CN113352051A - Piston type aeroengine casing joint surface repairing method - Google Patents
Piston type aeroengine casing joint surface repairing method Download PDFInfo
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- CN113352051A CN113352051A CN202110705070.7A CN202110705070A CN113352051A CN 113352051 A CN113352051 A CN 113352051A CN 202110705070 A CN202110705070 A CN 202110705070A CN 113352051 A CN113352051 A CN 113352051A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
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Abstract
The invention discloses a method for repairing a joint surface of a piston type aircraft engine casing, which comprises the following steps: firstly, respectively milling a half body side joint surface and a half body side joint surface, and completely removing micro-vibration wear structure layers on the half body side joint surface and the half body side joint surface; in the second stage, the combination is a whole casing to form a camshaft mounting hole and a crankshaft mounting hole; honing the camshaft mounting hole in the third stage; honing the crankshaft mounting hole; boring a crankshaft sealing ring mounting hole; boring an idler shaft mounting hole and reaming, manufacturing a bushing capable of being installed in the corresponding expanded idler shaft mounting hole and installing the bushing, and boring an inner hole of the bushing to a value meeting a calibration requirement according to the center distance between the idler shaft mounting hole meeting the calibration requirement and a crankshaft mounting hole; and fourthly, carrying out nondestructive testing and surface treatment on the whole casing. The repairable casing with moderate and/or severe fretting at the joint surface does not need to be sent to foreign countries for repairing, and the economical efficiency is remarkable.
Description
Technical Field
The invention relates to a method for repairing a casing joint surface of a piston type aircraft engine.
Background
The piston type aircraft engine mainly comprises a crankshaft, a camshaft, a connecting rod, a piston, a cylinder and other parts and a casing for supporting the crankshaft, the camshaft, the connecting rod, the piston, the cylinder and the like. The casing of the piston type aircraft engine is formed by horizontally and oppositely combining the first casing half body and the second casing half body by a combining surface, and not only bears the load and the vibration when the engine works, but also is a storage space of engine lubricating oil.
During the service process of the piston type aircraft engine, the working load and vibration can cause the first half case body and the second half case body to perform high-frequency dislocation mutually. After the engine casing half body I and the engine casing half body II are in service for a certain time, micro-vibration abrasion is generated on a joint surface of the engine casing half body I and the engine casing half body II respectively to form a fine pit structure, namely a micro-vibration abrasion structure layer, and the micro-vibration abrasion structure layer is further intensified along with the extension of the service time.
The fretting wear of the joint surface of the case of the piston type aero-engine (namely, the joint surface on one side of the case half body and the joint surface on two sides of the case half body) can reduce the horizontally-opposite pressure-bearing area between the case half body I and the case half body II, and the bearing capacity is weakened, so that the connecting bolt horizontally-opposite combined and connected between the case half body I and the case half body II can be loosened, and the operation safety of the piston type aero-engine is seriously affected.
The technical problem that the sliding bearings of the crankshaft and the camshaft are failed due to the fact that the gap is small is caused by the fact that the casing is deformed if the loose connecting bolt is simply screwed to the specified torque again due to looseness of the connecting bolt caused by fretting of the joint surface of the casing. In addition, the fretting wear of the joint surface of the casing inevitably causes the sealing performance at the joint surface to be reduced, even if the connecting bolt is screwed and then tightened, the sealing performance cannot be radically cured, and the lubricating oil stored in the casing leaks at the joint surface of the casing.
Therefore, once the fretting wear occurs at the joint surface of the piston type aircraft engine casing, the fretting wear needs to be repaired so as to ensure that all parts are matched according to the calibration requirement.
At present, aiming at the phenomenon of slight fretting wear at the joint surface of the casing, a repair mode of locally polishing to remove pits and coating glue on a polishing area is adopted domestically, and a better technical effect is achieved in actual maintenance operation.
Aiming at the moderate and/or severe fretting wear phenomenon at the joint surface of the casing, no effective repair method is available in China. The first one is to send the casing to abroad for repair evaluation and subsequent repair treatment, and the second one is to directly replace a new casing, both of which have the technical problem of high cost.
Disclosure of Invention
The technical purpose of the invention is as follows: aiming at the particularity and the fretting phenomenon of the piston type aeroengine casing and the defects of the existing repairing technology, a repairing method for the joint surface of the piston type aeroengine casing, which can enable the casing subjected to fretting to restore the normal service performance, is independently developed.
The technical purpose of the invention is realized by the following technical scheme, the method for repairing the joint surface of the piston type aeroengine casing is characterized in that the casing is formed by horizontally oppositely combining a casing half body I and a casing half body II, and the repairing method comprises the following four process stages:
the first step is:
milling a joint surface on one side of the half body, completely removing a micro-vibration wear structure layer on the joint surface on one side of the half body until the planeness, parallelism and surface roughness of the joint surface on one side of the half body and the distance between the joint surface and a corresponding cylinder mounting surface meet calibration requirements, and recording the milling depth in the process;
milling the joint surfaces on the two sides of the half body, completely removing the micro-vibration wear structure layers on the joint surfaces on the two sides of the half body until the planeness, parallelism and surface roughness of the joint surfaces on the two sides of the half body and the distance between the joint surfaces and the corresponding cylinder mounting surfaces meet the calibration requirement values, and recording the milling depth in the process;
the second step is a process stage:
combining the machined casing half body one and the machined casing half body into a casing whole through a connecting bolt to form a camshaft mounting hole and a crankshaft mounting hole;
the third step is a process stage:
honing the camshaft mounting hole until the aperture, roundness, coaxiality and surface roughness of the camshaft mounting hole meet the calibration requirement values;
honing the crankshaft mounting hole until the aperture, roundness, coaxiality and surface roughness of the crankshaft mounting hole meet the calibration requirement values;
boring a crankshaft seal ring mounting hole until the aperture, roundness, coaxiality and surface roughness of the crankshaft seal ring mounting hole meet the calibration requirement values;
boring and reaming an idler shaft mounting hole;
manufacturing a bushing capable of being installed in a corresponding expanded idler shaft mounting hole according to the calibration technical requirement;
installing the bushing into the corresponding mounting hole of the expanded idler shaft;
boring an inner hole of the bushing to a value meeting the calibration requirement according to the center distance between the idler shaft mounting hole and the crankshaft mounting hole meeting the calibration requirement;
the fourth step is a process stage:
-performing a non-destructive inspection;
-performing a surface treatment.
Preferably, in the first step of the process, the milling is performed in multiple times in a manner that the maximum milling depth of a single time is 0.1 mm.
As one preferable scheme, the first step process stage further comprises the following process measures:
milling a tappet body mounting surface on one side of the half body, wherein the milling depth is consistent with the milling depth of a junction surface on one side of the half body;
milling the mounting surface of the tappet body on the two sides of the half body, wherein the milling depth is consistent with the milling depth of the bonding surface on the two sides of the half body.
As one preferable scheme, the first step process stage further comprises the following process measures:
-installing an oil groove on the crankshaft at one side of the boring half body until the oil groove meets the calibration requirement;
and mounting oil grooves on the crankshafts on two sides of the boring half body until the oil grooves meet the calibration requirement.
As one preferable scheme, the first step process stage further comprises the following process measures:
a bearing bush clamping groove is arranged on a crankshaft on one side of the boring half body until the requirement value meets the calibration requirement;
and mounting bearing bush clamping grooves on crankshafts on two sides of the boring half body until the requirements for calibration are met.
Preferably, in the third process stage, the hole expansion is to expand the diameter of the idler shaft mounting hole to be larger than the diameter of the idler shaft mounting hole required by calibration.
Preferably, in the third process stage, the inner hole of the bushing before boring is smaller than the idler shaft mounting hole required by calibration.
Preferably, in the fourth process stage, the nondestructive testing is conducted on the whole casing or each half casing in a penetration testing manner.
Preferably, in the fourth process stage, the surface treatment is performed by anodizing or coating the surface of the whole casing or each casing half.
The beneficial technical effects of the invention are as follows: the modification method aims at the particularity and the micro-vibration abrasion phenomenon of the piston type aeroengine casing, and is used for milling the joint surface of the casing, effectively removing the micro-vibration abrasion structure layer at the joint surface of the casing and recovering the bearing capacity and the sealing performance at the joint surface of the casing; by the corresponding honing and boring treatment of each hole on the casing, the technical problem of cooperative matching among parts caused by the structural size change of the casing due to the removal of the micro-vibration wear structure layer is effectively solved, and the normal service performance of the casing is recovered.
Specifically, for the casing which has fretting at the joint surface and can be repaired, the repair method has the following beneficial technical effects:
1. the milling treatment of the joint surface of the casing can ensure that the distance between the joint surface of the casing and the corresponding cylinder mounting surface meets the minimum value of the calibration requirement, and has repair value; the flatness, parallelism and surface roughness of the joint surface of the casing can reach the calibration required value of a new casing, so that the finally obtained joint surface of the casing recovers the bearing capacity and the sealing performance;
in addition, although the milling treatment of the joint surface of the casing can influence the volume of the cylinder due to the fact that the distance between the crankshaft rotation center and the top of the cylinder is reduced, the influence can be effectively controlled according to the technical requirement of maximum depth milling of the joint surface of the casing, and the volume of the cylinder of the piston type aero-engine is originally large, so that the influence of the working volume of the cylinder caused by the milling treatment of the joint surface of the casing is very little, and the combustion performance and the power of the engine cannot be influenced basically;
2. milling the joint surface of the casing inevitably causes the crankshaft mounting hole and the camshaft mounting hole to be out of round due to the change of the diameters respectively;
by adopting honing treatment, the roundness precision technical requirement of the hole can be ensured under the condition of not enlarging the hole diameter, and the honing treatment has self-positioning property, so that the position degree and the coaxiality of the crankshaft mounting hole and the camshaft mounting hole can not be changed in the honing process, and meanwhile, smaller surface roughness can be obtained;
3. milling the joint surface of the casing inevitably reduces the center distance between the idle wheel shaft mounting hole and the crankshaft mounting hole on the rear end surface of the casing, and directly influences the gear transmission performance;
the processing mode of boring the idler shaft mounting hole according to the calibration requirement by additionally arranging the bushing is adopted, so that the diameter of the inner hole of the bushing reaches the calibration requirement value, and the technical requirement of hole-shaft matching is ensured; moreover, the center distance between the mounting hole of the idler shaft and the mounting hole of the crankshaft is recovered through the eccentricity of the inner hole of the bushing, so that the transmission performance of the gear is ensured;
4. milling the joint surface of the case inevitably reduces the distance between the rotation center of the camshaft and the mounting surface of the tappet body of the case, thereby influencing the gas distribution performance;
the distance between the rotation center of the camshaft and the installation surface of the tappet body of the casing is recovered through milling treatment of the installation surface of the tappet body, and the air distribution performance is guaranteed.
The repairing method effectively breaks through foreign technology blockade, the repairable casing with moderate and/or severe fretting at the joint surface does not need to be sent to the foreign country for repairing, and the economical efficiency is obvious.
Drawings
FIG. 1 is a schematic view of a piston aircraft engine casing in an exploded state.
FIG. 2 is a schematic view of a piston type aircraft engine casing in a combined state.
Fig. 3 is a structural schematic view of the casing half body in fig. 1 and 2.
Fig. 4 is a structural schematic view of the second casing half in fig. 1 and 2.
The reference numbers in the figures mean: 1, a first half body of the casing; 11-a half-body side junction surface; 12-camshaft mounting holes at one side of the half body; 13-mounting holes for idler shafts on one side of the half body; 14-crankshaft mounting holes on one side of the half body; 15-a crankshaft sealing ring mounting hole at one side of the half body; 16-oil grooves are arranged on the crankshaft at one side of the half body; 17-mounting surface of tappet body at one side of half body; 18-half body one side oil receiving pool mounting surface; 2, a second half body of the casing; 21-half body two-side joint surface; 22-camshaft mounting holes on two sides of the half body; 23-mounting holes for idler shafts on two sides of the half body; 24-crankshaft mounting holes on two sides of the half body; 25-a half body two-side crankshaft sealing ring mounting hole; 26-oil grooves are arranged on the crankshafts at two sides of the half body; 27-mounting surfaces of tappet bodies on two sides of the half body; 28-half body two-side oil collecting tank mounting surface; 3-camshaft mounting hole; 4-crankshaft mounting hole.
Detailed Description
The invention relates to a method for repairing a joint surface of a casing of a piston type aeroengine, which is clearly and specifically explained in detail with reference to the attached drawings of the specification, namely, fig. 1, fig. 2, fig. 3 and fig. 4.
It is expressly noted here that the drawings of the present invention are schematic and have been simplified in unnecessary detail for the purpose of clarity and to avoid obscuring the technical solutions that the present invention contributes to the prior art.
The noun explains: the calibration requirement value refers to the requirement value of the design technology of a casing of the piston type aircraft engine.
The half-side refers to a corresponding structure formed on the cartridge half, for example, the half-side junction surface refers to a junction surface formed on the cartridge half.
The two sides of the half body refer to corresponding structures formed on the two half casings, for example, the two-side crankshaft mounting holes of the half body refer to crankshaft mounting holes formed on the two half casings and having a semicircular structure.
The structure of the casing of the piston aeroengine to which the invention is directed is shown in fig. 1, 2, 3 and 4, and comprises a casing half body one 1 and a casing half body two 2. The first casing half body 1 and the second casing half body 2 are combined together by a plurality of connecting bolts in a horizontally opposed manner, so that a cylinder structure capable of mounting components such as a camshaft, a crankshaft, a connecting rod, a piston and the like and storing lubricating oil is formed.
The casing half body 1 has a structure including, but not limited to, the following:
a half-body-side joint surface 11, which is used as a joint surface for butting the casing half body two 2, i.e. as a median plane for butting with the casing half body two 2;
half-side camshaft mounting holes 12, in the form of semi-circular structures, for cooperating with corresponding hole-type structures on the second casing half 2 to form the camshaft mounting holes 3;
half-body side idler shaft mounting holes 13, in a full circle configuration, formed in the rear end face of the casing half-body 1;
a half-body side crankshaft mounting hole 14, having a semicircular structure, for forming a crankshaft mounting hole 4 in cooperation with a corresponding hole-type structure on the casing half body two 2; at least a half body side crankshaft sealing ring mounting hole 15 (front end) is arranged on the axial direction of the half body side crankshaft mounting hole 14, a half body side crankshaft mounting oil groove 16, a half body side crankshaft mounting bearing bush clamping groove and the like are arranged on the axial direction of the half body side crankshaft mounting hole;
a half body side tappet body mounting surface 17 for mounting a tappet body in cooperation with a corresponding structure on the second casing half body 2;
half-body side cylinder mounting surface, opposite half-body side joint surface 11, for mounting a corresponding cylinder;
a half-side oil sump mounting surface 18, at the bottom side of the rear region of the casing half 1, for mounting an oil sump in cooperation with a corresponding structure on the casing half 2.
The casing half body 2 has a structure including, but not limited to, the following:
a half-body two-side joint surface 21, which is used as a joint surface for butting against the casing half body 1, i.e. as a median plane for butting against the casing half body 1;
two-sided camshaft mounting holes 22 of half-body, in the form of semi-circular structures, intended to form the camshaft mounting holes 3 in cooperation with corresponding hole-type structures on the casing half-body 1;
the idler shaft mounting holes 23 on the two half sides are of a full circle structure and are formed on the rear end face of the second casing half 2;
two-half crankshaft mounting holes 24, in the form of semi-circular structures, for cooperating with corresponding hole-type structures on the casing half 1 to form the crankshaft mounting holes 4; the axial direction of the crankshaft mounting holes 24 on the two sides of the half body is at least provided with a crankshaft sealing ring mounting hole 25 (at the front end) on the two sides of the half body, a crankshaft mounting oil groove 26 on the two sides of the half body, a bearing bush clamping groove on the two sides of the half body and the like;
half-body two-side tappet body mounting surfaces 27 for mounting the tappet bodies in cooperation with corresponding structures on the casing half body 1;
half-body two-side cylinder mounting face, opposite to half-body two-side junction face 21, for mounting a corresponding cylinder;
two-half-side oil sump mounting surfaces 28, at the bottom side of the rear region of the second casing half 2, for mounting the oil sump in cooperation with corresponding structures on the first casing half 1.
In the service process of the cartridge receiver with the structure, due to working load and vibration, a micro-vibration abrasion structure layer is generated on a half body side joint surface 11 on the cartridge receiver half body I1 and a half body side joint surface 21 on the cartridge receiver half body II 2.
Before repairing the casing joint surface of the structure, whether the micro-vibration wear structure layers on the joint surface 11 on one side of the half body and the joint surface 21 on two sides of the half body can be repaired or not is analyzed and judged, and the judgment basis is as follows:
-whether the distance between the new half-body side joint surface 11 obtained by the repair and the half-body side cylinder mounting surface is greater than the minimum value required for the case calibration;
whether the distance between a new half body two-side joint surface 21 obtained through repair and a half body two-side cylinder mounting surface is larger than the minimum value of the casing calibration requirement or not;
if the result of the determination is greater than or equal to, the repair is possible;
if the judgment result is less than the preset value, the steel plate cannot be repaired and is directly scrapped.
The piston type aircraft engine casing with the structure has micro-vibration abrasion at the joint surface, and the analysis and judgment result is repairable.
The first process stage comprises the following technical measures:
step 1, taking a mounting surface of a cylinder at one side of a half body of a casing half body 1 as a horizontal positioning reference surface, and mounting the casing half body 1 on a clamp of a milling machine tool to enable a bonding surface 11 at one side of the half body to be vertical to the axial direction of a main shaft of the milling machine tool;
the rear end face of the first half case body 1 is used for alignment, so that the rear end face of the first half case body 1 is parallel to the Y-axis direction of a milling machine tool;
clamping a half case body 1;
milling the half-body side joint surface 11 by a single maximum milling depth of 0.1mm for multiple times, completely removing a micro-vibration abrasion structure layer on the half-body side joint surface 11 until the planeness, parallelism and surface roughness of the half-body side joint surface 11 and the distance between the half-body side joint surface 11 and the half-body side cylinder mounting surface accord with a calibration requirement value; whether the calibration requirement value is met or not needs to be detected, for example, the flatness of the half-body side joint surface 11, the parallelism between the half-body side joint surface 11 and the half-body side cylinder mounting surface and the distance between the half-body side joint surface 11 and the half-body side cylinder mounting surface are detected by adopting equipment such as a three-coordinate measuring instrument, the surface roughness of the half-body side joint surface 11 is detected by adopting equipment such as a roughness measuring instrument, if the flatness, the parallelism and the surface roughness do not reach the standard, processing is carried out again until the flatness reaches the standard, and if the actual distance between the half-body side joint surface 11 and the half-body side cylinder mounting surface is smaller than the minimum distance between the joint surface required by the calibration and the corresponding cylinder mounting surface, the half-body side joint surface is directly scrapped and is not allowed to be repaired;
the milling depth of the bonding surface 11 on one side of the half body is recorded in the process.
And step 2, keeping the clamping state of the step 1, milling the tappet body mounting surface 17 on one side of the half body, and keeping the milling depth consistent with that of the joint surface 11 on one side of the half body.
Step 3, taking the mounting surface of the cylinder at one side of the half body of the first half casing body 1 as a horizontal positioning reference surface, and mounting the first half casing body 1 on a clamp of a boring machine tool to ensure that the bonding surface 11 at one side of the half body is axially parallel to a main shaft of the boring machine tool;
aligning the crankshaft mounting hole 14 on one side of the half body to enable the crankshaft mounting hole 14 on one side of the half body to be coaxially matched with a spindle of a boring machine tool;
clamping a half case body 1;
and respectively boring oil grooves 16 on the crankshaft at one side of each half body in the crankshaft mounting holes 14 at one side of the half bodies until the required calibration value is met.
And step 4, keeping the clamping state of the step 3, and respectively boring the bearing bush clamping grooves of the crankshafts on the half sides in the crankshaft mounting holes 14 on the half sides until the required calibration value is met.
Step 5, taking the mounting surfaces of the cylinders on the two sides of the half body of the second half casing body 2 as horizontal positioning reference surfaces, and mounting the second half casing body 2 on a clamp of a milling machine tool to enable the bonding surfaces 21 on the two sides of the half body to be axially vertical to a main shaft of the milling machine tool;
the rear end face of the second half case body 2 is used for alignment, so that the rear end face of the second half case body 2 is parallel to the Y-axis direction of the milling machine tool;
clamping a second half case body 2;
milling the half-body two-side joint surface 21 by a single maximum milling depth of 0.1mm for multiple times, completely removing a micro-vibration abrasion structure layer on the half-body two-side joint surface 21 until the planeness, parallelism and surface roughness of the half-body two-side joint surface 21 and the distance between the half-body two-side joint surface 21 and the half-body two-side cylinder mounting surface accord with a calibration requirement value; whether the calibration requirement value is met or not needs to be detected, for example, the flatness of the half-body two-side bonding surface 21, the parallelism between the half-body two-side bonding surface 21 and the half-body two-side cylinder mounting surface and the distance between the half-body two-side bonding surface 21 and the half-body two-side cylinder mounting surface are detected by adopting equipment such as a three-coordinate measuring instrument, the surface roughness of the half-body two-side bonding surface 21 is detected by adopting equipment such as a roughness measuring instrument, if the flatness, the parallelism and the surface roughness do not reach the standard, processing is carried out again until the flatness reaches the standard, and if the actual distance between the half-body two-side bonding surface 21 and the half-body two-side cylinder mounting surface is smaller than the minimum distance between the bonding surface required by calibration and the corresponding cylinder mounting surface, the half-body two-side bonding surface is directly scrapped and is not allowed to be repaired;
the milling depth of the bonding surfaces 21 on both sides of the half body is recorded in the process.
And 6, keeping the clamping state of the 5, milling the mounting surface 27 of the tappet body on the two sides of the half body, wherein the milling depth is consistent with that of the joint surface 21 on the two sides of the half body.
Step 7, taking the mounting surfaces of the two-side cylinders of the half body of the second half casing body 2 as horizontal positioning reference surfaces, and mounting the second half casing body 2 on a fixture of a boring machine tool to enable the two-side bonding surfaces 21 of the half body to be parallel to the axial direction of a main shaft of the boring machine tool;
aligning the crankshaft mounting holes 24 on the two sides of the half body to enable the crankshaft mounting holes 24 on the two sides of the half body to be coaxially matched with a spindle of a boring machine tool;
clamping a second half case body 2;
and respectively boring oil grooves 26 of the crankshaft on the two sides of each half body in the crankshaft mounting holes 24 on the two sides of the half body until the required value of calibration is met.
And step 8, keeping the clamping state of the step 7, and respectively boring bearing bush clamping grooves of the two-side crankshafts of each half body in the two-side crankshaft mounting holes 24 of the half bodies until the required calibration value is met.
In the process stage, the first casing half body 1 and the second casing half body 2 are machined in no sequence.
In the process stage, the half body one-side junction surface 11/the half body two-side junction surface 21 is processed before the half body one-side tappet body mounting surface 17/the half body two-side tappet body mounting surface 27, the half body one-side crankshaft mounting oil groove 16/the half body two-side crankshaft mounting oil groove 26, and the half body one-side crankshaft mounting bearing bush clamping groove/the half body two-side crankshaft mounting bearing bush clamping groove are processed, so that the processed half body one-side junction surface 11/the half body two-side junction surface 21 can form a positioning reference.
In the process stage, the machining of the oil groove 16 for the crankshaft on one side of the half body/the oil groove 26 for the crankshaft on two sides of the half body is not performed in sequence with the machining of the bearing bush clamping groove for the crankshaft on one side of the half body/the bearing bush clamping groove for the crankshaft on two sides of the half body.
In the process stage, the machining precision detection of each measure should not be influenced by the clamping structure of the machine tool, if the detection precision is influenced inevitably by the current clamping structure, the clamping structure should be removed first, then the precision detection is performed, and the clamping is performed again after the detection is finished.
The second step is a process stage:
according to the assembling structure of the casing, a plurality of matched connecting bolts are adopted, the casing half body I1 and the casing half body II 2 which are processed according to the first step of process stage are combined into a whole casing, and the locking torque of each connecting bolt meets the calibration requirement value;
after the integral casing is combined, a camshaft mounting hole 12 on one side of the half body on the first casing half body 1 and a camshaft mounting hole 22 on two sides of the half body on the second casing half body 2 form a camshaft mounting hole 3 in a full circle structure; meanwhile, the crankshaft mounting hole 14 on one half body side on the first half casing body 1 and the crankshaft mounting holes 24 on two half body sides on the second half casing body 2 form the crankshaft mounting hole 4 in a full circle structure.
The third process stage comprises the following technical measures:
step 1, integrally clamping the casing on a honing machine;
honing the camshaft mounting hole 3 until the aperture, roundness, coaxiality and surface roughness of the camshaft mounting hole 3 meet the calibration requirement values; whether the required value meets the calibration requirement or not is detected, for example, the bore diameter and the roundness of the camshaft mounting hole 3 are detected by using equipment such as an inside dial gauge, the surface roughness of the camshaft mounting hole 3 is detected by using equipment such as a roughness measuring instrument, and the coaxiality of the camshaft mounting hole 3 is detected by using equipment such as a three-coordinate measuring instrument.
honing the crankshaft mounting hole 4 until the aperture, roundness, coaxiality and surface roughness of the crankshaft mounting hole 4 meet the calibration requirement values; whether the required value meets the calibration requirement or not is detected, for example, the bore diameter and the roundness of the crankshaft mounting hole 4 are detected by using equipment such as an inside dial gauge, the surface roughness of the crankshaft mounting hole 4 is detected by using equipment such as a roughness measuring instrument, and the coaxiality of the crankshaft mounting hole 4 is detected by using equipment such as a three-coordinate measuring instrument.
Step 3, taking the mounting surface of the oil receiving pool of the integral engine case as a horizontal positioning reference surface, and mounting the integral engine case on a clamp of a boring machine tool to enable the axial direction of the crankshaft mounting hole 4 to be parallel to the horizontal plane;
the crankshaft mounting hole 4 is used for alignment, so that the crankshaft mounting hole 4 is in coaxial fit with a spindle of a boring machine tool;
clamping the whole case;
boring a crankshaft sealing ring mounting hole until the aperture, roundness, coaxiality and surface roughness of the crankshaft sealing ring mounting hole meet the calibration requirement values; whether the required value meets the calibration requirement or not is detected, for example, the aperture and the roundness of the crankshaft seal ring mounting hole are detected by using equipment such as an inside dial gauge, the surface roughness of the crankshaft seal ring mounting hole is detected by using equipment such as a roughness measuring instrument, and the coaxiality of the crankshaft seal ring mounting hole is detected by using equipment such as a three-coordinate measuring instrument.
aligning the mounting hole 13 of the idler shaft at one side of the half body/the mounting hole 23 of the idler shaft at two sides of the half body on the first half body 1/the second half body 2 of the casing to ensure that the mounting hole 13 of the idler shaft at one side of the half body/the mounting hole 23 of the idler shaft at two sides of the half body are coaxially matched with a spindle of a boring machine tool;
clamping the whole case;
boring a current idler shaft mounting hole and reaming, wherein the reaming is to enlarge the aperture of the original idler shaft mounting hole to be larger than the idler shaft mounting hole required by calibration;
manufacturing a bushing capable of being installed in the corresponding expanded idler shaft mounting hole according to the material required by calibration, wherein the shape and the size of the manufactured bushing are matched with those of the corresponding expanded idler shaft mounting hole, and the inner hole (before boring) of the manufactured bushing is smaller than that of the idler shaft mounting hole required by calibration;
the manufactured bushing is arranged in the mounting hole of the corresponding expanded idle wheel shaft, so that stable mounting is ensured;
boring an inner hole of the lining to a value which meets a calibration requirement (namely the size of the idler shaft mounting hole meeting the calibration requirement) according to the center distance between the idler shaft mounting hole which meets the calibration requirement and the crankshaft mounting hole 4, and obtaining a new idler shaft mounting hole at the current position;
and obtaining new idler shaft mounting holes on the first casing half body 1 and the second casing half body 2.
In the process stage, the camshaft mounting hole 3 and the crankshaft mounting hole 4 are machined in no sequence.
In the process stage, the crankshaft mounting hole 4 is processed before the idle shaft mounting hole, so that a positioning reference can be formed by the processed crankshaft mounting hole 4.
In the process stage, the machining precision detection of each measure should not be influenced by the clamping structure of the machine tool, if the detection precision is influenced inevitably by the current clamping structure, the clamping structure should be removed first, then the precision detection is performed, and the clamping is performed again after the detection is finished.
The fourth step of the process comprises the following technical measures:
the method comprises the following steps that 1, the integral casing is disassembled to form a first casing half body 1 and a second casing half body 2 which are independent;
and step 3, after the detection is qualified, performing surface treatment on the first casing half body 1 and the second casing half body 2 respectively by adopting an anodizing mode (or an Allodin coating mode) until the calibration requirements are met.
In this process stage, the surface treatment is preceded by a non-destructive inspection treatment.
The above detailed description is merely illustrative of the present invention and is not to be construed as limiting thereof.
Although the present invention has been described in detail with reference to the above embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof, such as: different parts of the same processing mode can be processed in sequence by one-time clamping, or different parts of the same processing mode can be processed and clamped for multiple times in sequence; and such modifications or substitutions do not depart from the spirit and scope of the present invention in its essence.
Claims (9)
1. The method for repairing the joint surface of the piston type aeroengine casing is characterized by comprising the following four process stages:
the first step is:
milling a joint surface (11) at one side of the half body, completely removing a micro-vibration wear structure layer on the joint surface (11) at one side of the half body until the planeness, parallelism and surface roughness of the joint surface (11) at one side of the half body and the distance between the joint surface and a corresponding cylinder mounting surface meet calibration requirements, and recording the milling depth in the process;
milling two-side joint surfaces (21) of the half body, completely removing a micro-vibration abrasion structure layer on the two-side joint surfaces (21) of the half body until the planeness, parallelism and surface roughness of the two-side joint surfaces (21) of the half body and the distance between the joint surfaces and corresponding cylinder mounting surfaces meet calibration requirements, and recording the milling depth in the process;
the second step is a process stage:
combining the machined first casing half body (1) and the second casing half body (2) into a whole casing through connecting bolts to form a camshaft mounting hole (3) and a crankshaft mounting hole (4);
the third step is a process stage:
honing the camshaft mounting hole (3) until the aperture, roundness, coaxiality and surface roughness of the camshaft mounting hole (3) meet the calibration requirement values;
honing the crankshaft mounting hole (4) until the aperture, roundness, coaxiality and surface roughness of the crankshaft mounting hole (4) meet the calibration requirements;
boring a crankshaft seal ring mounting hole until the aperture, roundness, coaxiality and surface roughness of the crankshaft seal ring mounting hole meet the calibration requirement values;
boring and reaming an idler shaft mounting hole;
manufacturing a bushing capable of being installed in a corresponding expanded idler shaft mounting hole according to the calibration technical requirement;
installing the bushing into the corresponding mounting hole of the expanded idler shaft;
boring an inner hole of the bushing to a value meeting the calibration requirement according to the center distance between the idler shaft mounting hole meeting the calibration requirement and the crankshaft mounting hole (4);
the fourth step is a process stage:
-performing a non-destructive inspection;
-performing a surface treatment.
2. The method for repairing the joint surface of the piston type aircraft engine casing according to claim 1, wherein in the first process stage, the milling is performed in multiple times in a manner that the maximum milling depth of a single time is 0.1 mm.
3. The method for repairing the junction surface of the piston type aircraft engine casing according to claim 1, wherein the first process stage further comprises the following process steps:
-milling a tappet body mounting surface (17) on one side of the half body, the milling depth being consistent with the milling depth of the junction surface (11) on one side of the half body;
-milling the mounting surface (27) of the tappet on both sides of the half body to a milling depth corresponding to the milling depth of the bonding surface (21) on both sides of the half body.
4. The method for repairing the junction surface of the piston type aircraft engine casing according to claim 1, wherein the first process stage further comprises the following process steps:
-installing an oil groove (16) on the crankshaft on one side of the boring half body until the oil groove meets the calibration requirement;
-the crankshafts on both sides of the boring half-body are equipped with oil grooves (26) until the nominal requirements are met.
5. The method for repairing the junction surface of the piston type aircraft engine casing according to claim 1, wherein the first process stage further comprises the following process steps:
a bearing bush clamping groove is arranged on a crankshaft on one side of the boring half body until the requirement value meets the calibration requirement;
and mounting bearing bush clamping grooves on crankshafts on two sides of the boring half body until the requirements for calibration are met.
6. The method for repairing the joint surface of the piston type aircraft engine casing according to claim 1, wherein in the third process stage, the hole expansion is carried out by expanding the diameter of the idler shaft mounting hole to be larger than that of the idler shaft mounting hole required by calibration.
7. The method for repairing the joint surface of the piston type aircraft engine casing according to claim 1, wherein in the third process stage, an inner hole of the bush before boring is smaller than an idler shaft mounting hole required for calibration.
8. The method for repairing the joint surface of the piston type aircraft engine casing according to claim 1, wherein in the fourth process stage, the nondestructive testing is conducted on the whole casing or each casing half body in a penetration testing mode.
9. The method for repairing the joint surface of the piston type aircraft engine casing according to claim 1, wherein in the fourth process stage, the surface treatment is performed on the surface of the whole casing or each casing half body in an anodizing way or an alodine coating way.
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102248380A (en) * | 2011-07-04 | 2011-11-23 | 南京航空航天大学 | Method for processing integral casing of engine |
| CN103586625A (en) * | 2013-11-11 | 2014-02-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for restoring abrasion and deformation of spigot of thin-wall cartridge receiver |
| CN103624493A (en) * | 2013-11-26 | 2014-03-12 | 中国南方航空工业(集团)有限公司 | Method for machining half-and-half casings of gas compressor of aero-engine |
| US20140234098A1 (en) * | 2013-02-17 | 2014-08-21 | United Technologies Corporation | Turbine case retention hook with insert |
| CN104476096A (en) * | 2014-10-27 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Intermediate casing ring repairing method |
| CN105328399A (en) * | 2015-11-11 | 2016-02-17 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for split casing type parts of aero-engines |
| CN106493503A (en) * | 2016-11-25 | 2017-03-15 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity |
| CN106624588A (en) * | 2015-10-28 | 2017-05-10 | 中航湖南通用航空发动机有限公司 | Half-and-half case spraying deformation treatment method |
| CN107116336A (en) * | 2017-06-16 | 2017-09-01 | 中国人民解放军第五七九工厂 | A kind of aero-engine composite casing restorative procedure |
| CN110315276A (en) * | 2019-07-09 | 2019-10-11 | 中国航发哈尔滨东安发动机有限公司 | A kind of weak rigid casing repair method of aviation |
| CN110465783A (en) * | 2019-08-21 | 2019-11-19 | 无锡市润和机械有限公司 | A kind of processing method of aero-engine pin-connected panel cylinder casing |
| CN110497162A (en) * | 2019-09-23 | 2019-11-26 | 无锡航亚科技股份有限公司 | A kind of processing method of aero-engine casing |
| CN112051802A (en) * | 2020-09-16 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Automatic numerical control machining process method for aero-engine split-structure casing type parts |
-
2021
- 2021-06-24 CN CN202110705070.7A patent/CN113352051B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102248380A (en) * | 2011-07-04 | 2011-11-23 | 南京航空航天大学 | Method for processing integral casing of engine |
| US20140234098A1 (en) * | 2013-02-17 | 2014-08-21 | United Technologies Corporation | Turbine case retention hook with insert |
| CN103586625A (en) * | 2013-11-11 | 2014-02-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for restoring abrasion and deformation of spigot of thin-wall cartridge receiver |
| CN103624493A (en) * | 2013-11-26 | 2014-03-12 | 中国南方航空工业(集团)有限公司 | Method for machining half-and-half casings of gas compressor of aero-engine |
| CN104476096A (en) * | 2014-10-27 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Intermediate casing ring repairing method |
| CN106624588A (en) * | 2015-10-28 | 2017-05-10 | 中航湖南通用航空发动机有限公司 | Half-and-half case spraying deformation treatment method |
| CN105328399A (en) * | 2015-11-11 | 2016-02-17 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for split casing type parts of aero-engines |
| CN106493503A (en) * | 2016-11-25 | 2017-03-15 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity |
| CN107116336A (en) * | 2017-06-16 | 2017-09-01 | 中国人民解放军第五七九工厂 | A kind of aero-engine composite casing restorative procedure |
| CN110315276A (en) * | 2019-07-09 | 2019-10-11 | 中国航发哈尔滨东安发动机有限公司 | A kind of weak rigid casing repair method of aviation |
| CN110465783A (en) * | 2019-08-21 | 2019-11-19 | 无锡市润和机械有限公司 | A kind of processing method of aero-engine pin-connected panel cylinder casing |
| CN110497162A (en) * | 2019-09-23 | 2019-11-26 | 无锡航亚科技股份有限公司 | A kind of processing method of aero-engine casing |
| CN112051802A (en) * | 2020-09-16 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Automatic numerical control machining process method for aero-engine split-structure casing type parts |
Non-Patent Citations (4)
| Title |
|---|
| 中国航空工业集团公司离退休人员管理局: "《辉煌60年》", 31 December 2011, 航空工业出版社 * |
| 吴江等: "航空活塞发动机机匣结合面磨损失效分析", 《机械研究与应用》 * |
| 常虎山: "航空活塞发动机修理中珩磨应用技术研究", 《航空维修与工程》 * |
| 马文来等: "《航空概论》", 31 August 2018, 中国民航出版社 * |
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