CN205940943U - Engine blade clamping device - Google Patents
Engine blade clamping device Download PDFInfo
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- CN205940943U CN205940943U CN201620785802.2U CN201620785802U CN205940943U CN 205940943 U CN205940943 U CN 205940943U CN 201620785802 U CN201620785802 U CN 201620785802U CN 205940943 U CN205940943 U CN 205940943U
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- tenon
- blade
- engine blade
- clamping device
- hole
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- 241000397426 Centroberyx lineatus Species 0.000 claims description 19
- 238000009434 installation Methods 0.000 claims description 13
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 13
- 238000009661 fatigue test Methods 0.000 abstract description 10
- 230000014759 maintenance of location Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 7
- 238000013461 design Methods 0.000 description 6
- 239000000758 substrate Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses an engine blade clamping device for press from both sides tight engine blade, the engine blade includes blade and the tenon that is connected, and engine blade clamping device includes anchor clamps and fixed part, and anchor clamps have mounting hole and fixed orifices, and the mounting hole is used for holding the tenon, and the fixed part passes the fixed orifices, makes the tenon pressed from both sides and tightly sets up in the mounting hole. The utility model discloses an engine blade clamping device's simple structure can press from both sides the engine blade tightly easy dismounting, used repeatedly many times fast, reliably. The utility model discloses obtained using and verifying in aeroengine blade modal test and fatigue test's blade retention. Application result shows, the application the utility model discloses an engine blade clamping device can press from both sides tightly the engine blade fast effectively, and when the reliable clamp of blade was tight, the assurance can not damage the surface of blade.
Description
Technical field
This utility model relates generally to a kind of blade clamping device, carries out mould in particular to a kind of to blade
When state test and fatigue test, the device of clamping blade of aviation engine.
Background technology
Blade of aviation engine includes fan blade, compressor blade and turbo blade.After blade design machines,
In order to understand whether vibration characteristics and the fatigue properties of blade, the vibration of checking blade and fatigue behaviour meet design requirement, need
Modal test and fatigue test are carried out to blade.
, due to the differences such as purposes and use occasion, various structures, form is different for blade of aviation engine.More specifically,
Form due to blade tenon differs, then the fixed form of blade is different.The modal test of blade and fatigue test are to understand leaf
Piece vibration characteristics and the important method of fatigue properties, both tests are required to fixing individual blade, and the clamped mode of blade
The actual installation state of working-blade on needs simulated engine as much as possible.
It is flat that root plane listrium is mainly pressed abd fixed on test using follower bolt structure by traditional blade clamping mode
On platform, but this clamping mode is only applicable to the situation of plane listrium blade, is not particularly suited for the feelings of on-plane surface listrium blade
Shape.In prior art, have no the blade clamping device being specifically designed for these three blade tenon forms.
Actual engine blade tenon is complex-shaped various, is not planar structure, common on-plane surface blade tenon capitiform
Formula has peg type, swallow-tail form and fir shape, corresponding fixed way blade be pin listrium contact-type, dovetail three face contact-type and
Tenon tooth contact-type.
The clamping that existing blade clamping device can not meet actual blade requires, not to mention work on simulated engine
Make the actual installment state of blade.Therefore, existing blade clamping device cannot implement modal test and the fatigue test of blade,
Can not effectively obtain vibration and the fatigue properties of blade.
For the individual blade of non-integral leaf dish, need to secure the vanes to modal test is carried out on test platform and incite somebody to action
Blade is fixed on vibration table and carries out fatigue test, that is, need to design the blade clamping device dedicated for different tenon forms.
It is thus desirable to for the special blade clamping device of the blade design of these three tenon forms, for the mode of blade
Test and fatigue test.
Disclosed in described background section, above- mentioned information is only used for strengthening the understanding to background of the present utility model, because
This it can include not constituting the information to prior art known to persons of ordinary skill in the art.
Utility model content
A main purpose of the present utility model is to overcome at least one defect of above-mentioned prior art, provides a kind of sending out
Motivation blade clamping device, can be used in the modal test of blade and the fatigue test of on-plane surface tenon form.
For reaching above-mentioned purpose, this utility model provides a kind of engine blade clamping device, for clamping electromotor leaf
Piece, engine blade includes the blade being connected and tenon, and engine blade clamping device includes fixture and fixed part, and fixture has
There are installing hole and fixing hole, installing hole is used for accommodating tenon, fixed part passes through fixing hole so that tenon is clamped is arranged at installation
In the hole.
Wherein, engine blade is peg type tenon blade, and tenon is lug tenon, and lug tenon center has lug
Hole；Fixed part includes pin, stay-bolt and nut, and one end of stay-bolt is connected with nut, and is anchored on the outside of fixture,
The middle part of stay-bolt is located at fixing in the hole, and the other end of stay-bolt is located at installs in the hole, and is connected with lug tenon, pin
It is fixedly connected through lug hole with stay-bolt, thus lug tenon is fixed on installation in the hole.
Wherein, peg type tenon blade also includes listrium, and listrium is connected between lug tenon and blade；The hole of installing hole
Mouth has slope, and listrium is fitted tightly with slope.
Wherein, engine blade is swallow-tail form tenon blade, and tenon is swallow-tail form tenon；Installing hole and swallow-tail form tenon
Shape is consistent；Fixed part includes clamping screw；Engine blade clamping device also includes pressing tongue and pressure tongue apertures, and pressure tongue apertures is communicatively
It is arranged between installing hole and fixing hole, pressure tongue is placed in pressure tongue apertures, and contacts with swallow-tail form tenon, clamping screw and fixing hole
Threaded, and pressure tongue can be made to compress swallow-tail form tenon by tightening clamping screw.
Wherein, engine blade is fir shape tenon blade, and tenon is fir shape tenon；Rectangular opening is had in the middle part of fixture,
Fixture top opens up described fixing hole；Fixed part includes hold-down bolt；Engine blade clamping device also includes chuck, chuck position
In rectangle in the hole, installing hole is opened in chuck；Fir shape tenon can extend into installation in the hole, and by screwing hold-down bolt,
Make hold-down bolt support the upper surface of chuck, fir shape tenon is clampingly located in chuck.
Wherein, chuck also includes deforming groove, and deformation groove is opened in the outer rim of chuck, and connects with installing hole, and deformation groove is certainly
The outer rim of installing hole is radially expanded, and deformation groove is identical with the centrage of chuck with the centrage of installing hole；Hold-down bolt
The upper surface of compression chuck is so that deformation groove shrinks radially inward, and then fir shape tenon is fitted tightly with chuck.
Wherein, engine blade clamping device also includes baffle plate, and baffle plate is supported on fixture, and the side of fixture and chuck
Side be all resisted against baffle plate.
Wherein, between the upper surface of chuck and the interior upper wall of rectangular opening, there is gap.
This utility model having the beneficial effects that compared to prior art：Engine blade clamping device of the present utility model
Structure simple, engine blade quickly and reliably can be clamped, easy accessibility, can repeatedly use.This utility model is
Through being applied in the blade of blade of aviation engine modal test and fatigue test is fixing and being verified.Application result table
Bright, with engine blade clamping device of the present utility model, can fast and effeciently engine blade be clamped, in blade
While reliable grip it is ensured that will not damaged blade surface.
Brief description
By being considered in conjunction with the accompanying the following detailed description to preferred embodiment of the present utility model, of the present utility model each
Plant target, feature and advantage will become apparent from.Accompanying drawing is only exemplary diagram of the present utility model, is not necessarily
Drawn to scale.In the accompanying drawings, same reference represents same or similar part all the time.Wherein：
Fig. 1 is the schematic diagram of peg type tenon blade.
Fig. 2 is the schematic diagram of the first embodiment of engine blade clamping device.
Fig. 3 is the schematic diagram of swallow-tail form tenon blade.
Fig. 4 is the schematic diagram of the second embodiment of engine blade clamping device.
Fig. 5 is the schematic diagram of fir shape tenon blade.
Fig. 6 is the schematic diagram of the 3rd embodiment of engine blade clamping device.
Specific embodiment
It is described more fully with example embodiment referring now to accompanying drawing.However, example embodiment can be with multiple shapes
Formula is implemented, and is not understood as limited to embodiment set forth herein；On the contrary, these embodiments are provided so that this practicality is new
Type more comprehensively and completely, and the design of example embodiment is comprehensively conveyed to those skilled in the art.In figure identical
Reference represents same or similar structure, thus will omit their detailed description.
The term of relative property may be used, such as " relatively low " or " bottom " and " higher " or " top ", to retouch in embodiment
State the relativeness for another assembly for the assembly of icon.It is appreciated that, if the device upset of icon is made thereon
Lower reverse, then being described the assembly in " relatively low " side will become the assembly in " higher " side.Additionally, when certain layer in other layers or
Substrate " on " when it is possible to refer to " direct " on other layers or substrate, or refer to certain layer on other layers or substrate, or refer to other
Sandwiched other layer between layer or substrate.
This utility model provides a kind of engine blade clamping device, for clamping engine blade, engine blade bag
Include the blade being connected and tenon, wherein, engine blade clamping device includes fixture and fixed part, fixture have installing hole and
Fixing hole, installing hole is used for accommodating tenon, and fixed part passes through fixing hole so that tenon is clamped is arranged at installation in the hole.
The structure of engine blade clamping device of the present utility model is simple, can quickly and reliably press from both sides engine blade
Tightly, easy accessibility, can repeatedly use.This utility model is in blade of aviation engine modal test and fatigue test
Applied during blade is fixing and verified.Application result shows, with engine blade clamping device of the present utility model, can
Fast and effeciently engine blade is clamped, while blade reliable grip it is ensured that will not damaged blade surface.
Below for the engine blade of three types, the structure of the engine blade clamping device that it is used is carried out
Describe in detail.It should be appreciated that the form of engine blade is not limited to this, different according to its form, engine blade can be pressed from both sides
The structure of tight device adjusts accordingly, and any change or deformation are all covered by protection domain of the present utility model.
First embodiment
In the present embodiment, engine blade 12 is peg type tenon blade, and it includes blade 120 and tenon.With reference to Fig. 1 and
Fig. 2, which respectively show a kind of peg type tenon blade, and the engine blade clamping dress being applied to peg type tenon blade
Put.
As shown in figure 1, tenon is lug tenon 121, lug tenon 121 center has lug hole 123.Fixed part includes pin
Nail 13, stay-bolt 14 and nut 15, one end of stay-bolt 14 is connected with nut 15, and is anchored on the outside of fixture 11.Draw
The middle part of bar bolt 14 is located at fixing in the hole, and the other end of stay-bolt 14 is located at installs in the hole, and with lug tenon 121 even
Connect, pin 13 is fixedly connected through lug hole 123 with stay-bolt 14, thus lug tenon 121 is fixed on installation in the hole.
In the present embodiment, peg type tenon blade may also include listrium 122, and listrium 122 is connected to lug tenon 121 and leaf
Between body 120.The aperture of installing hole has slope, and listrium 122 and slope fit tightly, thus by peg type tenon blade
It is firmly fixed in fixture 11.
Second embodiment
In the present embodiment, engine blade 22 is swallow-tail form tenon blade, and it includes blade 220 and tenon.With reference to Fig. 3 and
Fig. 4, which respectively show a kind of swallow-tail form tenon blade, and the engine blade clamping dress being applied to swallow-tail form tenon blade
Put.
As shown in figure 3, tenon is swallow-tail form tenon 221.Installing hole is consistent with the shape of swallow-tail form tenon 221.Fixed part
Including clamping screw 24.Fixing hole has female thread.Engine blade clamping device also includes pressing tongue 23 and pressure tongue apertures, presses tongue apertures
Communicatively it is arranged between installing hole and fixing hole, pressure tongue 23 is placed in pressure tongue apertures, and contacts with swallow-tail form tenon 221, compression
Screw rod 24 is threadeded with fixing hole, and pressure tongue 23 can be made to compress swallow-tail form tenon 221 by tightening clamping screw 24, thus
Swallow-tail form tenon blade is firmly fixed in fixture 21.
3rd embodiment
In the present embodiment, engine blade 32 is fir shape tenon blade, and it includes blade 320 and tenon.With reference to Fig. 5 and
Fig. 6, which respectively show a kind of fir shape tenon blade, and the engine blade clamping dress being applied to fir shape tenon blade
Put.
In the present embodiment, tenon is fir shape tenon 321.Rectangular opening is had, fixture 31 top opens up institute in the middle part of fixture 31
State fixing hole.Fixed part includes hold-down bolt 35.Engine blade clamping device also includes chuck 34, and chuck 34 is located at rectangular opening
Interior, installing hole is opened in chuck 34.Fir shape tenon 321 can extend into installation in the hole, and by screwing hold-down bolt 35, makes
The upper surface of chuck 34 supported by hold-down bolt 35, by fir shape tenon 321 clamp in chuck 34.
In the present embodiment, chuck 34 also includes deforming groove, and deformation groove is opened in the outer rim of chuck 34, and with installing hole even
Logical, the outer rim in deformation groove self installation hole is radially expanded, and deforms groove and the centrage of installing hole and the centrage of chuck 34
Identical.Hold-down bolt 35 compresses the upper surface of chuck 34 so that deformation groove shrinks radially inward, and then makes fir shape tenon
321 are fitted tightly with chuck 34.
In the present embodiment, engine blade clamping device also includes baffle plate 33, and baffle plate 33 is supported on fixture 31, and fixture
The side of 31 side and chuck 34 is all resisted against baffle plate 33, realizes horizontal direction positioning in fixture 31 for the chuck 34.
In the present embodiment, there is between the upper surface of chuck 34 and the interior upper wall of rectangular opening gap, conveniently chuck 34 is put
In the rectangular opening of fixture 31.
In the present embodiment, fir shape tenon blade may also include listrium 322, listrium 322 be connected to fir shape tenon 321 with
Between blade 320.Listrium 322 can be resisted against the changeover portion between deformation groove and installing hole, in order to fir shape tenon blade
Positioning.
Above engine blade clamping device, only, illustrates this practicality taking the blade of this three kinds of tenon forms as a example
New specific design with implementation process it is not limited to the concrete structure of blade, type and purposes, for the technology of this area
For personnel, this utility model can have various modifications and variations.All of the present utility model spirit and principle within, made
Any modification, equivalent substitution and improvement etc., should be included within protection domain of the present utility model.
In sum, engine blade clamping device of the present utility model has advantages below：
1) this utility model is various for actual Turbine Blade Fir Tree Roots form complexity, and on-plane surface tenon structure is difficult to
The feature being fixedly clamped, devises the blade clamping device of three kinds of tenon forms, can effectively simulate the actual installation of working-blade
State, and blade surface will not be caused damage.
2) the blade clamping device of three kinds of tenon forms designed by, structure is simple, clamping effect is good, easy accessibility, can
Repeatedly use.
Although exemplary embodiment describing this utility model with reference to several, it is to be understood that, term used is explanation
With exemplary and nonrestrictive term.Because this utility model can be embodied as in a variety of forms without deviating from practical new
The spirit of type or essence, it should therefore be appreciated that above-described embodiment is not limited to any aforesaid details, and should be in appended claims
Widely explain in the spirit and scope being limited, therefore fall into the whole changes in claim or its equivalent scope and remodeling
All should be appended claims to be covered.
Claims (8)
1. a kind of engine blade clamping device, for clamping engine blade, described engine blade includes the leaf being connected
, it is characterised in that described engine blade clamping device includes fixture and fixed part, described fixture has installing hole for body and tenon
And fixing hole, described installing hole is used for accommodating tenon, and described fixed part passes through described fixing hole so that described tenon is clamped sets
It is placed in described installation in the hole.
2. engine blade clamping device as claimed in claim 1 is it is characterised in that described engine blade is peg type tenon
Head lobe piece, described tenon is lug tenon, and described lug tenon center has lug hole；Described fixed part includes pin, pull bar
Bolt and nut, one end of described stay-bolt is connected with described nut, and is anchored on the outside of described fixture, described pull bar spiral shell
The middle part of bolt is located at described fixing in the hole, and the other end of described stay-bolt is located at described installation in the hole, and with described lug tenon
Head connects, and described pin is fixedly connected through described lug hole with described stay-bolt, thus described lug tenon is fixed on
Described installation in the hole.
3. engine blade clamping device as claimed in claim 2 is it is characterised in that described peg type tenon blade also includes
Listrium, described listrium is connected between described lug tenon and described blade；The aperture of described installing hole has slope, described
Listrium is fitted tightly with described slope.
4. engine blade clamping device as claimed in claim 1 is it is characterised in that described engine blade is swallow-tail form tenon
Head lobe piece, described tenon is swallow-tail form tenon；Described installing hole is consistent with the shape of described swallow-tail form tenon；Described fixed part bag
Include clamping screw；Described engine blade clamping device also includes pressing tongue and pressure tongue apertures, and described pressure tongue apertures is communicatively arranged at institute
State between installing hole and described fixing hole, described pressure tongue is placed in described pressure tongue apertures, and contacts with described swallow-tail form tenon, described
Clamping screw is threadeded with described fixing hole, and described pressure tongue can be made to compress described dovetail by tightening described clamping screw
Shape tenon.
5. engine blade clamping device as claimed in claim 1 is it is characterised in that described engine blade is fir shape tenon
Head lobe piece, described tenon is fir shape tenon；The middle part of described fixture has a rectangular opening, and the top of described fixture opens up described solid
Determine hole；Described fixed part includes hold-down bolt；Described engine blade clamping device also includes chuck, and described chuck is located at described
Rectangle in the hole, described installing hole is opened in described chuck；Described fir shape tenon can extend into described installation in the hole, and passes through
Screw described hold-down bolt so that the upper surface of described chuck supported by described hold-down bolt, by described fir shape tenon clampingly
In described chuck.
6. engine blade clamping device as claimed in claim 5 is it is characterised in that described chuck also includes deforming groove, institute
State the outer rim that deformation groove is opened in described chuck, and connect with described installing hole, the described deformation outer rim from described installing hole for the groove
Radially expand, described deformation groove is identical with the centrage of described chuck with the centrage of described installing hole；Described compression
The upper surface of chuck described in bolt presses is so that described deformation groove shrinks radially inward, and then makes described fir shape tenon
Fit tightly with described chuck.
7. engine blade clamping device as claimed in claim 5 it is characterised in that described engine blade clamping device also
Including baffle plate, described baffle plate is supported on described fixture, and the side of the side of described fixture and described chuck is all resisted against institute
State baffle plate.
8. engine blade clamping device as claimed in claim 5 is it is characterised in that the upper surface of described chuck and described square
Between the interior upper wall in shape hole, there is gap.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620785802.2U CN205940943U (en) | 2016-07-25 | 2016-07-25 | Engine blade clamping device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620785802.2U CN205940943U (en) | 2016-07-25 | 2016-07-25 | Engine blade clamping device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205940943U true CN205940943U (en) | 2017-02-08 |
Family
ID=57926005
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620785802.2U Active CN205940943U (en) | 2016-07-25 | 2016-07-25 | Engine blade clamping device |
Country Status (1)
| Country | Link |
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| CN (1) | CN205940943U (en) |
Cited By (12)
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| CN107328568A (en) * | 2017-08-09 | 2017-11-07 | 海盐猛凌汽车配件有限公司 | Dog bone bar portion yield strength detects construction package and its detection method |
| CN107796696A (en) * | 2017-11-30 | 2018-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | The clamping device of aero-engine high-pressure turbine blade fatigue behaviour examination |
| CN108981629A (en) * | 2018-05-30 | 2018-12-11 | 中国航发动力股份有限公司 | A kind of engine blade measuring device |
| CN109029889A (en) * | 2018-08-27 | 2018-12-18 | 烟台大学 | A kind of the vibration-testing experimental rig and its test method of blade of aviation engine |
| CN109500682A (en) * | 2018-11-14 | 2019-03-22 | 中国航发动力股份有限公司 | A kind of antifatigue method improving tenon peg type construction rotor blade |
| CN110426171A (en) * | 2019-08-13 | 2019-11-08 | 中国航发贵阳发动机设计研究所 | A kind of fixture and its application method of turbine blade vibration fatigue test |
| CN112922794A (en) * | 2019-12-05 | 2021-06-08 | 河北新天科创新能源技术有限公司 | Blade replacing device and method of wind driven generator |
| CN112975758A (en) * | 2021-03-17 | 2021-06-18 | 中国航发动力股份有限公司 | Blade tenon tooth protection device and tenon tooth protection method thereof |
| CN113280979A (en) * | 2021-06-21 | 2021-08-20 | 中国民航大学 | Sudden-load unbalance applying device for simulating blade flying off |
| CN113695878A (en) * | 2021-11-01 | 2021-11-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for mounting cover plate on groove of tenon tooth air inlet window of high-pressure turbine blade |
| CN114708783A (en) * | 2022-04-12 | 2022-07-05 | 西北工业大学 | Detachable model and method for aircraft engine high-pressure compressor for teaching |
| CN115014790A (en) * | 2022-06-14 | 2022-09-06 | 南京航空航天大学 | Turbojet engine testing device and method for assembling ceramic matrix composite blades |
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2016
- 2016-07-25 CN CN201620785802.2U patent/CN205940943U/en active Active
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| CN107328568B (en) * | 2017-08-09 | 2023-08-08 | 海盐猛凌汽车配件有限公司 | Canine bone stem yield strength detection structural assembly and detection method thereof |
| CN107328568A (en) * | 2017-08-09 | 2017-11-07 | 海盐猛凌汽车配件有限公司 | Dog bone bar portion yield strength detects construction package and its detection method |
| CN107796696A (en) * | 2017-11-30 | 2018-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | The clamping device of aero-engine high-pressure turbine blade fatigue behaviour examination |
| CN108981629A (en) * | 2018-05-30 | 2018-12-11 | 中国航发动力股份有限公司 | A kind of engine blade measuring device |
| CN109029889A (en) * | 2018-08-27 | 2018-12-18 | 烟台大学 | A kind of the vibration-testing experimental rig and its test method of blade of aviation engine |
| CN109029889B (en) * | 2018-08-27 | 2023-09-26 | 烟台大学 | Vibration test device and method for aero-engine blade |
| CN109500682A (en) * | 2018-11-14 | 2019-03-22 | 中国航发动力股份有限公司 | A kind of antifatigue method improving tenon peg type construction rotor blade |
| CN110426171A (en) * | 2019-08-13 | 2019-11-08 | 中国航发贵阳发动机设计研究所 | A kind of fixture and its application method of turbine blade vibration fatigue test |
| CN112922794A (en) * | 2019-12-05 | 2021-06-08 | 河北新天科创新能源技术有限公司 | Blade replacing device and method of wind driven generator |
| CN112922794B (en) * | 2019-12-05 | 2022-04-19 | 河北新天科创新能源技术有限公司 | Blade replacing device and method of wind driven generator |
| CN112975758A (en) * | 2021-03-17 | 2021-06-18 | 中国航发动力股份有限公司 | Blade tenon tooth protection device and tenon tooth protection method thereof |
| CN113280979A (en) * | 2021-06-21 | 2021-08-20 | 中国民航大学 | Sudden-load unbalance applying device for simulating blade flying off |
| CN113695878A (en) * | 2021-11-01 | 2021-11-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for mounting cover plate on groove of tenon tooth air inlet window of high-pressure turbine blade |
| CN114708783A (en) * | 2022-04-12 | 2022-07-05 | 西北工业大学 | Detachable model and method for aircraft engine high-pressure compressor for teaching |
| CN115014790A (en) * | 2022-06-14 | 2022-09-06 | 南京航空航天大学 | Turbojet engine testing device and method for assembling ceramic matrix composite blades |
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| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |