CN102825524B - A kind of ultra-thin elongated moving turbine blade finishing, machine add localization method - Google Patents
A kind of ultra-thin elongated moving turbine blade finishing, machine add localization method Download PDFInfo
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- CN102825524B CN102825524B CN201210236884.1A CN201210236884A CN102825524B CN 102825524 B CN102825524 B CN 102825524B CN 201210236884 A CN201210236884 A CN 201210236884A CN 102825524 B CN102825524 B CN 102825524B
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Abstract
A kind of ultra-thin elongated moving turbine blade finishing, machine add localization method: it adopts " 5 add one side " localization method, specific requirement is as follows: on blade, selected A1, A2, A3, B1, C1 are point location five elements, is decided to be " integral shroud positioning reference plane M " by the non-machined surface near exhaust limit integral shroud; Wherein: A1, A2 are two anchor points on blade back tenon tooth extension, and A3 is the anchor point on blade back four cross section, A1, A2, A3 3 fixing Y-directions; B1 is a bit on the non-machined surface of tenon tooth side, together fixes X-direction with " integral shroud positioning reference plane M "; C1 is a bit on integral shroud internal channel, fixing Z-direction.Blade roughcast profile finishing detection of the present invention and machine add and adopt same positioning datum, avoid the machine added-time to turn location and produce error, shorten the process-cycle of blade, enhance productivity.
Description
Technical field
The present invention relates to Machining Technology field, specifically provide a kind of ultra-thin elongated moving turbine blade finishing, machine adds localization method.
Background technology
Large-scale military transport engine is the following type of China's aero-engine, has important strategic position.Solve and grasp ultra-thin, narrow string, slender construction, suppress distortion without surplus orientation works blade, machine adds the key manufacture of precision positioning, to meet the needs that new work engine manufactures.
In prior art, ultra-thin, narrow string, elongated, very high without finished machined (specifically comprising orthopedic, the profile refine of the blade etc.) technical requirement of operation after surplus directional solidification working-blade, the precision positioning of blade and the adjustment of machined location are all key problem in technology places for correlation technique.In large-scale military transport engine, low-pressure turbine working-blade requires can Long-Time Service below 1000 DEG C, and it is the technology that people catch at always that the ultra-thin elongated moving turbine blade finishing being representative with it, machine add localization method.
Summary of the invention
The object of this invention is to provide the excellent ultra-thin elongated moving turbine blade finishing of a kind of technique effect, machine adds localization method.
The invention provides a kind of ultra-thin elongated moving turbine blade finishing, machine adds localization method, it is characterized in that: it adopts " 5 add one side " localization method, specific requirement is as follows:
On blade, Chosen Point A1, some A2, some A3, some B1, some C1 are point location five elements, and the non-machined surface near exhaust limit integral shroud is decided to be " integral shroud positioning reference plane M "; Wherein: some A1, some A2 are two anchor points on blade back tenon tooth extension, and some A3 is the anchor point on blade back four cross section (near integral shroud), some A1, some A2, some A3 3 fixing Y-directions; Point B1 is a bit on tenon tooth side (exhaust edge direction) non-machined surface, together fixes X-direction with " integral shroud positioning reference plane M "; Point C1 is a bit on integral shroud internal channel, fixing Z-direction; Fig. 1 is seen in the position of anchor point.
Adopt blade locking device to carry out auxiliary positioning, described blade locking device is constructed as follows: bearing, integral shroud locking device, blade positioner etc., specifically see accompanying drawing 8,9,10.
Ultra-thin elongated moving turbine blade finishing of the present invention, machine add localization method, it is characterized in that: adopt some A1, some A2, some A3, some B1, some C1 5 to add " integral shroud positioning reference plane M " location, ensure the position degree of between the non-machined surface of integral shroud (comprising the resistance to roll flute in hat top) and the non-machined surface of listrium 4 ° 57 ', and be convenient to the rectification of blade profile.
The vane machine added-time adopts the positioning datum identical with the finishing of Blade roughcast profile, comprises blade precision positioning, tenon tooth grinding, integral shroud (comprising after integral shroud welding wear-resistant layer) grinding; With the error avoiding the machine added-time to turn location generation, shorten the process-cycle of blade, the machine improving blade adds efficiency.
The present invention be particularly useful for ultra-thin, narrow string, elongated, without finished machined (specifically comprising orthopedic, profile refine of blade the etc.) process of operation after surplus directional solidification working-blade.
Have in ultra-thin, narrow string, slender construction, manufacture process for blade very easily twist, the feature of buckling deformation, for suppressing the distortion in leaf blade manufacture process, the orthopedic difficulty of solution Blade roughcast, vane machine add the problem of precision positioning difficulty in process, the way that the blade " 6 points " that breaks traditions is located, adopts the process that this " add one side " locates at 5.Ensure the requirement of blade profile size conforms design drawing, the finishing detection of Blade roughcast profile and machine add and adopt same positioning datum, avoid the machine added-time to turn location generation error, the process-cycle of shortening blade, enhance productivity.
The present invention is applied to ultra-thin, narrow string, elongated, without the rear operation finishing of surplus working-blade, molding surface size 100% meets design drawing requirement.The finishing detection of Blade roughcast profile and machine add and adopt same positioning datum, avoid the machine added-time to turn the error that location produces, from the effect that machine adds, and efficient 100%, also shorten the process-cycle of blade simultaneously, improve production efficiency.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is one of the position principle schematic (blade construction figure) of blade anchor point, locating surface;
Fig. 2 is the position principle schematic two of blade anchor point, locating surface;
Fig. 3 is the position principle schematic three of blade anchor point, locating surface;
The position degree principle schematic of 4 ° 57 ' between Fig. 4 integral shroud and listrium;
One of torsion schematic diagram between Fig. 5 integral shroud and datum level M (the right torsional deflection of blade);
Torsion schematic diagram two (blade left handed twist is out of shape) between Fig. 6 integral shroud and datum level M;
Torsion schematic diagram three (blade is qualified) between Fig. 7 integral shroud and datum level M;
Fig. 8 is " 5 add one side " positioner principle of compositionality schematic diagram;
Fig. 9 is the A-A figure of Fig. 8;
Figure 10 is the B-B figure of Fig. 8.
Detailed description of the invention
Embodiment 1
A kind of ultra-thin elongated moving turbine blade finishing, machine add localization method, it adopts " 5 add one side " localization method, and specific requirement is as follows:
On blade, Chosen Point A1, some A2, some A3, some B1, some C1 are point location five elements, and the non-machined surface near exhaust limit integral shroud is decided to be " integral shroud positioning reference plane M "; Wherein: some A1, some A2 are two anchor points on blade back tenon tooth extension, and some A3 is the anchor point on blade back four cross section (near integral shroud), some A1, some A2, some A3 3 fixing Y-directions; Point B1 is a bit on tenon tooth side (exhaust edge direction) non-machined surface, together fixes X-direction with " integral shroud positioning reference plane M "; Point C1 is a bit on integral shroud internal channel, fixing Z-direction; Fig. 1 is seen in the position of anchor point.
Adopt blade locking device to carry out auxiliary positioning, described blade locking device is constructed as follows: bearing, integral shroud locking device, blade positioner etc., specifically see accompanying drawing 8,9,10.
Described in the present embodiment, ultra-thin elongated moving turbine blade finishing, machine add localization method, it is characterized in that: adopt some A1, some A2, some A3, some B1, some C1 5 to add " integral shroud positioning reference plane M " location, ensure the position degree of between the non-machined surface of integral shroud (comprising the resistance to roll flute in hat top) and the non-machined surface of listrium 4 ° 57 ', and be convenient to the rectification of blade profile.
The vane machine added-time adopts the positioning datum identical with the finishing of Blade roughcast profile, comprises blade precision positioning, tenon tooth grinding, integral shroud (comprising after integral shroud welding wear-resistant layer) grinding; With the error avoiding the machine added-time to turn location generation, shorten the process-cycle of blade, the machine improving blade adds efficiency.
The present embodiment be particularly useful for ultra-thin, narrow string, elongated, without finished machined (specifically comprising orthopedic, profile refine of blade the etc.) process of operation after surplus directional solidification working-blade.
Have in ultra-thin, narrow string, slender construction, manufacture process for blade very easily twist, the feature of buckling deformation, for suppressing the distortion in leaf blade manufacture process, the orthopedic difficulty of solution Blade roughcast, vane machine add the problem of precision positioning difficulty in process, the way that the blade " 6 points " that breaks traditions is located, adopts the process that this " add one side " locates at 5.Ensure the requirement of blade profile size conforms design drawing, the finishing detection of Blade roughcast profile and machine add and adopt same positioning datum, avoid the machine added-time to turn location generation error, the process-cycle of shortening blade, enhance productivity.
The present embodiment is applied to ultra-thin, narrow string, elongated, without the rear operation finishing of surplus working-blade, molding surface size 100% meets design drawing requirement.The finishing detection of Blade roughcast profile and machine add and adopt same positioning datum, avoid the machine added-time to turn the error that location produces, from the effect that machine adds, and efficient 100%, also shorten the process-cycle of blade simultaneously, improve production efficiency.
Claims (2)
1. ultra-thin elongated moving turbine blade finishing, machine add a localization method, it adopts " 5 add one side " localization method, and specific requirement is as follows:
On blade, Chosen Point A1, some A2, some A3, some B1, some C1 are point location five elements, and the non-machined surface near exhaust limit integral shroud is decided to be " integral shroud positioning reference plane M "; Wherein: some A1, some A2 are two anchor points on blade back tenon tooth extension, and some A3 is the anchor point on blade back four cross section, some A1, some A2, some A3 3 fixing Y-directions; Point B1 is a bit on the non-machined surface of tenon tooth side, together fixes X-direction with " integral shroud positioning reference plane M "; Point C1 is a bit on integral shroud internal channel, fixing Z-direction; It is characterized in that:
Adopt some A1, some A2, some A3, some B1, some C1 5 to add " integral shroud positioning reference plane M " location, ensure the position degree of between the non-machined surface of integral shroud and the non-machined surface of listrium 4 ° 57 ', and be convenient to the rectification of blade profile.
2. add localization method according to elongated moving turbine blade finishing ultra-thin described in claim 1, machine, it is characterized in that: the vane machine added-time adopts the positioning datum identical with the finishing of Blade roughcast profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210236884.1A CN102825524B (en) | 2012-07-09 | 2012-07-09 | A kind of ultra-thin elongated moving turbine blade finishing, machine add localization method |
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| CN201210236884.1A CN102825524B (en) | 2012-07-09 | 2012-07-09 | A kind of ultra-thin elongated moving turbine blade finishing, machine add localization method |
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| CN102825524A CN102825524A (en) | 2012-12-19 |
| CN102825524B true CN102825524B (en) | 2016-02-24 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105583672B (en) * | 2014-10-23 | 2018-01-23 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of localization method of conjuncted guide vane |
| CN106767324B (en) * | 2016-11-11 | 2019-08-02 | 四川成发航空科技股份有限公司 | For measuring the spacing device in blade of aviation engine type face |
| CN107570937B (en) * | 2017-09-28 | 2019-06-04 | 中国航发动力股份有限公司 | A kind of turbo blade inert gas welding positioning device |
| CN111215930B (en) * | 2019-11-14 | 2021-11-02 | 哈尔滨飞机工业集团有限责任公司 | Finish machining positioning device and method for composite material blade fatigue test piece |
| CN110834081B (en) * | 2019-11-26 | 2021-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | Multipurpose linear cutting clamp for single crystal blade with crown and cutting method thereof |
| CN113664665B (en) * | 2021-08-25 | 2022-09-20 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for setting positioning reference of working blade of isometric crystal low-pressure turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3331166A (en) * | 1964-11-27 | 1967-07-18 | Brenning Albert | Jig for grinding turbine blades of jet engines |
| US4128929A (en) * | 1977-03-15 | 1978-12-12 | Demusis Ralph T | Method of restoring worn turbine components |
| US6017263A (en) * | 1996-04-30 | 2000-01-25 | United Technologies Corporation | Method for manufacturing precisely shaped parts |
| CN1788927A (en) * | 2005-11-18 | 2006-06-21 | 沈阳黎明航空发动机(集团)有限责任公司 | Six point positioning base line transfer method for refine casting blade |
| CN101767286A (en) * | 2008-12-30 | 2010-07-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Finishing and machining locating process method of high- pressure turbine working blade |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4929156B2 (en) * | 2005-03-09 | 2012-05-09 | 株式会社Ｉｈｉ | jig |
| US7762004B2 (en) * | 2007-01-31 | 2010-07-27 | General Electric Company | Inspection tool for measuring bucket Z notch position |
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- 2012-07-09 CN CN201210236884.1A patent/CN102825524B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3331166A (en) * | 1964-11-27 | 1967-07-18 | Brenning Albert | Jig for grinding turbine blades of jet engines |
| US4128929A (en) * | 1977-03-15 | 1978-12-12 | Demusis Ralph T | Method of restoring worn turbine components |
| US6017263A (en) * | 1996-04-30 | 2000-01-25 | United Technologies Corporation | Method for manufacturing precisely shaped parts |
| CN1788927A (en) * | 2005-11-18 | 2006-06-21 | 沈阳黎明航空发动机(集团)有限责任公司 | Six point positioning base line transfer method for refine casting blade |
| CN101767286A (en) * | 2008-12-30 | 2010-07-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Finishing and machining locating process method of high- pressure turbine working blade |
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| CN102825524A (en) | 2012-12-19 |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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Granted publication date: 20160224 Termination date: 20210709 |
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