CN104481594A - Locking device used for circumferential compressor annular dovetail-shaped blade root of gas compressor - Google Patents
Locking device used for circumferential compressor annular dovetail-shaped blade root of gas compressor Download PDFInfo
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- CN104481594A CN104481594A CN201410587947.7A CN201410587947A CN104481594A CN 104481594 A CN104481594 A CN 104481594A CN 201410587947 A CN201410587947 A CN 201410587947A CN 104481594 A CN104481594 A CN 104481594A
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- China
- Prior art keywords
- chock
- locking device
- stopper
- hypomere
- stage casing
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Abstract
The invention discloses a locking device used for a circumferential compressor annular dovetail-shaped blade root of a gas compressor, and relates to a locking device. The locking device solves problems that the locking device is not dedicated to the circumferential compressor annular dovetail-shaped blade root of the gas compressor, and the diversity of gas compressor rotor structure and the flexibility of design are limited. A stopper upper section, a stopper middle section and a stopper lower section are arranged from small to large in sequence; the stopper upper section is a cuboid; the stopper middle section is a cylindrical section, and two sides of the stopper middle section are cut into an approximate cuboid; the stopper lower section is dovetail-shaped, and the cross section of the stopper lower section is trapezoidal; the length of the upper edge of the trapezoid is the same as that of the stopper middle section; the stopper upper section is fixedly connected to the center of the upper end face of the stopper middle section; the lower end face of the stopper middle section is fixed connected with the upper edge of the stopper lower section to form a whole; the center of a stopper is vertically processed with a thread through hole; and a round head fastening screw is in threaded connection with the thread through hole of the stopper. The locking device is used for locking the circumferential compressor annular dovetail-shaped blade root of the gas compressor.
Description
Technical field
The present invention relates to a kind of locking device, be specifically related to a kind of locking device for gas compressor circumferential ring-type dove-tail form blade root.
Background technique
At present, there is no the locking device of special gas compressor circumferential ring-type dove-tail form blade root, limit the diversity of compressor rotor structure, the flexibility of design.
Summary of the invention
The present invention solves the locking device not having special gas compressor circumferential ring-type dove-tail form blade root, limits the problem of the diversity of compressor rotor structure, the flexibility of design, and then provides a kind of locking device for gas compressor circumferential ring-type dove-tail form blade root.
The present invention solves the problems of the technologies described above the technological scheme taked to be:
Locking device for gas compressor circumferential ring-type dove-tail form blade root of the present invention comprises chock and round end fastening screw trip bolt, chock is by chock epimere, chock stage casing and chock hypomere are formed, chock epimere, chock stage casing and chock hypomere is ascending sets gradually, chock epimere is cuboid, chock stage casing is the approximate rectangular-shaped of formation after cylindrical section both sides are cut, chock hypomere is dove-tail form body, the cross section of chock hypomere is trapezoidal, the setting equal to the length in chock stage casing of described trapezoidal upper base, chock epimere is fixed in the center of the upper-end surface in chock stage casing, the lower end surface in chock stage casing overlaps with the upper bottom surface of chock hypomere and fixes as one, the upper bottom surface of chock hypomere is less than the bottom surface of chock hypomere, the center of chock is vertically processed with tapped through hole, and round end fastening screw trip bolt is threaded with the tapped through hole on chock, and the width of chock epimere is less than the width in chock stage casing.
The invention has the beneficial effects as follows:
When locking device for gas compressor circumferential ring-type dove-tail form blade root of the present invention is less for blade, blade quantity is more, adopt circumferential ring-type dove-tail form tongue-and-groove, bring and can much facilitate to processing and assembling, achieve the diversity of compressor rotor structure, the flexibility of design; Namely the locking mechanism of circumferential ring-type dove-tail form tongue-and-groove designs and provides a new field to the flexibility of the diversity of compressor rotor structural design and design.
Accompanying drawing explanation
Fig. 1 is the plan view of the locking device for gas compressor circumferential ring-type dove-tail form blade root of the present invention, Fig. 2 is the plan view of Fig. 1, Fig. 3 is the N-N sectional view of Fig. 2, Fig. 4 is the schematic diagram of annular tongue-and-groove on gas compressor, Fig. 5 is schematic diagram after gas compressor circumferential ring-type dove-tail form blade root blades installation, Fig. 6 is the initial assembling schematic diagram of locking mechanism, and Fig. 7 is the pilot process assembling schematic diagram of locking mechanism, and Fig. 8 is the locking assembling schematic diagram of locking mechanism.
Embodiment
Embodiment one: as shown in Fig. 1 ~ 8, the locking device for gas compressor circumferential ring-type dove-tail form blade root of present embodiment comprises chock 6 and round end fastening screw trip bolt 7, chock 6 is by chock epimere 1, chock stage casing 2 and chock hypomere 3 are formed, chock epimere 1, chock stage casing 2 and chock hypomere 3 is ascending sets gradually, chock epimere 1 is cuboid, chock stage casing 2 is for cutting the approximate rectangular-shaped of rear formation in cylindrical section both sides, chock hypomere 3 is dove-tail form body, the cross section of chock hypomere 3 is trapezoidal, the setting equal to the length in chock stage casing 2 of described trapezoidal upper base, chock epimere 1 is fixed in the center of the upper-end surface in chock stage casing 2, the lower end surface in chock stage casing 2 overlaps with the upper bottom surface of chock hypomere 3 and fixes as one, the upper bottom surface of chock hypomere 3 is less than the bottom surface of chock hypomere 3, the center of chock 6 is vertically processed with tapped through hole, and round end fastening screw trip bolt 7 is threaded with the tapped through hole on chock 6, and the width of chock epimere 1 is less than the width in chock stage casing 2.
The present invention becomes in the circumference on annular tongue-and-groove and has a blade gateway, and both sides, gateway have the breach that chock is blocked in two confessions;
In four blades in the end loaded for the locking mechanism of circumferential ring-type dove-tail form blade root of present embodiment, the breach having half to coordinate with chock top between every two blades, after installation, coordinate in the hole that top and described two blades of chock are formed;
Present embodiment is when chock 6 advances in annular tongue-and-groove, first chock 6 is screwed to the bottom of round end Cock screw 7 through tongue-and-groove, then after mounting point is determined, twist round end Cock screw 7, mentioned by chock 6, chock epimere 1 matches with the hole between blade 5 and blade 8, and chock stage casing 2 coordinates at chock breach Q semi-circle place, chock hypomere 3 pushes against tongue-and-groove both sides and is stuck in breach Q, is fixed by all blades.
Embodiment two: as shown in Figure 2, the cuboid of present embodiment chock epimere 1 is the cuboid of four rounding of angle.Design like this, when chock is to blade circumference location, reduces with the large stress of blade contact area, and surrounding rounding can avoid blade position generation stress to concentrate, and structure is simple, easy to process.
Other composition and annexation identical with embodiment one.
Embodiment three: as shown in Figure 1, the width setting equal to the width of chock hypomere 3 in present embodiment chock stage casing 2.Design like this, is easy to determine locked position in assembly process, the stage casing continuity that ensure Element Design equal to hypomere width.Other composition and annexation identical with embodiment one or two.
Embodiment four: as shown in Figure 2, the both sides of present embodiment chock hypomere 3 are symmetrically arranged dovetail body.Design like this, dovetail body loaded area is large, meets the requirement of chock intensity aspect.Other composition and annexation identical with embodiment three.
Embodiment five: as shown in Figure 1, the length of present embodiment chock epimere 1 is less than the minimum length in chock stage casing 2.Design like this, reduces the impact of throughflow surface and is less likely to occur in assembling to interfere.Other composition and annexation and embodiment one, two or four identical.
Working principle:
Have the gateway K of a blades installation in a position of the tongue-and-groove circumferentially circularized, when installing blade, blade loads tongue-and-groove from gateway successively, and advances in groove in order; The breach Q that chock is blocked in two confessions is had in K both sides, gateway, install at blade, only during remaining 4 blade rooms, a locking device of the present invention is added by between adjacent two the first end blades 5 and the second end blade 8, load breach K both sides successively, after blade is filled, all blades are circumferentially passed, chock 6 is just aligned with the breach Q on circular groove, twist Cock screw 7, mentioned by chock 6 and snap in breach, pressing close to tongue-and-groove bi-side, chock 6 pushes against tongue-and-groove both sides and is stuck in after in breach Q and just fixed by all blades.
Claims (5)
1. for the locking device of gas compressor circumferential ring-type dove-tail form blade root, it is characterized in that: locking device comprises chock (6) and round end fastening screw trip bolt (7), chock (6) is by chock epimere (1), chock stage casing (2) and chock hypomere (3) are formed, chock epimere (1), chock stage casing (2) and chock hypomere (3) is ascending sets gradually, chock epimere (1) is cuboid, chock stage casing (2) is for cutting the approximate rectangular-shaped of rear formation in cylindrical section both sides, chock hypomere (3) is dove-tail form body, the cross section of chock hypomere (3) is trapezoidal, the equal setting of length of described trapezoidal upper base and chock stage casing (2), chock epimere (1) is fixed in the center of the upper-end surface in chock stage casing (2), the lower end surface in chock stage casing (2) overlaps with the upper bottom surface of chock hypomere (3) and fixes as one, the upper bottom surface of chock hypomere (3) is less than the bottom surface of chock hypomere (3), the center of chock (6) is vertically processed with tapped through hole, round end fastening screw trip bolt (7) is threaded with the tapped through hole on chock (6), and the width of chock epimere (1) is less than the width of chock stage casing (2).
2. the locking device for gas compressor circumferential ring-type dove-tail form blade root according to claim 1, is characterized in that: the cuboid of chock epimere (1) is the cuboid of four rounding of angle.
3. the locking device for gas compressor circumferential ring-type dove-tail form blade root according to claim 1 and 2, is characterized in that: the width of chock stage casing (2) and the equal setting of width of chock hypomere (3).
4. the locking device for gas compressor circumferential ring-type dove-tail form blade root according to claim 3, is characterized in that: the both sides of chock hypomere (3) are symmetrically arranged dovetail body.
5. the locking device for gas compressor circumferential ring-type dove-tail form blade root according to claim 1,2 or 4, is characterized in that: the length of chock epimere (1) is less than the minimum length of chock stage casing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410587947.7A CN104481594A (en) | 2014-10-28 | 2014-10-28 | Locking device used for circumferential compressor annular dovetail-shaped blade root of gas compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410587947.7A CN104481594A (en) | 2014-10-28 | 2014-10-28 | Locking device used for circumferential compressor annular dovetail-shaped blade root of gas compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104481594A true CN104481594A (en) | 2015-04-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410587947.7A Pending CN104481594A (en) | 2014-10-28 | 2014-10-28 | Locking device used for circumferential compressor annular dovetail-shaped blade root of gas compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104481594A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014490A (en) * | 2016-06-22 | 2016-10-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Rotor vane locking structure |
| CN109209994A (en) * | 2017-06-29 | 2019-01-15 | 中国航发商用航空发动机有限责任公司 | rotor blade locking device |
| CN113251000A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Locking method of aircraft engine blade |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1164251A1 (en) * | 2000-06-15 | 2001-12-19 | Snecma Moteurs | Rotor blade locking means |
| EP1314856A1 (en) * | 2001-11-22 | 2003-05-28 | Snecma Moteurs | Device for locking blades in a disk groove |
| EP1321630A2 (en) * | 2001-12-21 | 2003-06-25 | Nuovo Pignone Holding S.P.A. | System for connecting and locking rotor blades of an axial compressor |
| US20110116933A1 (en) * | 2009-11-19 | 2011-05-19 | Nicholas Aiello | Rotor with one-sided load and lock slots |
| CN102733862A (en) * | 2011-04-05 | 2012-10-17 | 通用电气公司 | Locking device arrangement for rotating bladed stage |
| CN103726885A (en) * | 2012-10-12 | 2014-04-16 | 航空技术空间股份有限公司 | Lock for drum blades in a circumferential rotor groove |
-
2014
- 2014-10-28 CN CN201410587947.7A patent/CN104481594A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1164251A1 (en) * | 2000-06-15 | 2001-12-19 | Snecma Moteurs | Rotor blade locking means |
| EP1314856A1 (en) * | 2001-11-22 | 2003-05-28 | Snecma Moteurs | Device for locking blades in a disk groove |
| EP1321630A2 (en) * | 2001-12-21 | 2003-06-25 | Nuovo Pignone Holding S.P.A. | System for connecting and locking rotor blades of an axial compressor |
| US20110116933A1 (en) * | 2009-11-19 | 2011-05-19 | Nicholas Aiello | Rotor with one-sided load and lock slots |
| CN102733862A (en) * | 2011-04-05 | 2012-10-17 | 通用电气公司 | Locking device arrangement for rotating bladed stage |
| CN103726885A (en) * | 2012-10-12 | 2014-04-16 | 航空技术空间股份有限公司 | Lock for drum blades in a circumferential rotor groove |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014490A (en) * | 2016-06-22 | 2016-10-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Rotor vane locking structure |
| CN106014490B (en) * | 2016-06-22 | 2019-03-08 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of locking mechanism of rotor blade |
| CN109209994A (en) * | 2017-06-29 | 2019-01-15 | 中国航发商用航空发动机有限责任公司 | rotor blade locking device |
| CN113251000A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Locking method of aircraft engine blade |
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Application publication date: 20150401 |