CN103790640A - Blade capable of preventing wheel dish from being cracked - Google Patents
Blade capable of preventing wheel dish from being cracked Download PDFInfo
- Publication number
- CN103790640A CN103790640A CN201410056308.8A CN201410056308A CN103790640A CN 103790640 A CN103790640 A CN 103790640A CN 201410056308 A CN201410056308 A CN 201410056308A CN 103790640 A CN103790640 A CN 103790640A
- Authority
- CN
- China
- Prior art keywords
- wheel disc
- blade
- disk body
- explosion
- disc disk
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a blade capable of preventing a wheel dish from being cracked. The blade comprises a wheel dish body and a blade body arranged on the outer wheel edge of the wheel dish body, and a weak section is arranged at the portion, close to the outer wheel edge, of the blade body to guarantee that the weak section of the blade body is cracked in advance of the wheel dish body. According to the blade, the weak section having the protecting effect is arranged at the position where the blade body is connected with the wheel dish body, so that the weak section of the blade body is cracked in advance when the wheel dish body rotates at a high speed, the wheel dish body acutely swings after the weak section of the blade body is cracked to be in contact with a static piece, the rotation speed of the wheel dish body is lowered, cracking of the wheel dish body is avoided, and the operation safety performance of an air vehicle is improved.
Description
Technical field
The present invention relates to engine art, especially, relate to a kind of anti-wheel disc explosion blade for aeroengine.
Background technique
The Security of aeroengine is particularly important, especially civil aviation motor, the factor of overriding concern when Security is its design.The turbine disk is the critical component of motor, once there is the explosion along meridian plane, will discharge huge energy, causes the generation of disaster, is in principle therefore absolutely not to allow to occur.Prior art, in order to prevent that the turbine disk is along meridian plane explosion, makes wheel disc have very high burst speed in the time of design, and its measure designs more thick and heavyly by wheel disc exactly, and blade also has larger bearing capacity.Prior art increases the weight of to improve turbine disk burst speed by thickening, makes the turbine disk or overweight, or has the possibility along meridian plane explosion.
Summary of the invention
The object of the invention is to provide a kind of anti-wheel disc explosion blade, has explosion risk or the overweight technical problem of wheel disc quality to solve the existing turbine disk.
For achieving the above object, the technical solution used in the present invention is as follows:
A kind of anti-wheel disc explosion blade, for coordinating with wheel disc disk body, blade is located on the outer rim of wheel disc disk body, on blade, near the position of outer rim, weak section is set, and weakness section ruptures at weak section place prior to wheel disc disk body in order to guarantee blade.
Further, weak section place reduces thickness and/or width with respect to other positions of blade.
Further, blade and the one machine shaping of wheel disc disk body or blade are welded on the outer rim of wheel disc disk body, and weak section is the blade root position that blade is connected with wheel disc disk body.
Further, the outer rim place of wheel disc disk body is provided with tongue-and-groove, blade and wheel disc disk body joggle, weak section be positioned at blade tenon stretch root position.
Further, weak section offers at least one blind hole in the axial direction along wheel disc disk body.
Further, weak section place offers groove.
Further, groove is positioned on the left and right side of weak section and/or on front/rear end.
Further, the inside of wheel disc disk body is provided with airtight cavity.
Further, cavity place is provided with cavity is communicated to the vent outside wheel disc disk body.
Further, cavity in wheel disc disk body along circumferential perforation.
The present invention has following beneficial effect:
The anti-wheel disc explosion of the present invention blade; the weak section shielding is set by the joint at blade and wheel disc disk body; while making wheel disc High Rotation Speed; blade is in the preferential fracture in weak section place; and because blade is after the place's fracture of weak section, cause that wheel disc acutely rocks and with static element collision, thereby reduced wheel disc rotating speed; avoid the explosion of wheel disc disk body, improved the Security of aircraft operation.
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 that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of the anti-wheel disc explosion of preferred embodiment of the present invention blade;
Fig. 2 is the schematic diagram of preferred embodiment of the present invention blade profile curve chord length and maximum ga(u)ge;
Fig. 3 is the structural representation of offering cavity and vent on Fig. 1 basis in wheel disc disk body inside;
Fig. 4 is the blade structure schematic diagram of preferred embodiment of the present invention band tenon;
Fig. 5 is real another structural representation of preferably executing routine anti-wheel disc explosion blade of the present invention;
Fig. 6 stretches the A of root to schematic diagram in Fig. 5;
Fig. 7 preferred embodiment of the present invention is stretched root position and offers the structural representation of blind hole;
Fig. 8 is the B-B schematic cross-section of Fig. 7;
Fig. 9 is the structural representation that the preferred embodiment of the present invention is stretched root position and offer groove; And
Figure 10 is the C-C schematic cross-section of Fig. 9.
Description of reference numerals:
10, wheel disc disk body; 11, outer rim; 12, cavity; 13, vent; 14, tongue-and-groove; 20, blade; 21, blade root; 22, tenon; 23, stretch root; 231, blind hole; 232, groove.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
With reference to Fig. 1, the preferred embodiments of the present invention provide a kind of anti-wheel disc explosion blade, and for coordinating with wheel disc disk body 10, blade 20 is located on the outer rim 11 of wheel disc disk body 10.The embodiment of the present invention arranges weakness section near the position of outer rim 11 on blade 20, to guarantee that blade 20 ruptures at weak section place prior to wheel disc disk body 10.In the embodiment of the present invention, by reducing the lifting surface area at the weak section of blade 20 place, make wheel disc disk body 10 in the time approaching explosion rotating speed, blade 20 ruptures at weak section place prior to wheel disc disk body 10, a certain blade 20 can in succession interrupt other blades that are connected with wheel disc disk body 10 after weak section fracture, and blade 20 runs out of steam and can hinder the rotation of wheel disc disk body 10 after rupturing with wheel disc disk body 10, and because blade 20 is after the place's fracture of weak section, cause wheel disc acutely to rock and collide with static element, thereby further reduce wheel disc rotating speed, avoid the explosion of wheel disc disk body 10, improve the Security of flying body operation.
In the present embodiment, blade 20 is welded on the outer rim 11 of wheel disc disk body 10 with the 10 one machine shapings of wheel disc disk body or blade 20, blade root 21 positions that weak section is connected with wheel disc disk body 10 for blade 20.Preferably, weak section is for realizing at thickness and/or the width at weak section place by reducing blade 20.In the present embodiment, adopt the moulding design of Simulation of computer simulation program to blade 10, determine by computational analysis width of blade or the thickness that blade root 21 places are suitable, make the blade of this position there is suitable lifting surface area, to guarantee that blade root 21 is in wheel disc disk body 10 and occurs to rupture before explosion, make turbine lose acting ability, and bump with other static elements, thereby reduction rotating speed, avoids the generation of wheel disc disk body 10 explosions.With reference to Fig. 2, by changing maximum ga(u)ge d and the chord length L of each cross section blade profile curve, just can control vane thickness or the width at blade 20 different heights places.By repeatedly changing maximum ga(u)ge d or the chord length L of near blade root 21 blade profile curve, and emulation generates blade entity, call again finite element program (as the business software of AN5Y5) and carry out Stress calculation, the rotating speed applying is arranged on certain more than 8% rotating speed lower than wheel disc disk body explosion rotating speed, until reaching, blade stress makes blade root 21 places fracture, obtain width of blade and the vane thickness at blade root 21 places, completed the design of the weak section of blade 20.The fracture rotating speed of this weakness section should guarantee under prerequisite that the normal work of wheel disc do not lose efficacy, lower than wheel disc explosion rotating speed more than 8%.
Preferably, with reference to Fig. 3, in the present embodiment, the inside of wheel disc disk body 10 hollows out design and is processed with airtight cavity 12.By the hollow airtight cavity 12 of the indoor design at wheel disc disk body 10, save the consumptive material of wheel disc disk body 10, and the structure efficiency of wheel disc disk body 10 is greatly improved, alleviate the overall weight of wheel disc disk body 10, avoid the stress of wheel disc disk body 10 to concentrate, thereby reached the effect that alleviates the weight of wheel disc disk body 10 and extend the working life of wheel disc disk body 10.Preferably, cavity 12 places are provided with cavity 12 are communicated to the vent 13 outside wheel disc disk body 10.Vent 13 makes airtight cavity 12 be communicated to the outside of wheel disc disk body 10, has avoided the impact that air expanded with heat and contract with cold in cavity 12 and the stress that aggravates wheel disc disk body 10 is concentrated.Vent 13 can arrange multiple, and preferably, vent 13 is arranged on the position of wheel disc disk body 10 near outer rim 11.In the present embodiment, cavity 12 is interior along circumferential perforation at wheel disc disk body 10, to maximize the quality that alleviates wheel disc disk body 10, and optimizes the structure efficiency of wheel disc disk body 10.
With reference to Fig. 4 and Fig. 5, in another embodiment of the present invention, outer rim 11 places of wheel disc disk body 10 are provided with tongue-and-groove 14, and blade 20 is through tenon 22 and wheel disc disk body 10 joggles, and blade 20 is connected tenon 22 through stretching root 23, and what weak section was positioned at blade 20 stretches root 23 positions.Stretch root 23 places also as calculated machine simulated program rational lifting surface area is set, to guarantee that stretching root 23 is in wheel disc disk body 10 and occurs to rupture before explosion, thickness and/or width that concrete setting can also be stretched root 23 places by change are realized, with reference to Fig. 5 and Fig. 6, the width X and the thickness Y that stretch root 23 places all can realize through the maximum ga(u)ge d and the chord length L that change cross section blade profile curve, this step is identical with previous embodiment, does not repeat them here.
With reference to Fig. 7 and Fig. 8, preferably, the present embodiment is being stretched root 23 places along offering at least one blind hole 231 in the axial direction of wheel disc disk body 10.Particularly, with reference to Fig. 8, in the present embodiment, stretch on the axial front/rear end that root 23 is in wheel disc disk body 10 and respectively have a blind hole 231, to reduce to stretch the lifting surface area at root 23 places, and two blind holes 231 are not communicated with, in order to avoid affect normal gas flow.
With reference to Fig. 9 and Figure 10, preferably, to offering groove 232 as root 23 places of stretching of weak section.In the present embodiment, groove 232 is positioned at stretches root 23 along on the axial left and right side of wheel disc disk body 10 and/or on front/rear end, to reduce to stretch the lifting surface area at root 23 places, guarantees to stretch before root 23 has precedence over 10 explosions of wheel disc disk body and ruptures.
In the embodiment of the present invention, be also applicable to the cover plate with tenon structure such as fan, gas compressor with the blade of tenon structure.The embodiment of the present invention is by arranging the weak section shielding in blade 20 and the joint of wheel disc disk body 10; while making wheel disc disk body 10 High Rotation Speed; blade 20 is in the preferential fracture in weak section place; and because blade 20 is after the place's fracture of weak section; cause wheel disc acutely to rock and collide with static element; thereby reduce wheel disc rotating speed, avoided the explosion of wheel disc disk body 10, improved the Security of flying body operation.
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 modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (10)
1. an anti-wheel disc explosion blade, for coordinating with wheel disc disk body (10), described blade (20) is located on the outer rim (11) of wheel disc disk body (10), it is characterized in that,
The upper position near described outer rim (11) of described blade (20) arranges weak section, and described weakness section ruptures at described weak section place prior to described wheel disc disk body (10) in order to guarantee described blade (20).
2. anti-wheel disc explosion blade according to claim 1, is characterized in that,
Described weak section place reduces thickness and/or width with respect to other positions of described blade (20).
3. anti-wheel disc explosion blade according to claim 2, is characterized in that,
Described blade (20) is upper with the described outer rim (11) that described wheel disc disk body (10) one machine shaping or described blade (20) are welded on described wheel disc disk body (10), and described weak section is blade root (21) position that described blade (20) is connected with described wheel disc disk body (10).
4. anti-wheel disc explosion blade according to claim 2, is characterized in that,
The described outer rim (11) of described wheel disc disk body (10) locates to be provided with tongue-and-groove (14), described blade (20) and described wheel disc disk body (10) joggle, described weak section be positioned at described blade (20) tenon (22) stretch root (23) position.
5. according to the anti-wheel disc explosion blade described in claim 3 or 4, it is characterized in that,
Described weak section offers at least one blind hole (231) in the axial direction along described wheel disc disk body (10).
6. anti-wheel disc explosion blade according to claim 5, is characterized in that,
Described weak section place offers groove (232).
7. anti-wheel disc explosion blade according to claim 6, is characterized in that,
Described groove (232) is positioned on the left and right side of described weak section and/or on front/rear end.
8. anti-wheel disc explosion blade according to claim 1, is characterized in that,
The inside of described wheel disc disk body (10) is provided with airtight cavity (12).
9. anti-wheel disc explosion blade according to claim 8, is characterized in that,
Described cavity (12) is located to be provided with described cavity (12) is communicated to the vent (13) outside described wheel disc disk body (10).
10. anti-wheel disc explosion blade according to claim 9, is characterized in that,
Described cavity (12) in described wheel disc disk body (10) along circumferential perforation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410056308.8A CN103790640B (en) | 2014-02-19 | 2014-02-19 | Anti-wheel disc explosion blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410056308.8A CN103790640B (en) | 2014-02-19 | 2014-02-19 | Anti-wheel disc explosion blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103790640A true CN103790640A (en) | 2014-05-14 |
| CN103790640B CN103790640B (en) | 2015-10-28 |
Family
ID=50666650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410056308.8A Active CN103790640B (en) | 2014-02-19 | 2014-02-19 | Anti-wheel disc explosion blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103790640B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105512408A (en) * | 2015-12-14 | 2016-04-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Trisection grooving prefabrication method for disc, blade and shaft integrated turbine rotor with ultrahigh rotation speed |
| CN110185498A (en) * | 2019-05-27 | 2019-08-30 | 中国航发湖南动力机械研究所 | The design method of anti-wheel disc explosion blade and its weak structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB836030A (en) * | 1955-10-31 | 1960-06-01 | Maschf Augsburg Nuernberg Ag | Improvements in or relating to a turbine blade and rotor assembly |
| US2965355A (en) * | 1956-01-17 | 1960-12-20 | United Aircraft Corp | Turbine disc burst inhibitor |
| CA624166A (en) * | 1961-07-18 | Fairchild Engine And Airplane Corporation | Controlled turbine wheel failure | |
| US3952391A (en) * | 1974-07-22 | 1976-04-27 | General Motors Corporation | Turbine blade with configured stalk |
| EP0574708A1 (en) * | 1992-06-13 | 1993-12-22 | Asea Brown Boveri Ag | Component for high temperatures, in particular turbine blade, and process for preparing this blade |
| WO2010112767A1 (en) * | 2009-04-02 | 2010-10-07 | Turbomeca | Turbine wheel with untuned blades comprising a damping device |
| EP2696033A1 (en) * | 2012-08-10 | 2014-02-12 | MTU Aero Engines GmbH | Blade element of a turbomachine with a ductile compensation layer, corresponding turbomachine, methods of manufacturing of the blade element and of the turbomachine |
-
2014
- 2014-02-19 CN CN201410056308.8A patent/CN103790640B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA624166A (en) * | 1961-07-18 | Fairchild Engine And Airplane Corporation | Controlled turbine wheel failure | |
| GB836030A (en) * | 1955-10-31 | 1960-06-01 | Maschf Augsburg Nuernberg Ag | Improvements in or relating to a turbine blade and rotor assembly |
| US2965355A (en) * | 1956-01-17 | 1960-12-20 | United Aircraft Corp | Turbine disc burst inhibitor |
| US3952391A (en) * | 1974-07-22 | 1976-04-27 | General Motors Corporation | Turbine blade with configured stalk |
| EP0574708A1 (en) * | 1992-06-13 | 1993-12-22 | Asea Brown Boveri Ag | Component for high temperatures, in particular turbine blade, and process for preparing this blade |
| WO2010112767A1 (en) * | 2009-04-02 | 2010-10-07 | Turbomeca | Turbine wheel with untuned blades comprising a damping device |
| EP2696033A1 (en) * | 2012-08-10 | 2014-02-12 | MTU Aero Engines GmbH | Blade element of a turbomachine with a ductile compensation layer, corresponding turbomachine, methods of manufacturing of the blade element and of the turbomachine |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105512408A (en) * | 2015-12-14 | 2016-04-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Trisection grooving prefabrication method for disc, blade and shaft integrated turbine rotor with ultrahigh rotation speed |
| CN110185498A (en) * | 2019-05-27 | 2019-08-30 | 中国航发湖南动力机械研究所 | The design method of anti-wheel disc explosion blade and its weak structure |
| CN110185498B (en) * | 2019-05-27 | 2021-11-12 | 中国航发湖南动力机械研究所 | Wheel disc burst prevention blade and design method of weak structure thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103790640B (en) | 2015-10-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9932840B2 (en) | Rotor for a gas turbine engine | |
| CN103422912A (en) | Turbine with moving blades with pits at blade tops | |
| CN107269583A (en) | A kind of super/transonic speed axial fan designs method based on high-order moment | |
| CN103790639B (en) | A kind of turbine petiolarea blade inlet edge edge strip repaiies type method | |
| CN102562178A (en) | Turbine nozzle for air cycle machine | |
| CN108757555B (en) | Hollow blade structure of aircraft engine and design method thereof | |
| EA029645B1 (en) | Design method for three-dimensional curved airfoil section | |
| CN103790640B (en) | Anti-wheel disc explosion blade | |
| CN204357771U (en) | A kind of metal stiffened edge, fan blade and turbogenerator | |
| CN104314618B (en) | A kind of method of low-pressure turbine blade structure and reduction blade loss | |
| CN102163244A (en) | Method for dolphin head-shaped processing of blade leading edge | |
| CN205779470U (en) | A kind of blunt trailing edge wind mill airfoil circulation control device | |
| CN100458179C (en) | Wheel hub shaping method for improving end area blocking | |
| CN102889237A (en) | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor | |
| CN204726671U (en) | A kind of high efficient fan wing | |
| CN203948136U (en) | The low pressure stage group exhaust stage blade of leaving area 3.6m2 variable speed air cooling industrial steam turbine | |
| CN204312392U (en) | For installing novel tenon and the tongue-and-groove linkage structure of compressor blade and drum-type wheel disc | |
| CN105257590A (en) | Semi-serial blade and design method thereof | |
| CN105545810A (en) | Case of centrifugal compressor | |
| CN107605667A (en) | A kind of modularization pneumatic equipment bladess part synergy design method | |
| CN112211678A (en) | Long-life turbine rotor front baffle | |
| CN105065302A (en) | Efficient sweepforward-type subway tunnel axial flow fan | |
| CN203978917U (en) | A kind of transonic fan rotor blade | |
| CN104494842B (en) | Rising wingtip design method | |
| CN204921414U (en) | High -efficient sweepforward type subway tunnel axial fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |