CN111069674A - Method for sectional compensation groove milling of inner wall of titanium alloy thrust chamber - Google Patents
Method for sectional compensation groove milling of inner wall of titanium alloy thrust chamber Download PDFInfo
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- CN111069674A CN111069674A CN201911284411.7A CN201911284411A CN111069674A CN 111069674 A CN111069674 A CN 111069674A CN 201911284411 A CN201911284411 A CN 201911284411A CN 111069674 A CN111069674 A CN 111069674A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C3/00—Milling particular work; Special milling operations; Machines therefor
- B23C3/28—Grooving workpieces
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B23C2222/88—Titanium
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Abstract
The invention relates to a method for milling grooves on the inner wall of a titanium alloy thrust chamber in a sectional compensation manner, belonging to the field of processing of the inner wall of the titanium alloy thrust chamber of a liquid rocket engine; step one, coaxially sleeving a thrust chamber on the outer wall of a positioning mould; measuring a gap between the inner wall of the thrust chamber and the outer wall of the positioning mould; marking at a position where the gap size is greater than or equal to a threshold value A; step three, preprocessing a milling groove at the marked position of the inner wall of the thrust chamber along the direction of a bus; step four, carrying out secondary marking; measuring the error value of the depth of the pre-processing milling groove at each secondary mark and the depth of the pre-processing standard groove; step five, carrying out compensation groove milling processing on each position of the secondary mark to eliminate an error value; sixthly, finally processing a milling groove; finishing final forming and groove milling of the inner wall of the thrust chamber; according to the invention, by distinguishing the fit clearance between the inner wall of the thrust chamber and the clamping positioning mould and adopting the cutters with different parameters for compensation, the material rebound and the groove milling depth error caused by the fit clearance are overcome.
Description
Technical Field
The invention belongs to the field of machining of the inner wall of a titanium alloy thrust chamber of a liquid rocket engine, and relates to a method for milling grooves in a sectional compensation mode on the inner wall of the titanium alloy thrust chamber.
Background
Chinese patent publication No. CN 101412122a, published as 22.4.2009, entitled "vertical processing method for nozzle cooling channels of liquid rocket engines", discloses a method for vertically processing nozzle cooling channels of liquid rocket engines, which includes scanning buses one by one with a single-point laser sensor, performing data processing, calculating milling cutter positions, and completing groove milling and back chipping processing by one-time clamping. The method is a method for milling the groove of the stainless steel nozzle of the liquid rocket engine, and is suitable for milling the groove of the nozzle in a good fit state with a mould. The disadvantages are as follows: the requirement on the attaching state of the spray pipe and the clamping fixture is high, sampling and groove milling are completed at one time, accurate compensation cannot be performed on the position with poor attaching state of the local spray pipe and the clamping fixture, and accurate compensation cannot be performed on the size error caused by product rebound and cutter back-off processing. The inner wall of the thrust chamber of the titanium alloy liquid rocket engine with poor metal plate forming state can not meet the requirement of precise groove milling.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects in the prior art are overcome, the method for compensating the milling groove in the inner wall of the titanium alloy thrust chamber in a segmented mode is provided, the inner wall of the thrust chamber is distinguished from a clamping positioning mould through a fit clearance, cutters with different parameters are adopted for compensation, and material rebound and milling groove depth errors caused by the fit clearance are overcome.
The technical scheme of the invention is as follows:
a method for milling grooves on the inner wall of a titanium alloy thrust chamber in a sectional compensation mode comprises the following steps:
step one, coaxially sleeving a thrust chamber on the outer wall of a positioning mould;
measuring a gap between the inner wall of the thrust chamber and the outer wall of the positioning mould; marking is not carried out at the position where the gap size is smaller than the threshold A; marking at a position where the gap size is greater than or equal to a threshold value A;
step three, preprocessing a milling groove at the marked position of the inner wall of the thrust chamber along the direction of a bus;
step four, measuring the groove depth of the pre-processing milling groove, comparing the groove depth of the pre-processing milling groove with the pre-processing standard groove depth, and carrying out secondary marking; simultaneously measuring the error value of the depth of the pre-processing milling groove and the depth of the pre-processing standard groove at each mark;
fifthly, performing compensation groove milling processing on each position of the secondary mark according to the error value to eliminate the error value;
sixthly, finally processing a milling groove; and finishing final forming and groove milling of the inner wall of the thrust chamber.
In the method for milling the groove on the inner wall of the titanium alloy thrust chamber by section compensation, in the first step, the thrust chamber is of a hollow conical-cylindrical shell structure; the positioning mould is in a conical column structure; and the shape of the outer wall of the positioning mould corresponds to the shape of the inner wall of the thrust chamber.
In the above method for milling the groove on the inner wall of the titanium alloy thrust chamber by section compensation, in the second step, the threshold value a is 0.5 mm.
In the above method for milling the groove in the sectional compensation manner on the inner wall of the titanium alloy thrust chamber, in the third step, the method for preprocessing the groove comprises the following steps:
pre-processing a milling groove in the direction of the bus from the small end of the thrust chamber to the large end of the thrust chamber along the direction of the bus in the area with the mark; locations where no mark is present are not preprocessed.
In the method for milling the groove by section compensation on the inner wall of the titanium alloy thrust chamber, during the preprocessing, the depth of the preprocessed groove is 40-80% of the depth of the standard final processed groove; the number of the pre-processing milling grooves in the area where the mark exists is 10% -20% of the total number of the pre-processing milling grooves.
In the fourth step, the specific method of secondary marking is as follows:
comparing the measured groove depth with the pre-processing standard groove depth, and when the deviation value of the measured groove depth and the pre-processing standard groove depth is more than 0.1mm or the processing error is more than 50% of the tolerance zone of the standard final processing groove depth, carrying out secondary marking on the position; otherwise, it is not marked.
In the sixth step of the method for milling the grooves by section compensation of the inner wall of the titanium alloy thrust chamber, when the grooves are finally machined, the whole inner wall of the thrust chamber is machined according to the depth of the grooves which are finally milled.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention can purposefully solve the problems of different sinking and rebound amounts of the plate caused by different fit gaps between the inner wall of the thrust chamber and the clamping mould due to the adoption of regional cutting parameter compensation
(2) According to the invention, corresponding cutting parameters are selected for compensation aiming at different sinking and rebounding amounts of the plate, so that the consistency of the depth of the milling groove can be fully ensured, and the accuracy of the processing size of the milling groove is improved;
(3) the invention adopts regional compensation of cutting parameters, which can greatly reduce cutting vibration caused by fit clearance in the groove milling process, prolong the service life of the milling cutter and improve the surface quality of the groove milling part;
(4) the invention adopts the subareas to compensate the cutting parameters, can fully improve the groove milling efficiency of different areas and greatly shorten the processing time of products.
Drawings
FIG. 1 is a schematic view of a sectional compensation milling groove of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a method for milling grooves on the inner wall of a titanium alloy thrust chamber by sectional compensation, which is characterized in that the inner wall of a titanium alloy hot-forming metal plate thrust chamber of a rocket engine is pressed into a profiling mould; performing straight groove milling on the inner wall of the thrust chamber through a vertical groove milling machine; eliminating machining errors caused by fit gaps between the inner wall and the mould through axial and radial sectional parameter compensation; the depth consistency of the milling cooling channel on the inner wall of the thrust chamber is ensured. The invention effectively solves the problems of groove milling error caused by the fit clearance between the inner wall of the titanium alloy hot-forming metal plate thrust chamber and the positioning mould and the milling rebound error of the titanium alloy thin-wall part; the abrasion and damage of cutting vibration to the milling cutter are reduced; the efficiency of milling flutes in different positions is promoted.
As shown in fig. 1, a method for milling grooves on the inner wall of a titanium alloy thrust chamber in a sectional compensation manner comprises the following steps:
step one, coaxially sleeving a thrust chamber on the outer wall of a positioning mould; the thrust chamber is a hollow conical cylindrical shell structure; the positioning mould is in a conical column structure; and the shape of the outer wall of the positioning mould corresponds to the shape of the inner wall of the thrust chamber.
Measuring a gap between the inner wall of the thrust chamber and the outer wall of the positioning mould; marking is not carried out at the position where the gap size is smaller than the threshold A; marking at a position where the gap size is greater than or equal to a threshold value A; the threshold A is 0.5 mm.
Step three, preprocessing a milling groove at the marked position of the inner wall of the thrust chamber along the direction of a bus; the method for preprocessing the milling groove comprises the following steps:
pre-processing a milling groove in the direction of the bus from the small end of the thrust chamber to the large end of the thrust chamber along the direction of the bus in the area with the mark; locations where no mark is present are not preprocessed. The depth of the pre-processing milling groove is 40-80% of the depth of the standard final processing groove; the number of the pre-processing milling grooves in the area where the mark exists is 10% -20% of the total number of the pre-processing milling grooves.
Step four, measuring the groove depth of the pre-processing milling groove, comparing the groove depth of the pre-processing milling groove with the pre-processing standard groove depth, and carrying out secondary marking; simultaneously measuring the error value of the depth of the pre-processing milling groove and the depth of the pre-processing standard groove at each mark; the specific method of secondary marking is as follows:
comparing the measured groove depth with the pre-processing standard groove depth, and when the deviation value of the measured groove depth and the pre-processing standard groove depth is more than 0.1mm or the processing error is more than 50% of the tolerance zone of the standard final processing groove depth, carrying out secondary marking on the position; otherwise, it is not marked.
Fifthly, performing compensation groove milling processing on each position of the secondary mark according to the error value to eliminate the error value;
sixthly, finally processing a milling groove; and finishing final forming and groove milling of the inner wall of the thrust chamber. And when the groove is finally machined, machining the whole inner wall of the thrust chamber according to the depth of the final groove.
Example 1
(1) The non-uniform fit clearance exists between the inner wall of the thrust chamber and the positioning mould, the thickness of the non-uniform fit clearance is 0.1-2.2 mm, and the area of 0.5-2.2 mm accounts for about 20% of the total fit area. The fit clearance is 0.5-2.5 mm and is mainly distributed in the axial direction.
(2) And preprocessing the milling groove area, wherein the number of preprocessed milling grooves accounts for 20% of the total number of milling grooves, and the depth of the preprocessed milling grooves is 40% of the total depth of the milling grooves.
(3) And the condition of distinguishing and marking the area with the depth of the preprocessed groove deviating from the theoretical processing depth is that the processing error of the milling groove depth is more than 0.4 mm.
(4) Partitioning treatment is carried out in the axial direction according to the milling groove depth machining error larger than 0.4mm, and 3 sections of segmentation are adopted from top to bottom; the fit clearance in the radial direction is uniformly distributed without partition processing.
(5) The groove milling mode adopts a single-piece milling cutter groove milling mode and a double-piece milling cutter groove milling mode.
(6) By compensating the processing parameters of the divided areas, corresponding milling groove parameters are selected for compensation aiming at different sinking and rebounding amounts of the plate, and the milling depth processing error of 0.4mm caused by the fit clearance between the inner wall and the mould is eliminated.
Example 2
(1) The detection thrust chamber inner wall and the positioning mould have uneven fit gaps, the uneven fit gaps between the thrust chamber inner wall and the positioning mould are 0.1-2.5 mm, and the area of 0.5-2.5 mm accounts for about 40% of the total fit area. The bonding gap is 0.5-2.5 mm and is mainly distributed in the radial direction.
(2) And preprocessing the milling groove area, wherein the number of preprocessed milling grooves accounts for 10% of the total number of milling grooves, and the depth of the preprocessed milling grooves accounts for 80% of the total depth of the milling grooves.
(3) And the condition of distinguishing and marking the area with the depth of the preprocessed groove deviating from the theoretical processing depth is that the processing error of the milling groove depth is more than 0.2 mm.
(4) Carrying out partition treatment in the radial direction according to the milling groove depth machining error larger than 0.2mm, and dividing 16 areas on the circumference; the fit clearance in the axial direction is uniformly distributed without partition processing.
(5) The groove milling mode adopts a single-piece milling cutter groove milling mode and a double-piece milling cutter groove milling mode.
(6) By compensating the processing parameters of the divided areas, corresponding milling groove parameters are selected for compensation aiming at different sinking and rebounding amounts of the plate, and the milling depth processing error of 0.2mm caused by the fit clearance between the inner wall and the mould is eliminated.
Example 3
(1) The detection thrust chamber inner wall and the positioning mould have uneven fit gaps, the uneven fit gaps between the thrust chamber inner wall and the positioning mould are 0.1-2.5 mm, and the area of 0.5-2.5 mm accounts for about 40% of the total fit area. The fit clearance is 0.5-2.5 mm and is mainly distributed in the axial direction and the radial direction.
(2) And preprocessing the milling groove area, wherein the number of preprocessed milling grooves accounts for 15% of the total number of milling grooves, and the depth of the preprocessed milling grooves is 70% of the total depth of the milling grooves.
(3) And the condition of distinguishing and marking the area with the depth of the preprocessed groove deviating from the theoretical processing depth is that the processing error of the milling groove depth is more than 0.3 mm.
(4) Partitioning treatment is carried out in the axial direction according to the milling groove depth machining error larger than 0.3mm, and 5 sections are segmented from top to bottom; and (3) carrying out partition treatment in the radial direction according to the size of the fit clearance between the inner wall of the thrust chamber and the mould, and dividing 8 areas on the circumference.
(5) The groove milling mode adopts a single-piece milling cutter groove milling mode and a double-piece milling cutter groove milling mode.
(6) By compensating the processing parameters of the divided areas, corresponding milling groove parameters are selected for compensation aiming at different sinking and rebounding amounts of the plate, and the milling depth processing error of 0.3mm caused by the fit clearance between the inner wall and the mould is eliminated.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (7)
1. A method for milling grooves on the inner wall of a titanium alloy thrust chamber in a sectional compensation mode is characterized by comprising the following steps: the method comprises the following steps:
step one, coaxially sleeving a thrust chamber (1) on the outer wall of a positioning mould (2);
measuring a gap between the inner wall of the thrust chamber (1) and the outer wall of the positioning mould (2); marking is not carried out at the position where the gap size is smaller than the threshold A; marking at a position where the gap size is greater than or equal to a threshold value A;
step three, preprocessing a milling groove (3) at the marked position of the inner wall of the thrust chamber (1) along the direction of a bus;
step four, measuring the groove depth of the pre-processing milling groove (3), comparing the groove depth of the pre-processing milling groove (3) with the pre-processing standard groove depth, and carrying out secondary marking; simultaneously measuring the error value of the depth of the pre-processing milling groove and the depth of the pre-processing standard groove at each mark;
fifthly, performing compensation groove milling processing on each position of the secondary mark according to the error value to eliminate the error value;
sixthly, finally processing a milling groove; and finishing the final forming of the milling groove (4) on the inner wall of the thrust chamber (1).
2. The method for sectional compensation of milled grooves in the inner wall of the titanium alloy thrust chamber as claimed in claim 1, wherein: in the first step, the thrust chamber (1) is of a hollow conical cylindrical shell structure; the positioning mould (2) is in a conical and cylindrical structure; and the shape of the outer wall of the positioning mould (2) corresponds to the shape of the inner wall of the thrust chamber (1).
3. The method for sectional compensation of milled grooves in the inner wall of the titanium alloy thrust chamber as claimed in claim 2, wherein: in the second step, the threshold A is 0.5 mm.
4. The method for sectional compensation of milled grooves in the inner wall of the titanium alloy thrust chamber as claimed in claim 3, wherein: in the third step, the method for preprocessing the milling groove comprises the following steps:
pre-processing a milling groove (3) in the direction of a bus from the small end of the thrust chamber (1) to the large end of the thrust chamber (1) along the direction of the bus in a region with a mark; locations where no mark is present are not preprocessed.
5. The method for sectional compensation of milled grooves in the inner wall of the titanium alloy thrust chamber as claimed in claim 4, wherein: during preprocessing, the depth of a preprocessed milling groove is 40-80% of the depth of a standard final processing groove; the number of the pre-processing milling grooves in the area where the mark exists is 10% -20% of the total number of the pre-processing milling grooves.
6. The method for sectional compensation of milled grooves in the inner wall of the titanium alloy thrust chamber as claimed in claim 5, wherein: in the fourth step, the specific method of secondary marking is as follows:
comparing the measured groove depth with the pre-processing standard groove depth, and when the deviation value of the measured groove depth and the pre-processing standard groove depth is more than 0.1mm or the processing error is more than 50% of the tolerance zone of the standard final processing groove depth, carrying out secondary marking on the position; otherwise, it is not marked.
7. The method for sectional compensation of milled grooves in the inner wall of the titanium alloy thrust chamber as claimed in claim 6, wherein: and in the sixth step, when the milling groove is finally processed, the whole inner wall of the thrust chamber (1) is processed according to the depth of the final milling groove.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114535675A (en) * | 2022-04-02 | 2022-05-27 | 徐州乔南仪表有限公司 | Cutter for milling iron grooving and grooving method thereof |
| CN115091266A (en) * | 2022-05-31 | 2022-09-23 | 广东工业大学 | Springback error compensation method for ultraprecise cutting titanium alloy microstructure surface |
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| US20120009028A1 (en) * | 2010-07-09 | 2012-01-12 | Uwe Hobohm | Scem for heat-resistant materials (star mill) |
| CN205702130U (en) * | 2016-06-23 | 2016-11-23 | 海阳中集来福士海洋工程有限公司 | Groove type wall processing mold and groove type wall process equipment |
| CN107175470A (en) * | 2017-06-02 | 2017-09-19 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN109202502A (en) * | 2018-10-25 | 2019-01-15 | 西安航天发动机有限公司 | A kind of engine expansion segment slotting attachment and application method |
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2019
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Patent Citations (5)
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| DE1452115A1 (en) * | 1964-10-08 | 1969-03-20 | United Eng Foundry Co | Automatic roll gap control |
| US20120009028A1 (en) * | 2010-07-09 | 2012-01-12 | Uwe Hobohm | Scem for heat-resistant materials (star mill) |
| CN205702130U (en) * | 2016-06-23 | 2016-11-23 | 海阳中集来福士海洋工程有限公司 | Groove type wall processing mold and groove type wall process equipment |
| CN107175470A (en) * | 2017-06-02 | 2017-09-19 | 中国航发南方工业有限公司 | The special-shaped deep groove processing method of titanium alloy component |
| CN109202502A (en) * | 2018-10-25 | 2019-01-15 | 西安航天发动机有限公司 | A kind of engine expansion segment slotting attachment and application method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114535675A (en) * | 2022-04-02 | 2022-05-27 | 徐州乔南仪表有限公司 | Cutter for milling iron grooving and grooving method thereof |
| CN115091266A (en) * | 2022-05-31 | 2022-09-23 | 广东工业大学 | Springback error compensation method for ultraprecise cutting titanium alloy microstructure surface |
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