CN208619175U - A kind of anticorrosive high-strength titanium alloy blade of aviation engine - Google Patents
A kind of anticorrosive high-strength titanium alloy blade of aviation engine Download PDFInfo
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- CN208619175U CN208619175U CN201821225414.4U CN201821225414U CN208619175U CN 208619175 U CN208619175 U CN 208619175U CN 201821225414 U CN201821225414 U CN 201821225414U CN 208619175 U CN208619175 U CN 208619175U
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- blade
- buffer board
- dashpot
- blade body
- mounting base
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Abstract
The utility model relates to a kind of anticorrosive high-strength titanium alloy blades of aviation engine, including blade body and mounting base, blade body is set in mounting base, blade body includes blade enclosure and the partition that is arranged in the cavity that blade enclosure surrounds, and the cavity that partition surrounds blade body is separated at least two cooling chambers；Blade enclosure includes outer wall and inner layer wall, and framing system is provided between outer wall and inner layer wall, and the leading edge of blade body is equipped at least one exhaust fenestra, close to up-front cooling chamber by being connected to outside air film hole and blade body；Mounting base is equipped with dashpot, the first buffer board and the second buffer board are provided in dashpot, in the fixed setting of first buffer board and dashpot, second buffer board is connected in the first buffer board and is slideably positioned in dashpot by bolster, and the two sides of mounting base are additionally provided with the installing port being connected to dashpot；The blade construction of the utility model is compact, good cooling results, and noise is small when use, long service life.
Description
Technical field
The utility model relates to a kind of engine blade, specifically a kind of anticorrosive high-strength titanium alloy aero-engine
Blade.
Background technique
Aero-engine is a kind of highly complex and accurate thermal machine, and power required for flying is provided for aircraft
Engine is known as " flower of industry " as the heart of aircraft, it directly affects the performance, reliability and economy of aircraft, is
One national science and technology, industry and military capability of the country important embodiment, currently, can independently develop high-performance aeroengine in the world
Country there was only a few countries such as the U.S., Russia, Britain, France, technical threshold is very high；
Blade is a kind of special part, its quantity is more, complex-shaped, it is desirable that high, difficulty of processing is big, and is failure
Multiple part, the key of the production of each engine works all the time, therefore the human and material resources that put into it, financial resources are all ratios
It is biggish, and the performance of blade is improving just with maximum effort in engine producer both at home and abroad, and production capacity and quality meet
It needs；
Blade of aviation engine be to guide fluid to flow in certain direction in aero-engine, and drive rotor rotate
Important component；In the prior art, it needs for several blades to be looped around on rotor in a ring when assembling, and drive rotor rotation
Important component, when assembling, need for several blades to be looped around on rotor in a ring, and existing blade construction is simple, in high-speed rotation
When the vibration force that generates it is stronger, the noise not only generated is big, and generates, easy damaged blade also big to the pressure of blade, wind day
It is easy after solarization that the big load operation of engine is caused by hot fever and the whole of engine is caused to damage, it is existing to improve this
Shape researches and develops a kind of technical problem that the engine blade that can overcome drawbacks described above is urgently to be resolved as those skilled in the art.
Utility model content
The shortcomings that technical problem to be solved in the utility model is, overcomes the prior art provides a kind of anticorrosive high-strength
Titanium alloy blade of aviation engine, the blade construction is compact, good cooling results, and noise is small when use, long service life.
In order to solve the above technical problems, the utility model provides a kind of anticorrosive high-strength titanium alloy aero-engine leaf
Piece, including blade body and mounting base, blade body are set in mounting base, in which:
Blade body includes blade enclosure and the partition that is arranged in the cavity that blade enclosure surrounds, and partition is by blade body
The cavity surrounded is separated at least two cooling chambers；
Blade enclosure includes outer wall and inner layer wall, and framing system, blade body are provided between outer wall and inner layer wall
Leading edge be equipped at least one exhaust fenestra, is connected to close to up-front cooling chamber by air film hole and blade body outside；
Mounting base is equipped with dashpot, is provided with the first buffer board and the second buffer board being parallel to each other in dashpot, the
With in dashpot, the second buffer board is connected and is slideably positioned in slow in the first buffer board by bolster the fixed setting of one buffer board
In jet-bedding, the two sides of mounting base are additionally provided with the installing port being connected to dashpot.
The technical solution that the utility model further limits is:
Further, in aforementioned anticorrosive high-strength titanium alloy blade of aviation engine, framing system include Wahlen structure and
I-groove beam.
Technical effect, previous blade only use simple " Wahlen " structure, or only use " I-shaped groove profile " knot
Structure, but either that structure, main purpose are to guarantee the integral rigidity of blade to mitigate the weight of blade simultaneously, from
And it improves or guarantees that the anti-bird of blade hits impact capacity；But simple internal cavity structures cause blade hollow rate can not
It improves, can not further mitigate so as to cause the weight of blade, in the utility model, due to by Wahlen structure and I-shaped groove profile
Structure organically merges, and the rigidity that " Wahlen " structure was both utilized is strong, and shock resistance resultant effect is good, and " I-shaped slot is utilized
The high feature of type " structure hollow rate, in the case where guaranteeing blade integral rigidity strip, it is ensured that blade bird hits impact property and meets the requirements,
The higher hollow rate of previous blade (can reach 40% or more) can be obtained simultaneously, has effectively achieved the loss of weight of blade.
In aforementioned anticorrosive high-strength titanium alloy blade of aviation engine, bolster include buffer bar, support rod, sliding groove and
Spring, buffer bar are set on the first buffer board, and support rod is set on the second buffer board, and sliding groove is additionally provided on support rod,
Spring is provided on the inner wall of sliding groove, institute's spring is fixedly connected with buffer bar, and one end of buffer bar extends in sliding groove.
Technical effect, the utility model are convenient under the action of elasticity by the way that bolster is arranged between two buffer boards
The injury tolerance for reducing the vibration force that generates and noise in engine working process, while reducing blade itself, improves the blade
Service life, the utility model design layout is reasonable.
In aforementioned anticorrosive high-strength titanium alloy blade of aviation engine, air film hole is provided with two rows.
The beneficial effects of the utility model are:
Cold air is flowed out out of cooling chamber along air film hole, covers upper one layer of cooling air film in blade hot spot region, high temperature is fired
Gas and blade isolation are come, and outside wall surface temperature is reduced.
The utility model is provided with partition in blade enclosure cavity, forms cooling chamber, hollow to save material, simultaneously
Shell is hollow structure again, is framing system, further saves material, under the premise of guaranteeing rigidity, reduces cost；Meanwhile this
Utility model can reduce the vibration force generated in engine working process and noise when in use, while reducing blade itself
Injury tolerance, improve the service life of the blade, reduce cost to the full extent.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model embodiment；
Fig. 2 is the partial structural diagram of blade body in Fig. 1；
Fig. 3 is the main view of Fig. 1；
Fig. 4 is the partial enlarged view of part A in Fig. 3；
In figure, 1- blade body, 11- blade enclosure, 12- partition, 13- outer wall, 14- inner layer wall, the Wahlen 15- structure,
16- I-groove beam, 2- mounting base, 3- air film hole, 4- dashpot, the first buffer board of 5-, the second buffer board of 6-, 7- buffer bar,
8- support rod, 9- sliding groove, 10- spring.
Specific embodiment
Embodiment 1
A kind of anticorrosive high-strength titanium alloy blade of aviation engine provided in this embodiment, structure is as shown in Figs 1-4, including
Blade body 1 and mounting base 2, blade body 1 are set in mounting base 2, in which:
Blade body 1 includes blade enclosure 11 and the partition 12 being arranged in the cavity that blade enclosure 11 surrounds, partition 12
The cavity that blade body 1 surrounds is separated at least two cooling chambers；
Blade enclosure 11 includes outer wall 13 and inner layer wall 14, and rib cage knot is provided between outer wall 13 and inner layer wall 14
Structure, framing system include Wahlen structure 15 and I-groove beam 16, and the combination of Wahlen structure 15 and I-groove beam 16 can be each
It is also possible to other combinations from half cavity is occupied, with depending on the size of blade, medium-sized blade each accounts for half for this combination,
Large-scale blade, Wahlen structure 15 are arranged more than I-groove beam 16, and small-sized blade, Wahlen structure 15 is set less than I-groove beam 16
It sets；The leading edge of blade body 1 is equipped with two rows of air film holes 3, and air film hole 3 is arranged along blade radial as seen from Figure 2, close to up-front
Cooling chamber outside air film hole 3 and blade body 1 by being connected to；
Mounting base 2 is equipped with dashpot 4, is provided with the first buffer board 5 and the second buffer board being parallel to each other in dashpot 4
6, the first buffer board 5 is fixedly installed in dashpot 4, and the second buffer board 6 is connect and slided with the first buffer board 5 by bolster
It is set in dashpot 4, the two sides of mounting base 2 are additionally provided with the installing port being connected to dashpot 4；
Bolster includes buffer bar 7, support rod 8, sliding groove 9 and spring 10, and buffer bar 7 is set on the first buffer board 5,
Support rod 8 is set on the second buffer board 6, and sliding groove 9 is additionally provided on support rod 8, is provided with spring on the inner wall of sliding groove 9
10, spring 10 is fixedly connected with buffer bar 7, and one end of buffer bar 7 extends in sliding groove 9.
When work, blade is mounted on the rotor, between blade and rotor by two buffer boards and between bolster
Setting, it is convenient to reduce the vibration force generated in engine working process and noise under the action of elasticity, while reducing blade
The injury tolerance of itself improves the service life of blade.
In addition to the implementation, the utility model can also have other embodiments.It is all to use equivalent replacement or equivalent change
The technical solution to be formed is changed, the protection scope of the requires of the utility model is all fallen within.
Claims (4)
1. a kind of anticorrosive high-strength titanium alloy blade of aviation engine, it is characterised in that: including blade body (1) and mounting base
(2), the blade body (1) is set on the mounting base (2), in which:
The blade body (1) includes the partition of blade enclosure (11) and setting in the cavity that the blade enclosure (11) surrounds
(12), the cavity that blade body (1) surrounds is separated at least two cooling chambers by the partition (12)；
The blade enclosure (11) includes outer wall (13) and inner layer wall (14), between the outer wall (13) and inner layer wall (14)
It is provided with framing system, the leading edge of the blade body (1) is equipped at least one exhaust fenestra (3), close to the up-front cooling
Chamber outside the air film hole (3) and the blade body (1) by being connected to；
The mounting base (2) is equipped with dashpot (4), is provided with the first buffer board (5) being parallel to each other in the dashpot (4)
And second buffer board (6), first buffer board (5) are fixedly installed in the dashpot (4), second buffer board (6)
It is connect and is slideably positioned in the dashpot (4) with first buffer board (5) by bolster, the mounting base (2)
Two sides are additionally provided with the installing port being connected to dashpot (4).
2. anticorrosive high-strength titanium alloy blade of aviation engine according to claim 1, it is characterised in that: the rib cage knot
Structure includes Wahlen structure (15) and I-groove beam (16).
3. anticorrosive high-strength titanium alloy blade of aviation engine according to claim 1, it is characterised in that: the bolster
Including buffer bar (7), support rod (8), sliding groove (9) and spring (10), the buffer bar (7) is set to first buffer board
(5) on, the support rod (8) is set on second buffer board (6), is additionally provided with sliding groove (9) on the support rod (8),
It is provided with spring (10) on the inner wall of the sliding groove (9), institute's spring (10) is fixedly connected with buffer bar (7), buffer bar (7)
One end extends in sliding groove (9).
4. anticorrosive high-strength titanium alloy blade of aviation engine according to claim 1, it is characterised in that: the air film
Hole (3) is provided with two rows.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821225414.4U CN208619175U (en) | 2018-07-31 | 2018-07-31 | A kind of anticorrosive high-strength titanium alloy blade of aviation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821225414.4U CN208619175U (en) | 2018-07-31 | 2018-07-31 | A kind of anticorrosive high-strength titanium alloy blade of aviation engine |
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| Publication Number | Publication Date |
|---|---|
| CN208619175U true CN208619175U (en) | 2019-03-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201821225414.4U Active CN208619175U (en) | 2018-07-31 | 2018-07-31 | A kind of anticorrosive high-strength titanium alloy blade of aviation engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114439551A (en) * | 2020-10-30 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
-
2018
- 2018-07-31 CN CN201821225414.4U patent/CN208619175U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114439551A (en) * | 2020-10-30 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
| CN114439551B (en) * | 2020-10-30 | 2024-05-10 | 中国航发商用航空发动机有限责任公司 | Aero-engine |
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