CN205330744U - Reduce balancing piece installation hole -edge stress 's installation limit structure - Google Patents
Reduce balancing piece installation hole -edge stress 's installation limit structure Download PDFInfo
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- CN205330744U CN205330744U CN201521040104.1U CN201521040104U CN205330744U CN 205330744 U CN205330744 U CN 205330744U CN 201521040104 U CN201521040104 U CN 201521040104U CN 205330744 U CN205330744 U CN 205330744U
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Abstract
The utility model relates to an aeroengine rotor dynamic balance field, concretely relates to reduce balancing piece installation hole -edge stress's installation limit structure. The utility model discloses a form at balancing piece installation limit increase lace for balancing piece installation hole -edge stress reduces, thereby improves the life on installation limit, provides effective technological solution way for the problem that engine balance piece mounting hole stress is big, the life -span is low. The utility model discloses an in the form of balancing piece installation limit increase lace, can reduce balancing piece installation hole -edge stress to improve the life on installation limit. The utility model discloses be particularly useful for the higher condition of the great hole -edge stress of balancing piece mounting hole circumference interval.
Description
Technical field
The present invention relates to aeroengine rotor dynamic balance field, be specifically related to a kind of balance weight that reduces and the installation limit structure of around-the-hole stress is installed。
Background technology
For meeting the dynamically balanced requirement of aeroengine rotor, balance weight need to be installed according to amount of unbalance situation additional at Ye Panshang。Fig. 1 gives aero-engine blisk conventional balanced block scheme of installation。Installing for the balance on blisk 1 and pin hole 5 is offered on limit 2, fixing balance weight 3 by pin 4, by the installation quantity of design balance block 3 and angle so that the amount of unbalance of dish is as far as possible little, thus ensureing the stable operation of rotor。Radial location residing for balance weight is often higher, limit is installed and will bear bigger stress, add perforate and stress that edge effect causes is concentrated quite serious, make under especially limit, hole, limit, hole very big along stress, it is easily caused balance installation limit 2 to break, is substantially reduced the low Zhou Shouming of blisk。Dimension continues and needs this class formation of improvement badly。
Summary of the invention
Solve the technical problem that: the present invention by installing the form of limit increase lace at balance weight, make balance weight that around-the-hole stress be installed to reduce, thus improving the service life installing limit, provide effective technology solution route for engine balance block installing hole stress problem big, that the life-span is low。
Technical scheme: this utility model provides a kind of balance weight that reduces and installs the installation limit structure of around-the-hole stress, this installation limit structure is the installation limit 2 of aero-engine blisk, the circumference on this installation limit has multiple short slot uniformly, and described short slot is opened in the position between balance weight installing hole, thus greatly reducing the around-the-hole stress of balance weight installing hole 5。
The physical dimension of short slot is limited mainly by Fig. 2 R, the restriction of r, L dimension。Arc radius R bottom this short slot more than on balance weight installing hole along radius (shown in Fig. 3), the corner chamfering radius r of this short slot is less than the groove depth of short slot, avoid because of the short slot excessively not round and smooth stress concentration phenomenon caused, arc length L between short slot is more than the aperture of balance weight installing hole, such as, for 2 times of installing hole aperture。
Beneficial effect: the present invention by installing the form of limit increase lace at balance weight, it is possible to reduces balance weight and installs around-the-hole stress, thus improving the service life installing limit。Present invention is particularly suitable for the situation that balance weight installing hole circumference spacing large hole limit stress is higher。
Accompanying drawing explanation
Fig. 1 is the balance weight scheme of installation of sky blisk of engine；
Limit schematic diagram installed by the balance weight that Fig. 2 is prior art；
Limit schematic diagram installed by the balance weight that Fig. 3 is the present invention；
Fig. 4 is the balance weight scheme of installation of sky blisk of engine；
Fig. 5 is the partial enlarged drawing of Fig. 4；
Wherein: the arc length between the arc radius bottom limit, 3 balance weights, 4 pins, 5 balance weight installing holes, the local (limit installed by the balance weight including part) of A-sky blisk of engine, the local of B-balance weight mounting structure, R short slot, r short slot corner rounding, L short slot installed by 1 blisk, 2 balance weights。
Detailed description of the invention
The structural representation of the present invention is as shown in Figure 3。The installation limit structure of around-the-hole stress installed by a kind of balance weight that reduces, this installation limit structure is the installation limit 2 of aero-engine blisk, the circumference on this installation limit has multiple short slot uniformly, and described short slot is opened in the position between balance weight installing hole, thus greatly reducing the around-the-hole stress of balance weight installing hole 5。
The physical dimension of short slot is limited mainly by Fig. 2 R, the restriction of r, L dimension。Arc radius R bottom this short slot more than on balance weight installing hole along radius (shown in Fig. 3), the corner chamfering radius r of this short slot is less than the groove depth of short slot, avoid because of the short slot excessively not round and smooth stress concentration phenomenon caused, arc length L between short slot is more than the aperture of balance weight installing hole, such as, for 2 times of installing hole aperture。
The present invention installs limit place by balance weight and circumferentially uniformly establishes short slot newly, thus reducing the local stress of balance weight installing hole, improves the life-span installing limit。This structure has novelty, considers that the local stress on installing hole limit is affected by short slot relative dimensions during structural design so that installing limit upper stress distribution more uniformly, the life-span improves。At present, this invention has been applied to MS engine blower, compressor part, and has passed through the test of fan, compressor, complete machine, it was demonstrated that this design is feasible。
Present invention can apply in aeroengine rotor structural design。
Claims (2)
1. the installation limit structure reducing balance weight installation around-the-hole stress, it is characterized in that: this installation limit structure is the installation limit (2) of aero-engine blisk, the circumference on this installation limit has multiple short slot uniformly, and described short slot is opened in the position between balance weight installing hole；Arc radius R bottom this short slot more than on balance weight installing hole along radius, the corner chamfering radius r of this short slot is less than the groove depth of short slot, and the adjacent arc length L between two short slots is more than the aperture of balance weight installing hole。
2. the installation limit structure of around-the-hole stress installed by a kind of balance weight that reduces according to claim 1, it is characterised in that: described arc length L is 2 times of installing hole aperture。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521040104.1U CN205330744U (en) | 2015-12-14 | 2015-12-14 | Reduce balancing piece installation hole -edge stress 's installation limit structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521040104.1U CN205330744U (en) | 2015-12-14 | 2015-12-14 | Reduce balancing piece installation hole -edge stress 's installation limit structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205330744U true CN205330744U (en) | 2016-06-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201521040104.1U Active CN205330744U (en) | 2015-12-14 | 2015-12-14 | Reduce balancing piece installation hole -edge stress 's installation limit structure |
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| CN (1) | CN205330744U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113982998A (en) * | 2021-11-02 | 2022-01-28 | 中国航发沈阳发动机研究所 | Compressor complete machine balance structure |
| CN114857142A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Connecting structure between different material members |
-
2015
- 2015-12-14 CN CN201521040104.1U patent/CN205330744U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113982998A (en) * | 2021-11-02 | 2022-01-28 | 中国航发沈阳发动机研究所 | Compressor complete machine balance structure |
| CN114857142A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Connecting structure between different material members |
| CN114857142B (en) * | 2022-05-12 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Connection structure between different material components |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 610500 Xindu Xuefu Road, Xindu District, Chengdu, Sichuan Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 operation monitoring department, Jiangyou 305 mailbox, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |
|
| CP03 | Change of name, title or address |