disclosure of Invention
The embodiment of the invention provides an aeroengine circumferential sealing device overlock and a using method thereof, which at least solve some technical problems.
In a first aspect, an embodiment of the present invention provides an aircraft engine circumferential sealing device lockrand device, including: the device comprises a base, a gantry support, a sliding ball head, a clamping sleeve, a pressing plate, a wrench rod and a connecting bolt; wherein the content of the first and second substances,
the base comprises a rectangular platform, a circular-ring-shaped boss is arranged at the center of the rectangular platform, 3 openings are formed in the circumferential direction of the circular-ring-shaped boss, and a stepped slot-shaped hole with a large upper part and a small lower part is formed in the position, corresponding to each opening, of the rectangular platform;
threaded through holes are formed in the mounting edges at the lower ends of the two sides of the gantry support, the gantry support is fixed in the threaded holes in the two sides of the base through bolt connection, a threaded hole is formed in the center of the upper end of the gantry support, and the threaded section of the wrench rod is screwed into the threaded hole in the upper end of the gantry support to form a threaded pair;
a cylindrical boss is arranged at the center of the pressure plate, a spherical groove is formed in the cylindrical boss, the spherical groove is matched with a ball head at the end part of the wrench rod to form a rotating pair, limiting parts are symmetrically formed in two sides of the pressure plate, the limiting parts extend into vertical supports on two sides of the gantry support, and the two sides of the gantry support are vertically and directly used for limiting the circumferential rotation of the pressure plate in the downward moving process;
the cutting sleeve is an annular blocking cover, 3 notches are uniformly formed in the circumferential direction of the cutting sleeve, and the shape and position of the notch in the cutting sleeve are the same as those of an opening of an annular boss on the base;
the sliding ball head is a cylindrical sliding block, the upper end of the cylindrical sliding block is a spherical surface, a cylinder at the lower end of the cylindrical sliding block extends into the stepped groove-shaped hole of the base, and the sliding ball head extrudes the circumferential sealing device of the engine when moving along the radial direction of the stepped groove-shaped hole.
Optionally, the wrench rod comprises a rotating rod and an application rod, a threaded hole is formed in the middle of the application rod, and one end of the rotating rod is in steering threaded connection with the threaded hole of the application rod;
the other end of dwang is the bulb, being close to of dwang the body of rod of bulb is the screw thread section, the screw thread section of dwang is selected into behind the screw hole butt of gantry support arrive on the spherical recess above the clamp plate.
Optionally, rectangular limiting holes are symmetrically formed in two sides of the pressing plate, and the vertical supports on two sides of the gantry support are respectively clamped in the rectangular limiting holes to limit circumferential rotation of the pressing plate.
Optionally, a threaded hole is formed in the bottom end of the sliding ball head, a column body of the sliding ball head extends into the stepped groove-shaped hole of the base, and a bolt extends into the threaded hole of the sliding ball head through the bottom surface of the base to realize radial movement of the east China ball head.
In a second aspect, an embodiment of the present invention further provides a use method of an aircraft engine circumferential sealing device serging device, which is applied to the aircraft engine circumferential sealing device serging device according to any one of the first aspect, and is used for serging an engine circumferential sealing device; the method comprises the following steps:
firstly, adjusting the position of a sliding ball head in a stepped groove-shaped hole of a base according to the graphite compression amount required by the sealing device, and screwing a bolt for fixing;
one surface of the circumferential sealing device, which is required to be subjected to edge locking, faces upwards, the sleeve chuck is sleeved with the circumferential sealing device with the opening facing downwards, and the sleeve chuck is arranged in the annular boss of the base in an overturning manner, so that the opening positions correspond to each other;
and rotating the wrench rod to drive the pressure plate to move downwards, so that the circumferential sealing device is extruded downwards, the edge of the shell is extruded into a corresponding lock seaming mode, and the shape and the amplitude of the lock seaming at the position 3 are the same.
According to the overlock device of the circumferential sealing device of the aero-engine and the using method thereof, the position of the sliding ball head in the stepped groove-shaped hole of the base is adjusted according to the graphite compression amount required by the sealing device, and the sliding ball head is screwed up and fixed; one surface of the circumferential sealing device, which is required to be subjected to edge locking, faces upwards, the sleeve chuck is sleeved with the circumferential sealing device with the opening facing downwards, and the sleeve chuck is arranged in the annular boss of the base in an overturning manner, so that the opening positions correspond to each other; and rotating the wrench rod to drive the pressure plate to move downwards, so that the circumferential sealing device is extruded downwards, the edge of the shell is extruded into a corresponding lock seaming mode, and the shape and the amplitude of the lock seaming at the position 3 are the same. The scheme of this embodiment, through the removal of adjustable slip bulb radial position, and pour the cutting ferrule mounting means into to effectively guarantee to extrude the lockstitching a border form that corresponds with circumference sealing device casing edge, and the shape and the range of lockstitching a border are the same, do not have the difference, thereby effectively guaranteed the standardization and the controllability of circumference sealing device lockstitching a border.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft engine circumferential sealing device serging device provided by an embodiment of the invention;
FIG. 2 is a schematic diagram of an operation of an aircraft engine circumferential sealing device serger provided in an embodiment of the invention;
fig. 3 is a schematic structural diagram of a base of an edge locker of a circumferential sealing device of an aircraft engine according to an embodiment of the invention.
Summary of reference numerals: a base 1; a gantry support 2; a sliding ball head 3; a ferrule 4; a pressing plate 5; a trigger lever 6.
Detailed Description
The present invention is described in further detail below.
Referring to fig. 1, a schematic structural diagram of an aircraft engine circumferential sealing device serger provided in an embodiment of the present invention is shown. As shown in fig. 1 to 3, the lockstitch device of the aeroengine circumferential sealing device comprises:
the device comprises a base 1, a gantry support 2, a sliding ball head 3, a clamping sleeve 4, a pressing plate 5, a wrench rod 6 and a connecting bolt; wherein the content of the first and second substances,
the base 1 comprises a rectangular platform, a circular-ring-shaped boss is arranged at the center of the rectangular platform, 3 openings are formed in the circumferential direction of the circular-ring-shaped boss, and a stepped slot-shaped hole with a large upper part and a small lower part is formed in the rectangular platform corresponding to each opening;
threaded through holes are formed in the mounting edges at the lower ends of the two sides of the gantry support 2, the gantry support 2 is fixed in the threaded holes in the two sides of the base 1 through bolt connection, a threaded hole is formed in the center of the upper end of the gantry support 2, and the threaded section of the wrench rod 6 is screwed into the threaded hole in the upper end of the gantry support 2 to form a threaded pair;
a cylindrical boss is arranged at the center of the pressing plate 5, a spherical groove is formed in the cylindrical boss, the spherical groove is matched with a ball head at the end part of the wrench rod 6 to form a rotating pair, limiting parts are symmetrically formed on two sides of the pressing plate 5, the limiting parts extend into vertical supports on two sides of the gantry support 2, and the vertical parts on two sides of the gantry support 2 are directly used for limiting circumferential rotation in the downward moving process of the pressing plate 5;
the cutting sleeve 4 is an annular blocking cover, 3 notches are uniformly formed in the circumferential direction of the cutting sleeve 4, and the shape and position of the notch in the cutting sleeve 4 are the same as those of an opening of an annular boss on the base 1;
the sliding ball head 3 is a cylindrical sliding block, the upper end of the cylindrical sliding block is a spherical surface, a cylinder at the lower end of the cylindrical sliding block extends into the stepped groove-shaped hole of the base 1, and the sliding ball head 3 extrudes the circumferential sealing device of the engine when moving along the radial direction of the stepped groove-shaped hole.
Optionally, the wrench rod 6 includes a rotating rod and an applying rod, a threaded hole is formed in the middle of the applying rod, and one end of the rotating rod is in steering threaded connection with the threaded hole of the applying rod;
the other end of the rotating rod is a ball head, the rod body of the rotating rod close to the ball head is a threaded section, and the threaded section of the rotating rod is abutted to the spherical groove on the pressing plate 5 after being selected into the threaded hole in the upper end of the gantry support 2.
Optionally, rectangular limiting holes are symmetrically formed in two sides of the pressing plate 5, and the vertical supports on two sides of the gantry support 2 are respectively clamped in the rectangular limiting holes to limit circumferential rotation of the pressing plate 5.
Optionally, a threaded hole is formed in the bottom end of the sliding ball head 3, a column of the sliding ball head 3 extends into the stepped groove-shaped hole of the base 1, and a bolt extends into the threaded hole of the sliding ball head 3 through the bottom surface of the base 1 to realize radial movement of the east China ball head.
In addition, the embodiment of the invention also provides a using method of the lockrand device of the circumferential sealing device of the aero-engine, which is applied to the lockrand device of the circumferential sealing device of the aero-engine and is used for lockrand the circumferential sealing device of the aero-engine; the method comprises the following steps:
firstly, adjusting the position of a sliding ball head 3 in a stepped groove-shaped hole of a base 1 according to the graphite compression amount required by the sealing device, and screwing a bolt for fixing;
one side of the circumferential sealing device, which is required to be subjected to edge locking, faces upwards, the cutting sleeve 4 is sleeved into the circumferential sealing device with an opening facing downwards, and the cutting sleeve is overturned and arranged in the annular boss of the base 1, so that the opening positions correspond to each other;
turning the trigger lever 6 causes the pressure plate 5 to move downwards, thereby squeezing the circumferential sealing means downwards, squeezing the edge of the housing out of the corresponding lockstitching pattern, and the shape and amplitude of the lockstitching at 3 is the same.
In specific implementation, as shown in fig. 1 to 3, when the circumferential sealing device is subjected to overlocking, the position of the sliding ball 3 at the position 3 in the stepped slot-shaped hole of the base 1 is adjusted according to the required graphite compression amount, and the bolt is tightened for fixing; then with the required one side of lockstitching a border of circumference sealing device up, embolia circumference sealing device with cutting ferrule 4 opening down, then the upset is packed into in the ring type boss of base 1 to the open position corresponds, rotate wrench lever 6 and impel clamp plate 5 downstream, thereby extrude circumference sealing device downwards, extrude the casing edge corresponding lockstitching a border form, and 3 shapes and the range of lockstitching a border the same, do not have the difference, thereby effectively guaranteed the standardization and the controllability of circumference sealing device lockstitching a border.
According to the overlock device of the circumferential sealing device of the aero-engine and the using method thereof, the position of the sliding ball head in the stepped groove-shaped hole of the base is adjusted according to the graphite compression amount required by the sealing device, and the sliding ball head is screwed up and fixed; one surface of the circumferential sealing device, which is required to be subjected to edge locking, faces upwards, the sleeve chuck is sleeved with the circumferential sealing device with the opening facing downwards, and the sleeve chuck is arranged in the annular boss of the base in an overturning manner, so that the opening positions correspond to each other; and rotating the wrench rod to drive the pressure plate to move downwards, so that the circumferential sealing device is extruded downwards, the edge of the shell is extruded into a corresponding lock seaming mode, and the shape and the amplitude of the lock seaming at the position 3 are the same. The scheme of this embodiment, through the removal of adjustable slip bulb radial position, and pour the cutting ferrule mounting means into to effectively guarantee to extrude the lockstitching a border form that corresponds with circumference sealing device casing edge, and the shape and the range of lockstitching a border are the same, do not have the difference, thereby effectively guaranteed the standardization and the controllability of circumference sealing device lockstitching a border.
The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present disclosure, and all the changes or substitutions should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.
Claims (5)
1. An aeroengine circumference sealing device overlock characterized by comprising: the device comprises a base, a gantry support, a sliding ball head, a clamping sleeve, a pressing plate, a wrench rod and a connecting bolt; wherein the content of the first and second substances,
the base comprises a rectangular platform, a circular-ring-shaped boss is arranged at the center of the rectangular platform, 3 openings are formed in the circumferential direction of the circular-ring-shaped boss, and a stepped slot-shaped hole with a large upper part and a small lower part is formed in the position, corresponding to each opening, of the rectangular platform;
threaded through holes are formed in the mounting edges at the lower ends of the two sides of the gantry support, the gantry support is fixed in the threaded holes in the two sides of the base through bolt connection, a threaded hole is formed in the center of the upper end of the gantry support, and the threaded section of the wrench rod is screwed into the threaded hole in the upper end of the gantry support to form a threaded pair;
a cylindrical boss is arranged at the center of the pressure plate, a spherical groove is formed in the cylindrical boss and matched with a ball head at the end part of the wrench rod to form a rotating pair, limiting parts are symmetrically formed in two sides of the pressure plate and extend into vertical supports on two sides of the gantry support, and the vertical supports on two sides of the gantry support are used for limiting circumferential rotation of the pressure plate in the downward moving process;
the cutting sleeve is an annular blocking cover, 3 notches are uniformly formed in the circumferential direction of the cutting sleeve, and the shape and position of the notch in the cutting sleeve are the same as those of an opening of an annular boss on the base;
the sliding ball head is a cylindrical sliding block, the upper end of the cylindrical sliding block is a spherical surface, a cylinder at the lower end of the cylindrical sliding block extends into the stepped groove-shaped hole of the base, and the sliding ball head extrudes the circumferential sealing device of the engine when moving along the radial direction of the stepped groove-shaped hole.
2. The serging device as claimed in claim 1, wherein the wrench rod comprises a rotation rod and an application rod, a threaded hole is formed in the middle of the application rod, and one end of the rotation rod is rotatably and threadedly connected with the threaded hole of the application rod;
the other end of the rotating rod is a ball head, the rod body of the rotating rod close to the ball head is a threaded section, and the threaded section of the rotating rod is screwed into a threaded hole in the upper end of the gantry support and then is abutted to the spherical groove in the upper surface of the pressing plate.
3. The serging device of claim 1, wherein rectangular limiting holes are symmetrically formed in two sides of the pressing plate, and the vertical supports on two sides of the gantry support are respectively clamped in the rectangular limiting holes to limit circumferential rotation of the pressing plate.
4. The serging device as claimed in claim 1, wherein a threaded hole is formed at a bottom end of the sliding ball head, a column of the sliding ball head extends into the stepped groove-shaped hole of the base, and a bolt extends into the threaded hole of the sliding ball head through a bottom surface of the base to realize radial movement of the sliding ball head.
5. The use method of the lockrand device of the circumferential sealing device of the aircraft engine is characterized by being applied to the lockrand device of the circumferential sealing device of the aircraft engine, which is used for lockrand the circumferential sealing device of the engine, according to any one of claims 1 to 4; the method comprises the following steps:
firstly, adjusting the position of a sliding ball head in a stepped groove-shaped hole of a base according to the graphite compression amount required by the sealing device, and screwing a bolt for fixing;
one surface of the circumferential sealing device, which is required to be subjected to edge locking, faces upwards, the sleeve chuck is sleeved with the circumferential sealing device with the opening facing downwards, and the sleeve chuck is arranged in the annular boss of the base in an overturning manner, so that the opening positions correspond to each other;
the wrench rod is rotated to drive the pressure plate to move downwards, so that the circumferential sealing device is extruded downwards, the edge of the shell is extruded into a corresponding lock seaming mode, and the shape and the amplitude of the lock seaming at the position 3 are the same.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911236189.3A CN110774215B (en) | 2019-12-05 | 2019-12-05 | Overlock device of aero-engine circumferential sealing device and overlock method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911236189.3A CN110774215B (en) | 2019-12-05 | 2019-12-05 | Overlock device of aero-engine circumferential sealing device and overlock method thereof |
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| Publication Number | Publication Date |
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| CN110774215A CN110774215A (en) | 2020-02-11 |
| CN110774215B true CN110774215B (en) | 2021-07-20 |
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| CN113084725B (en) * | 2021-03-15 | 2023-06-16 | 上海新力动力设备研究所 | Solid rail accuse engine spout blanking cover annular positioning device |
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| FR2270998B1 (en) * | 1973-09-24 | 1976-12-03 | France Etat | |
| US9522462B2 (en) * | 2014-11-14 | 2016-12-20 | Robert Baker | Flange gasket installation apparatus and method |
| CN206465040U (en) * | 2016-11-21 | 2017-09-05 | 闫学贵 | Combined multi-functional forcing press |
| CN208231692U (en) * | 2017-12-29 | 2018-12-14 | 中国航发中传机械有限公司 | Steady pressing device for reducer group casing inner oil seal |
| CN208323246U (en) * | 2018-06-25 | 2019-01-04 | 陕西北元化工集团股份有限公司 | A kind of vacuum pump machine envelope mounting device |
| CN208946071U (en) * | 2018-10-31 | 2019-06-07 | 重庆小康工业集团股份有限公司 | Piston component is fitted into the tooling of cylinder barrel |
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