CN205074920U - Listrium positioner for grinding on combustion engine turbine work blade - Google Patents
Listrium positioner for grinding on combustion engine turbine work blade Download PDFInfo
- Publication number
- CN205074920U CN205074920U CN201520330309.7U CN201520330309U CN205074920U CN 205074920 U CN205074920 U CN 205074920U CN 201520330309 U CN201520330309 U CN 201520330309U CN 205074920 U CN205074920 U CN 205074920U
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- blade
- listrium
- supramarginal plate
- combustion engine
- installing rack
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Abstract
The utility model provides a listrium positioner for grinding on combustion engine turbine work blade, a serial communication port, include and grind processing base (1), install listrium mounting bracket (2), lower listrium mounting bracket (3), blade auxiliary stay (5), blade clamp plate (6) on the mill processing base (1), go up listrium mounting bracket (2) locating piece (7) and housing screw (8) of both sides including the lower part for listrium in the support, listrium mounting bracket (3) include supporting shoe (4), upper portion clamp plate (9), briquetting (10) and adjusting bolt (11) down, and the screw of supporting shoe (4), upper portion clamp plate (9) is passed in adjusting bolt (11), and briquetting (10) lie in the one end of upper portion clamp plate (9) for support listrium down, blade auxiliary stay (5) of lower part and blade clamp plate (6) on upper portion combine to support the blade middle part.
Description
Technical field:
The present invention relates to aero-turbine working-blade processing and manufacturing technology, specifically provide a kind of for aero-turbine working-blade supramarginal plate grinding positioner.
Background technology:
During machining blade supramarginal plate, selection of location datum be supramarginal plate locating hole and blade tenon Profile of AT, the blade machined according to this kind of method is when carrying out turbine disk assembling, supramarginal plate gap width cannot ensure, to cause in follow-up assembling process repeatedly reconditioning maybe must change blade, cause the reason of this kind of situation to be that main location uses center hole location when machining blade supramarginal plate, this hole is that one-step casting is shaping, very large with batch biased difference in blade tips hole.After blade clamping, there is gap in top locating surface, and during machining supramarginal plate, by the effect of grinding force, blade produces along grinding direction and departs from, the supramarginal plate dimension overproof processed and otherness is larger.
Summary of the invention:
The invention provides a kind of for aero-turbine working-blade supramarginal plate grinding positioner.The arrangement increases the stability of blade supramarginal plate processing dimension, stopped the repair repeatedly in follow-up assembling process, overcome the deficiencies in the prior art part.
The invention provides a kind of combustion engine turbine working-blade supramarginal plate grinding positioner, it is characterized in that, comprise mill processing base (1), mill processing base 1 is provided with supramarginal plate installing rack (2), inframarginal installing rack (3), blade supplemental support (5), blade pressing plate (6)
Supramarginal plate installing rack (2) comprises the locating piece (7) of bottom and the housing screw (8) of both sides, for supporting supramarginal plate;
Inframarginal installing rack (3) comprises back-up block (4), top hold-down (9), briquetting (10) and adjusting bolt (11), adjusting bolt (11) is through the screw of back-up block (4), top hold-down (9), briquetting (10) is positioned at one end of top hold-down (9), for supporting inframarginal;
The blade supplemental support (5) of bottom and the blade pressing plate (6) on top combine and support in the middle part of blade.Adopt this kind of assisted location method effectively to enhance the stability of blade location in the blade middle class in a kindergarten, also enhance the stability of blade work in-process size simultaneously.
Further, locating piece (7) has and adopts the V-shaped groove consistent with moving turbine blade blade back integral shroud listrium profile as main location herein with the V-shaped groove that supramarginal plate end surface shape is mated, avoid original location using casting center hole orifice position and orifice shapes deviation to cause unreliable.
Further, blade supplemental support (5) comprises jack bolt (12) and supplemental support block (13), and jack bolt (12) is installed on mill processing base (1).
The advantage of the invention is: reduce the dimension overproof and wild effect that cause due to foundry goods deviation in processing, the adjustment repeatedly reduced or stop in turbine disk assembling process and the number of times of repairing repeatedly for supramarginal plate gap, shorten assembly period, effectively improve working (machining) efficiency.
Accompanying drawing illustrates:
Fig. 1 the utility model scheme of installation;
Fig. 2 blade supplemental support and blade pressing plate schematic diagram;
Fig. 3 supramarginal plate installing rack schematic diagram;
Fig. 4 inframarginal installing rack schematic diagram.
Detailed description of the invention:
Consult the utility model and provide a kind of combustion engine turbine working-blade supramarginal plate grinding positioner, it is characterized in that, comprise mill processing base 1, mill processing base 1 is provided with supramarginal plate installing rack 2, inframarginal installing rack 3, blade supplemental support 5, blade pressing plate 6
Supramarginal plate installing rack 2 comprises the locating piece 7 of bottom and the housing screw 8 of both sides, for supporting supramarginal plate;
Inframarginal installing rack 3 comprises back-up block 4, top hold-down 9, briquetting 10 and adjusting bolt 11, and adjusting bolt 11 is through the screw of back-up block 4, top hold-down 9, and briquetting 10 is positioned at one end of top hold-down 9, for supporting inframarginal;
The blade supplemental support 5 of bottom and the blade pressing plate 6 on top combine and support in the middle part of blade.Blade supplemental support 5 termination is facet and blade contact surface is linear contact lay, reaches the effect supported in the middle part of blade in conjunction with blade pressing plate.
Further, locating piece 7 has the V-shaped groove mated with supramarginal plate end surface shape.Technique effect uses such V-shaped groove of locating piece 7 as main locating surface, supports the integral shroud of whole moving turbine blade, is carrying out adding the effect playing main holding capacity man-hour.
Further, blade supplemental support 5 comprises jack bolt 12 and supplemental support block 13, and jack bolt 12 is installed on mill processing base 1.
With supramarginal plate installing rack 2 and inframarginal installing rack 3 for main member, by blades installation on location main member supramarginal plate installing rack 2 and inframarginal installing rack 3, check locating surface gap, regulate blade supplemental support 5, regulate inframarginal installing rack 3 and briquetting 10, compress blade pressing plate 6, hold out against supramarginal plate housing screw 8, each locating piece 7 of final inspection and gap, blade contact face.The fixture installing blade is arranged on grinding machine workbench, realizes the processing to supramarginal plate size V-type face.
Claims (3)
1. a combustion engine turbine working-blade supramarginal plate grinding positioner, it is characterized in that, comprise mill processing base (1), mill processing base (1) is provided with supramarginal plate installing rack (2), inframarginal installing rack (3), blade supplemental support (5), blade pressing plate (6)
Supramarginal plate installing rack (2) comprises the locating piece (7) of bottom and the housing screw (8) of both sides, for supporting supramarginal plate;
Inframarginal installing rack (3) comprises back-up block (4), top hold-down (9), briquetting (10) and adjusting bolt (11), adjusting bolt (11) is through the screw of back-up block (4), top hold-down (9), briquetting (10) is positioned at one end of top hold-down (9), for supporting inframarginal;
The blade supplemental support (5) of bottom and the blade pressing plate (6) on top combine and support in the middle part of blade.
2. combustion engine turbine working-blade supramarginal plate grinding positioner according to claim 1, is characterized in that, locating piece (7) has the V-shaped groove mated with supramarginal plate end surface shape.
3. combustion engine turbine working-blade supramarginal plate grinding positioner according to claim 1, it is characterized in that, blade supplemental support (5) comprises jack bolt (12) and supplemental support block (13), and jack bolt (12) is installed on mill processing base (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520330309.7U CN205074920U (en) | 2015-05-21 | 2015-05-21 | Listrium positioner for grinding on combustion engine turbine work blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520330309.7U CN205074920U (en) | 2015-05-21 | 2015-05-21 | Listrium positioner for grinding on combustion engine turbine work blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205074920U true CN205074920U (en) | 2016-03-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520330309.7U Active CN205074920U (en) | 2015-05-21 | 2015-05-21 | Listrium positioner for grinding on combustion engine turbine work blade |
Country Status (1)
| Country | Link |
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| CN (1) | CN205074920U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107553169A (en) * | 2017-09-28 | 2018-01-09 | 中国航发动力股份有限公司 | One kind is used for aero-engine finish forge blade processing positioner |
| CN107570937A (en) * | 2017-09-28 | 2018-01-12 | 中国航发动力股份有限公司 | A kind of turbo blade inert gas welds positioner |
| CN111607814A (en) * | 2020-06-30 | 2020-09-01 | 中国航发动力股份有限公司 | Tool device for turbine disc corrosion process and use method thereof |
| CN111750809A (en) * | 2020-06-30 | 2020-10-09 | 中国航发动力股份有限公司 | Tool device and method for measuring thickness of casting |
| CN113829131A (en) * | 2021-09-03 | 2021-12-24 | 中国航发哈尔滨东安发动机有限公司 | Turbine disk blade grinding device |
| CN115157123A (en) * | 2022-08-25 | 2022-10-11 | 南京农业大学 | Fixture and grinding method for grinding upper citron plate side face and lower citron plate air inlet edge of gas turbine guide vane fan-shaped piece |
-
2015
- 2015-05-21 CN CN201520330309.7U patent/CN205074920U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107553169A (en) * | 2017-09-28 | 2018-01-09 | 中国航发动力股份有限公司 | One kind is used for aero-engine finish forge blade processing positioner |
| CN107570937A (en) * | 2017-09-28 | 2018-01-12 | 中国航发动力股份有限公司 | A kind of turbo blade inert gas welds positioner |
| CN111607814A (en) * | 2020-06-30 | 2020-09-01 | 中国航发动力股份有限公司 | Tool device for turbine disc corrosion process and use method thereof |
| CN111750809A (en) * | 2020-06-30 | 2020-10-09 | 中国航发动力股份有限公司 | Tool device and method for measuring thickness of casting |
| CN111607814B (en) * | 2020-06-30 | 2021-08-17 | 中国航发动力股份有限公司 | Tool device for turbine disc corrosion process and use method thereof |
| CN111750809B (en) * | 2020-06-30 | 2022-04-01 | 中国航发动力股份有限公司 | Tool device and method for measuring thickness of casting |
| CN113829131A (en) * | 2021-09-03 | 2021-12-24 | 中国航发哈尔滨东安发动机有限公司 | Turbine disk blade grinding device |
| CN113829131B (en) * | 2021-09-03 | 2024-03-22 | 中国航发哈尔滨东安发动机有限公司 | Turbine disc blade grinding device |
| CN115157123A (en) * | 2022-08-25 | 2022-10-11 | 南京农业大学 | Fixture and grinding method for grinding upper citron plate side face and lower citron plate air inlet edge of gas turbine guide vane fan-shaped piece |
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|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |