CN105312864A - Machining method of turbine working blade - Google Patents
Machining method of turbine working blade Download PDFInfo
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- CN105312864A CN105312864A CN201510899892.8A CN201510899892A CN105312864A CN 105312864 A CN105312864 A CN 105312864A CN 201510899892 A CN201510899892 A CN 201510899892A CN 105312864 A CN105312864 A CN 105312864A
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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
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Abstract
The invention discloses a machining method of a turbine working blade, which comprises the following steps: a, unifying positioning standards of a turbine working blade blank and turbine working blade machining; b, fixing and positioning the turbine working blade blank, and performing machining according to the positioning standards; c, performing grinding to form tenon teeth, positioning machined tenon teeth, machining an upper edge plate and a lower edge plate of the turbine working blade and sawteeth of a blade tip shroud; and d, performing heat treatment and shot blasting of the machined turbine working blade to form the turbine working blade. Machining and blank standards are unified to realize the consistency of a blank mould positioning point and a machined tenon positioning point, so that an error caused by standard disunity is eliminated, the frequency of standard conversion is reduced, the conversion precision is increased, and the designed blade profile positional tolerance requirement is met; and the precision of coordinate positional tolerance evaluated by building a standard after machining is improved. The machining method is suitable for technological equipment and manufacturing of aero-engine turbine working blades.
Description
Technical field
The present invention relates to aero-engine technological equipment and manufacturing technology field, especially, relate to a kind of processing method of moving turbine blade.
Background technology
Novel engine blade raising engine performance while also for process technology brings a new difficult problem.Blade profile position degree in machining, established angle, integral shroud sawtooth equidimension are interrelated, and precision is high, and it is completely qualified to be difficult to be able to.Wherein key factor is that precision positioning is difficult, and add multiple conversions from blank to machine after, accumulated error has exceeded the required precision of blade itself, and these become present stage limit product quality and the key factor of qualification rate.
Novel engine blade project organization is complicated, and blade is space curved surface, and tenon tooth is fir-tree type structure, and integral shroud is with the zigzag of complexity.In addition, the similar power turbine working-blade tenon tooth more in the past processed decrease half across excellent size, length really adds one times, and the thickness of blade profile is also significantly thinning.This little tenon tooth, the feature of long thin-walled is subsequent mechanical processing, detection brings new challenge.Blank this as blade without surplus hot investment casting part, wherein machine adds position and mainly contains tenon tooth, tenon both ends of the surface, listrium four side, leaf basin, back of the body both sides sawtooth.
Existing moving turbine blade processing method: upper and lower two place's listriums of first machining blade, one is blank blade profile benchmark is transformed into machine add on listrium, two is the upper and lower square listriums processing convenient location, to facilitate clamping part benchmark (reference for assembling) the tenon tenon tooth that processing is final further.Locate with the tenon tooth processed again and again process inframarginal inclined-plane size and integral shroud sawtooth, complete final part blade profile position degree size and integral shroud size.Processing listrium method is that blank blade four mathematical points selected do measurement point, and grinding upper and lower listrium face special measuring tool and standard component comparison record to four measurement point values.
The shortcoming of prior art is: the method operation is loaded down with trivial details, efficiency is low; Blank and machine add benchmark disunity, and need Blade measuring, calculating and adjustment one by one, precision is low; Benchmark needs twice conversion to cause accumulated error large, and it is easily overproof that machine adds rear size.This processing method is easily subject to the impact of actual blade profile profile, in order to ensure equivalent, needs established angle to carry out angle adjustment.Blade blank Reference Transforming on listrium, and then is converted to tenon tooth from listrium, and Reference Transforming accumulated error far exceedes machine and adds precision prescribed own.So in actual processing often rough benchmark check that part is qualified, record part in equivalent processing qualified, after tenon tooth grinding with final smart benchmaring blade profile position degree and established angle overproof.Set up centre axis Z when three-dimensional gauge check with tenon tooth both sides roller location, be not more than 0.01 offsetting because tenon tooth itself exists, this error has a strong impact on the accuracy that long thin wall vane Z axis is set up.Suppose that both sides tenon tooth offsets as limiting condition 0.01, such Z axis reaches 0.22 in blade tip position and real Z axis position deviation, sees that 4.1.2 describes in detail.So the method that the independent tenon tooth of tradition sets up coordinate basis be not just suitable for.
Summary of the invention
The invention provides a kind of processing method of moving turbine blade, to solve existing moving turbine blade processing method, location degree and the overproof problem of established angle, tenon tooth offsets and there is to blade profile benchmark the technical problem that mistake judges.
The invention provides a kind of processing method of moving turbine blade, comprise the following steps: a, unified moving turbine blade blank and the mach positioning datum of moving turbine blade blank; B, location is fixed to moving turbine blade blank, and processes according to positioning datum; The tenon tooth of c, grinding formation moving turbine blade, positions to process tenon tooth, processes the sawtooth of the supramarginal plate of moving turbine blade, inframarginal and integral shroud; Moving turbine blade after d, processing is heat-treated and shot-peening, forms shaping moving turbine blade.
Further, the concrete procedure of processing of step c is: two sawtooth of two inclined-planes of the leaf basin inframarginal of processing moving turbine blade, two inclined-planes processing blade back inframarginal and processing integral shroud.
Further, in step a, the determination concrete steps of positioning datum are as follows: determine A1 point and A2 point respectively at the blade leading edge of moving turbine blade and the inside 2mm-5mm place of plate edge of blade exhaust limit both direction, and A1 point and A2 point are chosen to increase the distance between 2 respectively to end position, determine the X-direction of coordinate with A1 point and A2 point; Based on X-axis, and draw Y direction and Z-direction according to the processing entity of moving turbine blade blank, thus set up three-dimensional coordinate system.
Further, X-axis intercepts the blade tip cross section of moving turbine blade blank, get the convex surface tangent line peak in blade tip cross section as A3 point; A3 point is in the centre position of back of the body arc tolerance band, to make the theoretical curve of back of the body arc drop in back of the body arc tolerance band, thus ensures machining accuracy.
Further, B1 point and B2 point is chosen respectively in the supramarginal plate centre position in moving turbine blade leading edge direction and inframarginal centre position; B1 point and B2 are respectively at the listrium mid-depth of present position short transverse.
Further, choose a bit as C1 point in the region that moving turbine blade inframarginal exhaust edge direction upper periphery space is maximum; Using C1 point as radial reference, prop up for follow-up machining fixture alignment pin and lean on.
Further, five one lines are selected according to moving turbine blade blank dimension; The movement of moving turbine blade blank Y-axis and the rotation of XY plane and YZ plane is limited with A1 point, A2 point and A3 point; The movement of X-axis and the rotation of XZ plane is limited with B1 point and B2 point; With the movement of C1 point restriction Z axis.
Further, using a line of A1 point, A2 point, B1 point, B2 point, 5 of C1 point and blade tip cross section back of the body camber line as moving turbine blade blank and the mach positioning datum of moving turbine blade blank.
Further, during grinding tenon tooth, the position degree ensureing to grind the relative blade profile center of tenon tooth come closes and ties up to XY coordinate plane ± 0.28mm; During the sawtooth of grinding integral shroud, ensure coordinate system reference position degree ± 0.02mm that the relative tenon tooth of the size of sawtooth is set up; The sawtooth of grinding tenon tooth and grinding integral shroud is creep feed grinding.
Further, clamping device when processing tenon tooth comprises chuck body, for the pressure head of each positioning datum point of fixed turbine working-blade blank, for clamping the housing screw of moving turbine blade blank and the governor motion for finely tuning each positioning datum point; Clamping device during processing blade comprises firm banking, and firm banking is provided with chuck for clamping tenon tooth, in order to from the support member of moving turbine blade blank bottom support moving turbine blade blank, for the steel band from moving turbine blade blank side direction fixed turbine working-blade blank and positioned opposite and be resisted against the backing pin of the integral shroud sawtooth end of moving turbine blade blank with chuck; Clamping device after tenon tooth completion of processing comprises fixed platform, be located in fixed platform and for the support supporting moving turbine blade blank, the teeth groove folder be held on by roller in the teeth groove of tenon tooth.
The present invention has following beneficial effect:
The processing method of moving turbine blade of the present invention, machine is added with rough benchmark unified, it is consistent that the anchor point of the die for blank of realization and machine add tenon tooth anchor point, eliminate the skimble-scamble error of benchmark, so just the three cover frames of reference in blank inspection in the past-part processing-part checking process are reduced to blank inspection, the processing two cover frame of reference, decrease the number of times that benchmark transforms, improve conversion accuracy, reach the blade profile position degree requirement of design; With blank measuring basis positioning and clamping blade, directly process tenon tooth; With the clamping of tenon tooth location, processing inlet and outlet side tenon end surface and tenon tooth top; Clamping is added, processing each of inframarginal with tenon tooth location; Add clamping with tenon tooth location, processing integral shroud sawtooth, achieves accurately determining of the position relationship of tenon tooth and integral shroud, tenon tooth and blade, and the precision of the coordinate position degree that raising is set up benchmark after processing and evaluated, controls within the 0.28mm of theoretical position.Be applicable to technological equipment and the manufacture of aero-turbine working-blade.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structured flowchart of the processing method of the moving turbine blade of the preferred embodiment of the present invention;
Fig. 2 is the structural representation of the moving turbine blade blank of the preferred embodiment of the present invention;
Fig. 3 is one of structural representation of five one lines foundation of the preferred embodiment of the present invention;
Fig. 4 is the structural representation two that five one lines of the preferred embodiment of the present invention are set up;
The structural representation of clamping device when Fig. 5 is the processing tenon tooth of the preferred embodiment of the present invention;
Fig. 6 is the left view of Fig. 5;
Fig. 7 is the rearview of Fig. 5;
The structural representation of clamping device when Fig. 8 is the processing blade of the preferred embodiment of the present invention;
The structural representation of clamping device when Fig. 9 is the processing tenon tooth of the preferred embodiment of the present invention;
Figure 10 is the rearview of Fig. 9.
Marginal data:
1, chuck body; 2, pressure head; 3, housing screw; 4, governor motion; 5, firm banking; 6, chuck; 7, support member; 8, steel band; 9, backing pin; 10, fixed platform; 11, support; 12, roller; 13, teeth groove folder; 14, moving turbine blade blank.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the present invention can be implemented by following the multitude of different ways limiting and cover.
Fig. 1 is the structured flowchart of the processing method of the moving turbine blade of the preferred embodiment of the present invention; Fig. 2 is the structural representation of the moving turbine blade blank of the preferred embodiment of the present invention; Fig. 3 is one of structural representation of five one lines foundation of the preferred embodiment of the present invention; Fig. 4 is the structural representation two that five one lines of the preferred embodiment of the present invention are set up; The structural representation of clamping device when Fig. 5 is the processing tenon tooth of the preferred embodiment of the present invention; Fig. 6 is the left view of Fig. 5; Fig. 7 is the rearview of Fig. 5; The structural representation of clamping device when Fig. 8 is the processing blade of the preferred embodiment of the present invention; The structural representation of clamping device when Fig. 9 is the processing tenon tooth of the preferred embodiment of the present invention; Figure 10 is the rearview of Fig. 9.
As shown in Figure 1, the processing method of the moving turbine blade of the present embodiment, comprises the following steps: a, unified moving turbine blade blank 14 and the mach positioning datum of moving turbine blade blank 14; B, location is fixed to moving turbine blade blank 14, and processes according to positioning datum; The tenon tooth of c, grinding formation moving turbine blade, positions to process tenon tooth, processes the sawtooth of the supramarginal plate of moving turbine blade, inframarginal and integral shroud; Moving turbine blade after d, processing is heat-treated and shot-peening, forms shaping moving turbine blade.The processing method of moving turbine blade of the present invention, machine is added with rough benchmark unified, it is consistent that the anchor point of the die for blank of realization and machine add tenon tooth anchor point, eliminate the skimble-scamble error of benchmark, so just the three cover frames of reference in blank inspection in the past-part processing-part checking process are reduced to blank inspection, the processing two cover frame of reference, decrease the number of times that benchmark transforms, improve conversion accuracy, reach the blade profile position degree requirement of design; With blank measuring basis positioning and clamping blade, directly process tenon tooth; With the clamping of tenon tooth location, processing inlet and outlet side tenon end surface and tenon tooth top; Clamping is added, processing each of inframarginal with tenon tooth location; Add clamping with tenon tooth location, processing integral shroud sawtooth, achieves accurately determining of the position relationship of tenon tooth and integral shroud, tenon tooth and blade, and the precision of the coordinate position degree that raising is set up benchmark after processing and evaluated, controls within the 0.28mm of theoretical position.Be applicable to technological equipment and the manufacture of aero-turbine working-blade.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, in the present embodiment, the concrete procedure of processing of step c is: two sawtooth of two inclined-planes of the leaf basin inframarginal of processing moving turbine blade, two inclined-planes processing blade back inframarginal and processing integral shroud.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, in step a, the determination concrete steps of positioning datum are as follows: determine A1 point and A2 point respectively at the blade leading edge of moving turbine blade and the inside 2mm-5mm place of plate edge of blade exhaust limit both direction.A1 point and A2 point are chosen to increase the distance between 2 respectively to end position, determine the X-direction of coordinate with A1 point and A2 point.Based on X-axis, and draw Y direction and Z-direction according to the processing entity of moving turbine blade blank 14, thus set up three-dimensional coordinate system.
As shown in Figure 1, Figure 2 and Figure 4, in the present embodiment, X-axis intercepts the blade tip cross section of moving turbine blade blank 14, get the convex surface tangent line peak in blade tip cross section as A3 point.A3 point is in the centre position of back of the body arc tolerance band, to make the theoretical curve of back of the body arc drop in back of the body arc tolerance band, thus ensures machining accuracy.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, choose B1 point and B2 point respectively in the supramarginal plate centre position in moving turbine blade leading edge direction and inframarginal centre position.B1 point and B2 are respectively at the listrium mid-depth of present position short transverse.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the region maximum in moving turbine blade inframarginal exhaust edge direction upper periphery space is chosen a bit as C1 point.Using C1 point as radial reference, prop up for follow-up machining fixture alignment pin and lean on.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, in the present embodiment, according to moving turbine blade blank 14 size Selection five line.The movement of moving turbine blade blank 14Y axle and the rotation of XY plane and YZ plane is limited with A1 point, A2 point and A3 point.The movement of X-axis and the rotation of XZ plane is limited with B1 point and B2 point.With the movement of C1 point restriction Z axis.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, in the present embodiment, using a line of A1 point, A2 point, B1 point, B2 point, 5 of C1 point and blade tip cross section back of the body camber line as moving turbine blade blank 14 and the mach positioning datum of moving turbine blade blank 14.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, in the present embodiment, during grinding tenon tooth, the position degree ensureing to grind the relative blade profile center of tenon tooth come closes and ties up to XY coordinate plane ± 0.28mm.During the sawtooth of grinding integral shroud, ensure coordinate system reference position degree ± 0.02mm that the relative tenon tooth of the size of sawtooth is set up.The sawtooth of grinding tenon tooth and grinding integral shroud is creep feed grinding.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, in the present embodiment, clamping device during processing tenon tooth comprises chuck body 1, for the pressure head 2 of each positioning datum point of fixed turbine working-blade blank 14, for clamping the housing screw 3 of moving turbine blade blank 14 and the governor motion 4 for finely tuning each positioning datum point.Clamping device during processing blade comprises firm banking 5, and firm banking 5 is provided with chuck 6 for clamping tenon tooth, in order to from the support member 7 of moving turbine blade blank 14 bottom support moving turbine blade blank 14, for the steel band 8 from moving turbine blade blank 14 side direction fixed turbine working-blade blank 14 and positioned opposite and be resisted against the backing pin 9 of the integral shroud sawtooth end of moving turbine blade blank 14 with chuck 6.Clamping device after tenon tooth completion of processing comprises fixed platform 10, be located in fixed platform 10 and for the support 11 supporting moving turbine blade blank 14, the teeth groove folder 13 be held on by roller 12 in the teeth groove of tenon tooth.
During enforcement, provide a kind of processing method of moving turbine blade.Concrete step: A1 point, A2 point coordinates X-direction are chosen for the inside 3mm place of both direction listrium, blade inlet and outlet limit, principle is as far as possible near end positions, increases distance between two points; Y-direction and Z-direction then really fix on blank entity according to X-coordinate and draw.A3 point coordinates is chosen for A1 point, A2 point in the same way, to be on blade tip cross section and with the parallel lines of A1 point, A2 point line, tangent line peak is defined as A3 point, and is carry on the back on the centre position of arc tolerance band, and the theoretical curve carrying on the back arc like this drops in tolerance range and ensures machining accuracy.B1 point, B2 point are chosen for upper and lower listrium centre position, leading edge direction, the listrium mid-depth of short transverse.C1 point coordinates is that larger region, inframarginal exhaust edge direction space is chosen a bit as radial reference, facilitates follow-up machine to add clamp locating pin and props up and lean on.Move and X, Y plane Y, Z Plane Rotation according to the A3 point limit feature Y that blank accessory size selects A1 point, A2 point and blade tangent line to cross.B1 point, B2 point restriction X-direction moves and X, Z Plane Rotation, and C1 point restriction Z moves.
The main points one of processing: the position degree ensureing to grind the tenon tooth relative blade profile center come during mill tenon closes and ties up to X, Y Two Ge plane ± 0.28mm; The main points two of processing: when grinding the sawtooth pattern of integral shroud, ensure the coordinate system benchmark that the relative tenon tooth of the size of sawtooth is set up, position degree ± 0.02mm; Processing method is all creep feed grinding.
Because blank is blade profile precision castings, appearance and size is organic to be added and casts common formation, inevitably has the transformed error that Reference Transforming brings.For reducing error and truly reflect part status as far as possible, first the benchmark that unified blank and machine add, adopt leading edge direction upper and lower listrium B1 point and B2 point, radial passage point to add the A3 point that on blade back inframarginal A1 point, A2 point and blade, tangent line is fixed, 5 add one line control blank X, Y, the movement of Z-direction and the rotation around X, Y, Z-direction.Add a line location grinding tenon tooth with 5, then with tenon tooth location processing leaf basin, blade back inframarginal two inclined-plane, integral shroud two sawtooth, the one-shot forming of each position, fixture adopts tenon tooth precision positioning and blade A3 point auxiliary positioning mode.Processing route is as follows:
Machine add with rough benchmark after reunification, it is consistent that the anchor point of the die for blank of realization and machine add tenon tooth anchor point, eliminate the skimble-scamble error of benchmark, so just the three cover frames of reference in blank inspection in the past-part processing-part checking process are reduced to blank inspection (part processing)-part and check the two cover frames of reference, decrease the number of times that benchmark transforms, improve conversion accuracy, reach the blade profile position degree requirement of design.With blank measuring basis positioning and clamping blade, directly process tenon tooth; With the clamping of tenon tooth location, processing inlet and outlet side tenon end surface and tenon tooth top; Clamping is added, processing each of inframarginal with tenon tooth location; Clamping is added, processing integral shroud sawtooth with tenon tooth location.
The detection of part after processing
The impact of tenon tooth offsetting amount can be subject to merely with the Z axis that tenon tooth roller defines part by the data moving turbine blade shown for little tenon tooth, long thin-walled.Measure out part blade profile size to occur more toward the illusion that blade tip is more overproof, reason is that three-dimensional definition two is the long-pending folded axle Z axis of part across the Central Symmetry face of rod, each part can cause the position of Z axis and the reality set up to there is the deviation of certain angle because of the error of respective tenon tooth own like this, and this deviation can be amplified along with the increase of blade height.Therefore, when using three-dimensional to set up the long-pending folded axle of vane foil, jointly determine that the Z plane of part can be more accurate and true with the roller of tenon tooth both sides and blade A3 point.Roller only defines the circumference of part, is defined his angle by blade A3 point, and A3 point draws by accurately calculating tangential direction point behind scanning blade tip cross section.Prove in actual production, this two add the locate mode of a line for the most reasonably to set up coordinate system method across rod.Achieve the position relationship of tenon tooth and integral shroud, tenon tooth and blade after scheme implementation, the precision of X, Y position degree set up benchmark and evaluate with tenon tooth and A3 after improving processing, controls within 0.28 of theoretical position.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a processing method for moving turbine blade, is characterized in that, comprises the following steps:
A, unified moving turbine blade blank (14) and moving turbine blade blank (14) mach positioning datum;
B, location is fixed to moving turbine blade blank (14), and processes according to positioning datum;
The tenon tooth of c, grinding formation moving turbine blade, positions to process tenon tooth, processes the sawtooth of the supramarginal plate of moving turbine blade, inframarginal and integral shroud;
Moving turbine blade after d, processing is heat-treated and shot-peening, forms shaping moving turbine blade.
2. the processing method of moving turbine blade according to claim 1, is characterized in that,
The concrete procedure of processing of described step c is:
Two sawtooth of two inclined-planes of the leaf basin inframarginal of processing moving turbine blade, two inclined-planes processing blade back inframarginal and processing integral shroud.
3. the processing method of moving turbine blade according to claim 1, is characterized in that,
In described step a, the determination concrete steps of positioning datum are as follows:
A1 point and A2 point is determined respectively at the blade leading edge of moving turbine blade and the inside 2mm-5mm place of plate edge of blade exhaust limit both direction, and A1 point and A2 point are chosen to increase the distance between 2 respectively to end position, determine the X-direction of coordinate with A1 point and A2 point;
Based on X-axis, and draw Y direction and Z-direction according to the processing entity of moving turbine blade blank (14), thus set up three-dimensional coordinate system.
4. the processing method of moving turbine blade according to claim 3, is characterized in that,
X-axis intercepts the blade tip cross section of moving turbine blade blank (14), gets the convex surface tangent line peak in blade tip cross section as A3 point;
A3 point is in the centre position of back of the body arc tolerance band, to make the theoretical curve of back of the body arc drop in back of the body arc tolerance band, thus ensures machining accuracy.
5. the processing method of moving turbine blade according to claim 4, is characterized in that,
B1 point and B2 point is chosen respectively in the supramarginal plate centre position in moving turbine blade leading edge direction and inframarginal centre position;
B1 point and B2 are respectively at the listrium mid-depth of present position short transverse.
6. the processing method of moving turbine blade according to claim 5, is characterized in that,
The region maximum in moving turbine blade inframarginal exhaust edge direction upper periphery space is chosen a bit as C1 point;
Using C1 point as radial reference, prop up for follow-up machining fixture alignment pin and lean on.
7. the processing method of moving turbine blade according to claim 6, is characterized in that,
According to moving turbine blade blank (14) size Selection five line;
The movement of moving turbine blade blank (14) Y-axis and the rotation of XY plane and YZ plane is limited with A1 point, A2 point and A3 point;
The movement of X-axis and the rotation of XZ plane is limited with B1 point and B2 point;
With the movement of C1 point restriction Z axis.
8. the processing method of moving turbine blade according to claim 7, is characterized in that,
Using a line of A1 point, A2 point, B1 point, B2 point, 5 of C1 point and blade tip cross section back of the body camber line as moving turbine blade blank (14) and moving turbine blade blank (14) mach positioning datum.
9. the processing method of moving turbine blade according to claim 8, is characterized in that,
During grinding tenon tooth, the position degree ensureing to grind the relative blade profile center of tenon tooth come closes and ties up to XY coordinate plane ± 0.28mm;
During the sawtooth of grinding integral shroud, ensure coordinate system reference position degree ± 0.02mm that the relative tenon tooth of the size of sawtooth is set up;
The sawtooth of grinding tenon tooth and grinding integral shroud is creep feed grinding.
10. the processing method of moving turbine blade according to any one of claim 1 to 9, is characterized in that,
Clamping device during processing tenon tooth comprises chuck body (1), for the pressure head (2) of each positioning datum point of fixed turbine working-blade blank (14), for clamping the housing screw (3) of moving turbine blade blank (14) and the governor motion (4) for finely tuning each positioning datum point;
Clamping device during processing blade comprises firm banking (5), and firm banking (5) is provided with chuck (6) for clamping tenon tooth, in order to from the support member (7) of moving turbine blade blank (14) bottom support moving turbine blade blank (14), for the steel band (8) from moving turbine blade blank (14) side direction fixed turbine working-blade blank (14) and positioned opposite and be resisted against the backing pin (9) of the integral shroud sawtooth end of moving turbine blade blank (14) with chuck (6);
Clamping device after tenon tooth completion of processing comprises fixed platform (10), it is upper and for the support (11) supporting moving turbine blade blank (14), teeth groove folder (13) be held on by roller (12) in the teeth groove of tenon tooth to be located at fixed platform (10).
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| CN111790911A (en) * | 2020-07-20 | 2020-10-20 | 李庆宇 | Method for manufacturing thin-wall cooling air guide pipe of turbine blade of gas turbine engine |
| CN112484600A (en) * | 2020-11-16 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for inspecting multi-tooth shrouded turbine blade in aircraft engine |
| CN112959013A (en) * | 2021-03-17 | 2021-06-15 | 中国航发动力股份有限公司 | Method for machining square steel rough blade |
| CN113020900A (en) * | 2021-01-11 | 2021-06-25 | 重庆江增船舶重工有限公司 | Method for machining turbine blade of axial flow supercharger |
| CN113369831A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Machining process of aero-engine blade |
| CN113403464A (en) * | 2021-06-16 | 2021-09-17 | 中国航发航空科技股份有限公司 | Heat treatment device for aero-engine blade |
| CN113681466A (en) * | 2021-08-20 | 2021-11-23 | 中国航发航空科技股份有限公司 | Novel integrated machining clamp for turbine blade of aero-engine and machining process of novel integrated machining clamp |
| CN114101822A (en) * | 2021-12-15 | 2022-03-01 | 贵阳航发精密铸造有限公司 | Turbine blade air film hole machining method and machining device |
| CN116026265A (en) * | 2023-03-28 | 2023-04-28 | 沈阳强航时代精密科技有限公司 | Method for detecting low-pressure turbine blade sawtooth type blade crowns on three-coordinate measuring machine |
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| CN109332653B (en) * | 2018-12-07 | 2020-10-13 | 中国航发南方工业有限公司 | Manufacturing method of blade positioning base |
| CN109465405A (en) * | 2018-12-07 | 2019-03-15 | 中国航发南方工业有限公司 | A kind of Blade roughcast measuring block manufacturing method |
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| CN109332653A (en) * | 2018-12-07 | 2019-02-15 | 中国航发南方工业有限公司 | A kind of blade positioning base manufacturing method |
| CN111790911A (en) * | 2020-07-20 | 2020-10-20 | 李庆宇 | Method for manufacturing thin-wall cooling air guide pipe of turbine blade of gas turbine engine |
| CN112484600A (en) * | 2020-11-16 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for inspecting multi-tooth shrouded turbine blade in aircraft engine |
| CN112484600B (en) * | 2020-11-16 | 2021-12-24 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for inspecting multi-tooth shrouded turbine blade in aircraft engine |
| CN113020900A (en) * | 2021-01-11 | 2021-06-25 | 重庆江增船舶重工有限公司 | Method for machining turbine blade of axial flow supercharger |
| CN112959013A (en) * | 2021-03-17 | 2021-06-15 | 中国航发动力股份有限公司 | Method for machining square steel rough blade |
| CN113403464A (en) * | 2021-06-16 | 2021-09-17 | 中国航发航空科技股份有限公司 | Heat treatment device for aero-engine blade |
| CN113369831A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Machining process of aero-engine blade |
| CN113681466A (en) * | 2021-08-20 | 2021-11-23 | 中国航发航空科技股份有限公司 | Novel integrated machining clamp for turbine blade of aero-engine and machining process of novel integrated machining clamp |
| CN114101822A (en) * | 2021-12-15 | 2022-03-01 | 贵阳航发精密铸造有限公司 | Turbine blade air film hole machining method and machining device |
| CN116026265A (en) * | 2023-03-28 | 2023-04-28 | 沈阳强航时代精密科技有限公司 | Method for detecting low-pressure turbine blade sawtooth type blade crowns on three-coordinate measuring machine |
| CN116026265B (en) * | 2023-03-28 | 2023-06-09 | 沈阳强航时代精密科技有限公司 | Method for detecting low-pressure turbine blade sawtooth type blade crowns on three-coordinate measuring machine |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |