CN114055102A - Single turbine blade tip machining method - Google Patents
Single turbine blade tip machining method Download PDFInfo
- Publication number
- CN114055102A CN114055102A CN202111223557.8A CN202111223557A CN114055102A CN 114055102 A CN114055102 A CN 114055102A CN 202111223557 A CN202111223557 A CN 202111223557A CN 114055102 A CN114055102 A CN 114055102A
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- turbine
- blade
- turbine blade
- machining
- tip
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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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
Abstract
The invention provides a method for machining a single turbine blade tip, which comprises the following steps: s1: pretreating the turbine blade; s2: mounting the pretreated turbine blade on a turbine disc by using a machining tool, and judging the blade tip allowance of the turbine blade; s3, processing the blade tip of the turbine blade according to the blade tip allowance obtained in the S2; s4: the turbine blade processed at S3 is detached from the turbine disk and is handled and stored. The method for machining the blade tip of the single turbine blade ensures the reliability of machining quality, is simple and convenient to operate, and improves the machining quality and the machining efficiency.
Description
Technical Field
The invention belongs to the field of manufacturing of aero-engines, and particularly relates to a method for machining a single turbine blade tip.
Background
Turbine blades are important components of aircraft engines, and the blades are connected in turbine disk mortises by tenons. Turbine blades are susceptible to damage and scuffing after prolonged operation, at which time the damaged blades need to be replaced. The new blade to be replaced requires tip grinding to ensure clearance requirements with the turbine case. For the processing of a single blade tip, if a grinding method is adopted, all the blades need to be installed on a turbine disc and belong to intermittent cutting, the processing quality is unstable, and the processing efficiency is low. Meanwhile, the number of the turbine blades is odd, so that the turbine blades are not symmetrically arranged on a turbine disc, and the size of the blade tip cannot be measured by adopting a conventional method.
Disclosure of Invention
In order to solve the problems and ensure the processing quality and the processing efficiency of the single turbine blade tip processing, the single turbine blade tip processing method is provided.
The invention aims to provide a method for machining a single turbine blade tip, which comprises the following steps: s1: pretreating the turbine blade; s2: mounting the pretreated turbine blade on a turbine disc by using a machining tool, and judging the blade tip allowance of the turbine blade; s3, processing the blade tip of the turbine blade according to the blade tip allowance obtained in the S2; s4: the turbine blade processed at S3 is detached from the turbine disk and is handled and stored.
The method for machining the blade tip of the single turbine blade provided by the invention is also characterized in that the step S1 comprises the following steps: s1.1: cleaning the surface of the turbine blade by using absolute alcohol; s1.2: and (3) sticking and plugging the surface air film holes of the turbine blade by using medical adhesive tape.
The method for machining the blade tip of the single turbine blade provided by the invention is also characterized in that the step S2 comprises the following steps: s2.1: installing and pressing a turbine disc on a bottom plate of a machining tool; s2.2: installing tenons of the turbine blades into mortises of the turbine disc, and tightly pushing and fixing the turbine blades on the turbine disc through wedges; s2.3: a damping piece is plugged between the lower end surface of the turbine blade and the bottom plate; s2.4: and (4) checking the radius difference between the blade tip of the turbine blade and the outer diameter of the base plate by using a dial indicator, and judging the condition of the blade tip allowance.
The single turbine blade tip machining method provided by the invention is also characterized in that in S2.1, the bottom plate is fixed on a machine tool workbench, the turbine disc and the bottom plate are installed on the same rotation center, the lower end face of a tenon of the turbine disc is attached to the upper end face of the bottom plate, the excircle of the lower installation edge of the turbine disc is embedded into the central hole of the bottom plate, the turbine disc is pressed through a cushion block, a pressing bolt and a pressing plate, the cushion block is arranged on the right annular positioning surface of the bottom plate, one end of the pressing plate is pressed on the upper end face of a mortise of the turbine disc, the other end of the pressing plate is pressed on the cushion block, and the pressing bolt penetrates through the pressing plate to fix the turbine disc and the bottom plate.
The method for machining the blade tip of the single turbine blade is further characterized in that the wedge block is knocked into a gap between the bottom of the tenon of the turbine blade and the mortise of the turbine disc through the copper rod, the wedge block is of an L-shaped structure, the vertical part of the L-shaped structure is of a wedge-shaped structure, and the wedge angle is 1-2 degrees.
The method for machining the blade tip of the single turbine blade is further characterized in that the upper surface of the wedge block is provided with a bolt hole convenient to pull out.
The method for machining the blade tip of the single turbine blade is further characterized in that the damping piece is made of foam rubber.
The single turbine blade tip machining method provided by the invention is also characterized in that the outer diameter of the bottom plate is the same as the outer circle diameter of the standard blade tip, and the center hole of the bottom plate is the same as the outer circle diameter of the lower mounting edge of the turbine disc.
The method for machining the blade tip of the single turbine blade provided by the invention is also characterized in that the step S3 comprises the following steps: s3.1: calling a numerical control program, and processing the blade tips of the turbine blades, wherein the cutting depth of each blade is 0.08-0.1 mm, and the cutting speed is 150-200 mm/min; s3.2: and (4) checking the radius difference between the blade tip and the outer diameter of the base plate of the turbine blade, and repeating S3.1 if the radius difference still exists until the radius difference is zero.
The method for machining the blade tip of the single turbine blade provided by the invention is also characterized in that the step S4 comprises the following steps: s4.1, disassembling the turbine blade and the turbine disc, filing the surface of the blade tip with oilstone, and removing burrs; s4.2: disassembling the medical adhesive plaster, cleaning the blade again by absolute alcohol, and checking whether the air film hole on the surface of the blade is blocked; s4.3: and wrapping the cleaned turbine blades by using oil seal paper, and putting the wrapped turbine blades into a special turnover box for storage.
Compared with the prior art, the invention has the following beneficial effects
The method for machining the blade tip of the single turbine blade ensures the reliability of machining quality, is simple and convenient to operate, and improves the machining quality and the machining efficiency.
Description of the drawings:
in order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a processing tool used in a processing method according to an embodiment of the present invention;
fig. 2 is a top view of fig. 1.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the processing method provided by the invention is specifically described in the following embodiments with reference to the attached drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified. The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
The embodiment of the invention provides a method for machining a single turbine blade tip, which comprises the following steps: s1: pretreating the turbine blade; s2: mounting the pretreated turbine blade on a turbine disc by using a machining tool, and judging the blade tip allowance of the turbine blade; s3, processing the blade tip of the turbine blade according to the blade tip allowance obtained in the S2; s4: the turbine blade processed at S3 is detached from the turbine disk and is handled and stored.
In some embodiments, the S1 includes the following steps: s1.1: cleaning the surface of the turbine blade by using absolute alcohol; s1.2: and (3) sticking and plugging the surface air film holes of the turbine blade by using medical adhesive tape.
In some embodiments, the S2 includes the following steps: s2.1: installing and pressing a turbine disc on a bottom plate of a machining tool; s2.2: installing tenons of the turbine blades into mortises of the turbine disc, and tightly pushing and fixing the turbine blades on the turbine disc through wedges; s2.3: a damping piece is plugged between the lower end surface of the turbine blade and the bottom plate; s2.4: and (4) checking the radius difference between the blade tip of the turbine blade and the outer diameter of the base plate by using a dial indicator, and judging the condition of the blade tip allowance.
In some embodiments, in S2.1, the base plate is fixed on a machine tool workbench, the turbine disc and the base plate are mounted on the same rotation center, the lower end face of the tenon of the turbine disc is fitted with the upper end face of the base plate, the outer circle of the lower mounting edge of the turbine disc is embedded into the center hole of the base plate, and the turbine disc is pressed through a cushion block, a pressing bolt and a pressing plate, the cushion block is arranged on the right annular positioning surface of the base plate, one end of the pressing plate is pressed on the upper end face of the mortise of the turbine disc, the other end of the pressing plate is pressed on the cushion block, and the pressing bolt penetrates through the pressing plate to fix the turbine disc and the base plate.
In some embodiments, the wedge is knocked into a gap between the bottom of the turbine blade tenon and the mortise of the turbine disc through a copper rod, the wedge is in an L-shaped structure, the vertical part of the L is in a wedge-shaped structure, and the wedge angle is 1-2 degrees.
In some embodiments, the upper surface of the wedge is provided with a bolt hole for facilitating extraction.
In some embodiments, the shock absorbing member is foam rubber.
In some embodiments, the outer diameter of the bottom plate is the same as the outer diameter of the standard blade tip, and the central hole of the bottom plate is the same as the outer diameter of the lower mounting edge of the turbine disc.
In some embodiments, the S3 includes the following steps: s3.1: calling a numerical control program, and processing the blade tips of the turbine blades, wherein the cutting depth of each blade is 0.08-0.1 mm, and the cutting speed is 150-200 mm/min; s3.2: and (4) checking the radius difference between the blade tip and the outer diameter of the base plate of the turbine blade, and repeating S3.1 if the radius difference still exists until the radius difference is zero.
In some embodiments, the S4 includes the following steps: s4.1, disassembling the turbine blade and the turbine disc, filing the surface of the blade tip with oilstone, and removing burrs; s4.2: disassembling the medical adhesive plaster, cleaning the blade again by absolute alcohol, and checking whether the air film hole on the surface of the blade is blocked; s4.3: and wrapping the cleaned turbine blades by using oil seal paper, and putting the wrapped turbine blades into a special turnover box for storage.
In some embodiments, as shown in fig. 1-2, a single turbine blade tip machining tool is provided, and the tool consists of a bottom plate 1, a cushion block 2, a compression bolt 3, a pressure plate 4, a wedge block 5 and foam rubber 6; the base plate 1 is of a disc structure, a fixed mounting hole 1a is formed in the base plate 1, and the base plate is connected with a machine tool workbench through the fixed mounting hole 1 a; the turbine disc and the bottom plate 1 are installed in the same rotation center, the lower end face of a tenon of the turbine disc is attached to the upper end face 1c of the bottom plate 1, and the excircle of the lower installation edge of the turbine disc is embedded into the center hole 1b of the bottom plate 1; a cushion block 2 is placed on a right annular positioning surface of the bottom plate 1, one end of a pressure plate 4 is tightly pressed on the upper end surface of a mortise of the turbine disc, the other end of the pressure plate is tightly pressed on the cushion block 2, and a pressure bolt 3 penetrates through the first pressure plate 4 to tightly press the turbine disc on the bottom plate 1; the wedge 5 is of an L-shaped structure, the vertical part of the L-shape is of a wedge-shaped structure, and the wedge angle is 2 degrees; the tenon of the turbine blade is arranged in the mortise of the turbine disc, and the wedge 5 is embedded in a gap between the bottom of the tenon of the turbine blade and the mortise of the turbine disc, so that the turbine blade is tightly propped and fixed on the turbine disc; foam rubber 6 is filled between the lower end surface of the turbine blade and the left annular surface of the bottom plate 1, and the shock absorption effect is achieved.
In some embodiments, the central hole 1b of the bottom plate 1 has the same diameter as the outer circle of the lower mounting edge of the turbine disk.
In some embodiments, the wedge 5 has a bolt hole on its upper surface to facilitate the extraction of the wedge 5.
In some embodiments, the large outer circle size of the base plate 1 is within the tolerance range of the dimension of the tip of the turbine blade in the drawing.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A method for machining the tip of a single turbine blade is characterized by comprising the following steps:
s1: pretreating the turbine blade;
s2: mounting the pretreated turbine blade on a turbine disc by using a machining tool, and judging the blade tip allowance of the turbine blade;
s3, processing the blade tip of the turbine blade according to the blade tip allowance obtained in the S2;
s4: the turbine blade processed at S3 is detached from the turbine disk and is handled and stored.
2. The method for machining the tip of the single turbine blade according to claim 1, wherein the step S1 includes the steps of:
s1.1: cleaning the surface of the turbine blade by using absolute alcohol;
s1.2: and (3) sticking and plugging the surface air film holes of the turbine blade by using medical adhesive tape.
3. The method for machining the tip of the single turbine blade according to claim 1, wherein the step S2 includes the steps of:
s2.1: installing and pressing a turbine disc on a bottom plate of a machining tool;
s2.2: installing tenons of the turbine blades into mortises of the turbine disc, and tightly pushing and fixing the turbine blades on the turbine disc through wedges;
s2.3: a damping piece is plugged between the lower end surface of the turbine blade and the bottom plate;
s2.4: and (4) checking the radius difference between the blade tip of the turbine blade and the outer diameter of the base plate by using a dial indicator, and judging the condition of the blade tip allowance.
4. The single-turbine blade tip machining method of claim 3, wherein in S2.1, the base plate is fixed on a machine tool workbench, the turbine disc and the base plate are installed on the same rotation center, the lower end face of a tenon of the turbine disc is attached to the upper end face of the base plate, an outer circle of a lower installation edge of the turbine disc is embedded into a center hole of the base plate, the turbine disc is pressed through a cushion block, a pressing bolt and a pressing plate, the cushion block is arranged on a right annular positioning surface of the base plate, one end of the pressing plate is pressed on the upper end face of a mortise of the turbine disc, the other end of the pressing plate is pressed on the cushion block, and the pressing bolt penetrates through the pressing plate to fix the turbine disc and the base plate.
5. The method for machining the blade tip of the single-turbine blade as claimed in claim 3, wherein the wedge block is knocked into a gap between the bottom of the tenon of the turbine blade and the mortise of the turbine disc through a copper bar, the wedge block is of an L-shaped structure, the vertical part of the L-shaped structure is of a wedge-shaped structure, and the wedge angle is 1-2 degrees.
6. The method of machining a single turbine blade tip as claimed in claim 5, wherein the wedge has bolt holes in its upper surface to facilitate extraction.
7. The method of machining a single turbine blade tip as set forth in claim 3, wherein the damping member is a foam rubber.
8. The single turbine blade tip machining method of claim 3, wherein the outer diameter of the bottom plate is the same as the outer diameter of a standard blade tip, and the center hole of the bottom plate is the same as the outer diameter of a lower mounting edge of a turbine disk.
9. The method for machining the tip of the single turbine blade according to claim 1, wherein the step S3 includes the steps of:
s3.1: calling a numerical control program, and processing the blade tips of the turbine blades, wherein the cutting depth of each blade is 0.08-0.1 mm, and the cutting speed is 150-200 mm/min;
s3.2: and (4) checking the radius difference between the blade tip and the outer diameter of the base plate of the turbine blade, and repeating S3.1 if the radius difference still exists until the radius difference is zero.
10. The method for machining the tip of the single turbine blade according to claim 1, wherein the step S4 includes the steps of:
s4.1, disassembling the turbine blade and the turbine disc, filing the surface of the blade tip with oilstone, and removing burrs;
s4.2: disassembling the medical adhesive plaster, cleaning the blade again by absolute alcohol, and checking whether the air film hole on the surface of the blade is blocked;
s4.3: and wrapping the cleaned turbine blades by using oil seal paper, and putting the wrapped turbine blades into a special turnover box for storage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111223557.8A CN114055102B (en) | 2021-10-20 | 2021-10-20 | Single turbine blade tip machining method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111223557.8A CN114055102B (en) | 2021-10-20 | 2021-10-20 | Single turbine blade tip machining method |
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| CN114055102A true CN114055102A (en) | 2022-02-18 |
| CN114055102B CN114055102B (en) | 2023-03-07 |
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Citations (10)
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| JP2005069018A (en) * | 2003-08-26 | 2005-03-17 | Fuji Electric Systems Co Ltd | Steam turbine rotor |
| CN101160452A (en) * | 2005-03-24 | 2008-04-09 | 西门子迪马格德拉瓦尔涡轮机器公司 | Locking arrangement for radial entry turbine blades |
| CN201863020U (en) * | 2010-10-27 | 2011-06-15 | 中国北车集团大连机车研究所有限公司 | Drilling clamp for turbocharger turbine disk |
| US20130156590A1 (en) * | 2010-06-25 | 2013-06-20 | Snecma | Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping |
| CN205271486U (en) * | 2015-12-21 | 2016-06-01 | 中国燃气涡轮研究院 | Whole bladed disk's of processing aeroengine anchor clamps |
| CN106767239A (en) * | 2016-11-29 | 2017-05-31 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of turbine disk assembling assembly blade installation site measurement apparatus |
| CN107498428A (en) * | 2017-09-21 | 2017-12-22 | 湖南南方通用航空发动机有限公司 | Engine blower rotator tip organisation of working |
| CN210475699U (en) * | 2019-07-11 | 2020-05-08 | 嘉兴恒瑞动力有限公司 | Clamp for broaching mortise sample block |
| CN111173570A (en) * | 2019-12-30 | 2020-05-19 | 中国南方航空股份有限公司 | Method for replacing turbine blade |
| CN214250824U (en) * | 2021-03-30 | 2021-09-21 | 中国航发商用航空发动机有限责任公司 | Blade tip diameter measuring tool |
-
2021
- 2021-10-20 CN CN202111223557.8A patent/CN114055102B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005069018A (en) * | 2003-08-26 | 2005-03-17 | Fuji Electric Systems Co Ltd | Steam turbine rotor |
| CN101160452A (en) * | 2005-03-24 | 2008-04-09 | 西门子迪马格德拉瓦尔涡轮机器公司 | Locking arrangement for radial entry turbine blades |
| US20130156590A1 (en) * | 2010-06-25 | 2013-06-20 | Snecma | Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping |
| CN201863020U (en) * | 2010-10-27 | 2011-06-15 | 中国北车集团大连机车研究所有限公司 | Drilling clamp for turbocharger turbine disk |
| CN205271486U (en) * | 2015-12-21 | 2016-06-01 | 中国燃气涡轮研究院 | Whole bladed disk's of processing aeroengine anchor clamps |
| CN106767239A (en) * | 2016-11-29 | 2017-05-31 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of turbine disk assembling assembly blade installation site measurement apparatus |
| CN107498428A (en) * | 2017-09-21 | 2017-12-22 | 湖南南方通用航空发动机有限公司 | Engine blower rotator tip organisation of working |
| CN210475699U (en) * | 2019-07-11 | 2020-05-08 | 嘉兴恒瑞动力有限公司 | Clamp for broaching mortise sample block |
| CN111173570A (en) * | 2019-12-30 | 2020-05-19 | 中国南方航空股份有限公司 | Method for replacing turbine blade |
| CN214250824U (en) * | 2021-03-30 | 2021-09-21 | 中国航发商用航空发动机有限责任公司 | Blade tip diameter measuring tool |
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