CN110118658B - Containing structure for rotor blade flying-off test - Google Patents
Containing structure for rotor blade flying-off test Download PDFInfo
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- CN110118658B CN110118658B CN201810111786.2A CN201810111786A CN110118658B CN 110118658 B CN110118658 B CN 110118658B CN 201810111786 A CN201810111786 A CN 201810111786A CN 110118658 B CN110118658 B CN 110118658B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The invention aims to provide a containing structure for a rotor blade flying test, which is used for surrounding a rotor at the periphery of the rotor in the radial direction so as to contain a flying block flying off from a rotor blade of the rotor; the containing structure comprises an inner ring plate, an outer ring plate and a plurality of middle clapboards; the middle partition plates are distributed and arranged along the circumferential direction and are respectively connected with the outer wall surface of the inner ring plate and the inner wall surface of the outer ring plate so as to partition a plurality of chambers which are continuously distributed along the circumferential direction between the inner ring plate and the outer ring plate; after the flyoff block breaks through the inner ring plate and enters one chamber of the plurality of chambers, the flyoff block can continue to break through the middle partition plate and enter another chamber adjacent to the one chamber, and the flyoff block is accommodated in the another chamber. Since the portion of the inner ring plate that forms the further chamber is not broken through by the flyweights, the flyweights can be accommodated well and do not return to the region where the rotor blades rotate.
Description
Technical Field
The invention relates to a containing structure for a rotor blade flying test.
Background
The flying off of the rotor blades of an aircraft engine can lead to damage to the engine and even compromise the safety of the whole aircraft and the life of the passengers. The fan flying block has high energy and can penetrate through a casing to endanger a control circuit, an aircraft oil way, an oil tank, a cabin and the like, and once the equipment is damaged, the aircraft loses control, oil leakage and fire, and the aircraft is damaged and people are killed, so that serious safety accidents are caused. Blade fly-off testing is an important test in the development of aircraft engines, given the severity of the blade fly-off event.
Through the blade flying test, the inclusiveness of the fan casing can be verified, but the test cost is expensive due to certain destructiveness of the test. In order to fully utilize the value of the test equipment, a small-mass flying-off test (namely a small sudden unbalance response test) of the blades is usually carried out before a fan casing containment test so as to obtain the response of the rotor under the action of an impact load and the load transmitted by the rotor to a bearing casing and other stator parts.
When the blades are in fly-off in the actual operation of the engine, the fly-off mass is returned due to the existence of the fan casing, but in the small-mass fly-off test, the return of the fly-off mass is not desired, so that the continuous development of a series of mass fly-off tests is not influenced.
When a mass flying test is carried out, a step-by-step loading method is generally adopted, namely, a rotor flies out smaller mass firstly by methods such as prefabricating cracks, the impact response of the rotor and a support system under small unbalance is researched, then the flying mass is gradually increased, and a series of tests are carried out; in the series of tests, the flying mass block is required to be ensured not to return to the rotor, otherwise, the returned mass block collides with the rotor blade, and the collided blade influences the dynamic balance of a rotor system and the strength of the rotor, so that the smooth proceeding and developing of the subsequent tests are influenced; if the impacted blade fails to repair, the blade needs to be replaced, which not only increases the cost of the test, but may also severely slow the progress of the test. Therefore, a structure is needed for the mass fly-off test, which can "absorb", contain, and contain the flying mass, ensuring that the flying mass does not return to the rotor rotation region.
Some laboratories adopt a method of installing a simple box-type protective cover instead of installing a fan case, and the protective cover is internally provided with an impact reduction protective layer such as foam and a lead plate, but in an actual test, under the influence of factors such as a flying-off direction, an impact posture and the like, a flying-off block can be embedded into the protective layer sometimes and cannot be embedded into the protective layer sometimes, and the test safety risk coefficient is still relatively high.
The existing and common fan accommodating casings comprise alloy casings, Kevlar (Kevlar) wound alloy casings, composite material casings and the like, but the product type casings can ensure that the fly-off quality cannot fly out of the casings, but cannot be ensured to return to the rotor to collide with the rotor blades.
US6053696 discloses an impact resistant fibre composite casing, the casing having three layers of main structures with no gaps between the layers, which can ensure that the fan flying block does not fly out of the casing, but cannot ensure that the flying block does not return to collide with the rotor.
US patent US4534698 uses a double honeycomb structure containing kevlar scrim for retaining the flyoff chips, which better buffers the impact of the flyoff mass, and the scrim retains smaller flyoff masses, the possibility of the larger flyoff mass returning to the rotor rotation zone and colliding with the rotor blades still remaining.
The chinese patent CN205560243U adopts a 4-layer structure, which comprises a buffer isolation cover layer, an energy absorption block layer, an energy buffer layer, and a protective shell layer from inside to outside in sequence, wherein an air isolation layer is provided between the buffer isolation cover layer and the energy absorption block layer, and the flying block penetrates through the buffer isolation cover layer and then enters the air isolation layer. However, during testing, the incoming air insulation flyaway mass still has a certain tendency to return to the test chamber from the point where the damping insulation cover layer is broken down, causing an impact with the rotor blade.
Disclosure of Invention
The invention aims to provide a containing structure for a rotor blade flying test, which can prevent a flying block from returning to a rotating area of a rotor blade, so that the rotor blade is prevented from being damaged due to collision with the flying block.
The containing structure of the rotor blade flying test for achieving the purpose is used for being arranged around the rotor at the periphery of the rotor so as to contain flying blocks flying from the rotor blades of the rotor;
the containing structure comprises an inner ring plate, an outer ring plate and a plurality of middle clapboards; the inner wall surface of the inner ring plate is opposite to the rotor blade, and the outer wall surface of the inner ring plate is opposite to the inner wall surface of the outer ring plate; the intermediate partition plates are arranged at intervals in a distributed manner along the circumferential direction between the inner ring plate and the outer ring plate, and are respectively connected with the outer wall surface of the inner ring plate and the inner wall surface of the outer ring plate so as to partition a plurality of chambers which are continuously distributed along the circumferential direction between the inner ring plate and the outer ring plate.
The containing structure for the rotor blade flying test is further characterized in that a chamber is formed between the inner ring plate and the outer ring plate and the adjacent middle partition plate.
The containing structure for the rotor blade flying test is further characterized in that the inner ring plate, the outer ring plate and the rotor are arranged on the same center line.
The containing structure for the rotor blade flying test is further characterized in that the middle partition plate inclines in the direction opposite to the rotation direction of the rotor and forms a certain angle with the radial direction of the center line of the rotor so as to ensure that the flying block collides with the front face of the middle partition plate.
The containing structure for the rotor blade flying test is further characterized by further comprising a first end support and a second end support;
the first end bracket comprises a first outer ring plate fixing piece, a first inner ring plate fixing piece and a plurality of first middle clapboard fixing pieces;
the second end bracket comprises a second outer ring plate fixing piece, a second inner ring plate fixing piece and a plurality of second middle clapboard fixing pieces;
the first outer ring plate fixing piece and the second outer ring plate fixing piece are clamped and fixed at two axial ends of the outer ring plate, the first inner ring plate fixing piece and the second inner ring plate fixing piece are clamped and fixed at two axial ends of the inner ring plate, the first middle clapboard fixing piece and the second middle clapboard fixing piece are clamped and fixed at two axial ends of the middle clapboard,
the first middle clapboard fixing pieces are respectively connected with the first inner ring plate fixing piece and the first outer ring plate fixing piece;
the second middle clapboard fixing pieces are respectively connected with the second inner ring plate fixing pieces and the second outer ring plate fixing pieces.
The containing structure for the rotor blade flying test is further characterized in that the inner ring plate and the outer ring plate are formed by combining and splicing a plurality of arc-shaped plates.
The containing structure for the rotor blade flying test is further characterized in that the plurality of intermediate bulkheads are rotationally and symmetrically arranged around the central line.
The containing structure for the rotor blade flying-off test is further characterized in that a first annular fixing part is arranged on the radial inner side of the first inner ring plate mounting part, a second annular fixing part is arranged on the radial inner side of the second inner ring plate mounting part, and the first annular fixing part and the second annular fixing part are used for installing the first inner ring plate mounting part and the second inner ring plate mounting part so as to install the containing structure.
The containing structure for the rotor blade flying test is further characterized in that the first annular fixing part and the second annular fixing part are provided with through holes for installation.
The containing structure for the rotor blade flying test is further characterized by further comprising a driving system, wherein the driving system is used for driving the rotor to rotate.
The positive progress effects of the invention are as follows: the invention provides a containing structure for a rotor blade flying test, which is used for surrounding a rotor at the periphery of the rotor to contain a flying block flying off from a rotor blade of the rotor; the containing structure comprises an inner ring plate, an outer ring plate and a plurality of middle clapboards; the inner wall surface of the inner ring plate is arranged opposite to the rotor blades, and the outer wall surface of the inner ring plate is arranged opposite to the inner wall surface of the outer ring plate; the middle clapboards are distributed and arranged at intervals along the circumferential direction between the inner ring board and the outer ring board and are respectively connected with the outer wall surface of the inner ring board and the inner wall surface of the outer ring board so as to form a plurality of chambers which are continuously distributed along the circumferential direction between the inner ring board and the outer ring board; after the flyoff block breaks through the inner ring plate and enters one chamber of the plurality of chambers, the flyoff block can continue to break through the middle partition plate and enter another chamber adjacent to the one chamber, and the flyoff block is accommodated in the another chamber.
The part of the inner ring plate used for forming the other chamber is not punctured by the flying block, so that the flying block can be well accommodated, cannot slide to other regions with puncturing points on the inner ring plate, and cannot return to the rotating region of the rotor blade, and the rotor blade is prevented from being damaged due to collision with the flying block.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a cross-sectional view of a containment structure for a rotor blade fly-off test of the present invention, showing a rotor;
FIG. 2 is a schematic view of a first end bracket according to the present invention;
FIG. 3 is a schematic view of a second end mount of the present invention;
FIG. 4 is a schematic illustration of a containment structure for a rotor blade fly-off test of the present invention, showing the impact path of the fly-off block;
FIG. 5 is a schematic view of the flyweight of the present invention impacting the inner ring plate at the most penetrating angle;
FIG. 6 is a schematic view of the flyweight of the present invention impacting the inner ring plate at the most difficult angle to penetrate;
FIG. 7 is a schematic view of an inner ring plate according to the present invention;
FIG. 8 is a schematic view of the first end mount and the second end mount arranged axially forward and aft of one another in accordance with the present invention;
FIG. 9 is a schematic view of the first end bracket and the second end bracket clamping the inner race plate in accordance with the present invention;
FIG. 10 is a schematic view showing a plurality of intermediate partitions arranged in a circumferentially dispersed manner according to the present invention;
FIG. 11 is a schematic view of the first end bracket and the second end bracket clamping the inner ring plate and the plurality of middle spacers in accordance with the present invention;
FIG. 12 is a schematic view of an outer ring plate according to the present invention;
FIG. 13 is a schematic view of a containment structure for a rotor blade fly-off test in accordance with the present invention, wherein the outer ring plate is clamped in place by a first end bracket and a second end bracket;
FIG. 14 is a front view of containment structure for a rotor blade fly-off test in accordance with the present invention, viewed in the axial direction.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner" and "outer" etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
It should be noted that fig. 1-14 are exemplary only, are not drawn to scale, and should not be construed as limiting the scope of the invention as actually claimed. "axial", "radial" and circumferential are with reference to the rotor 4.
In order to ensure the safety of the rotor blade, the blade flying test is an important test in the development process of the aircraft engine.
Fig. 1 shows a containment structure 3 for a rotor blade fly-off test according to the invention, which is arranged around a rotor 4 at the periphery of the rotor 4 in order to accommodate a fly-off mass m flying off a rotor blade 2 of the rotor 4. The rotor 4 comprises a rotor blade 2 and a rotating shaft 1, and in one embodiment, the containing structure 3 for the rotor blade flying test further comprises a driving system, and the driving system can drive the rotating shaft 1 to rotate so as to drive the rotor blade 2 to rotate.
The flyoff mass m may be a mass thrown tangentially from the top of the rotor blade 2 as shown in fig. 4, and impacts the containment structure 3 after flying out.
In order to increase the containment of the containment structure 3 of the vane fly-off test, the containment structure 3 of the rotor vane fly-off test comprises an inner ring plate 31, an outer ring plate 33 and a plurality of intermediate bulkheads 32. The inner wall surface 31a of the inner ring plate 31 is provided to face the rotor blade 2, and the outer wall surface 31b of the inner ring plate 31 is provided to face the inner wall surface 33a of the outer ring plate 33; the intermediate partitions 32 are arranged at intervals in a circumferentially dispersed manner between the inner ring plate 31 and the outer ring plate 33, and each connects the outer wall surface 31b of the inner ring plate 31 and the inner wall surface 33a of the outer ring plate 33, respectively, to partition the plurality of chambers 3a continuously distributed in the circumferential direction between the inner ring plate 31 and the outer ring plate 33. The chamber 3a is used to accommodate a flyout mass m which breaks through the inner ring plate 31. A chamber 3a is formed between the inner ring plate 31 and the outer ring plate 33 and the adjacent intermediate partition plate 32.
In one embodiment, the inner ring plate 31 and the outer ring plate 33 are each a circular plate having a certain width in the axial direction. The inner ring plate 31, the outer ring plate 33 and the rotor 4 are disposed concentrically, the center line of the rotor 4 being the axis a-a in fig. 1. In another embodiment, the plurality of intermediate bulkheads 32 are disposed rotationally symmetric about the axis A-A. The term rotationally symmetrical means that any one of the intermediate partitions 32 can be overlapped with another intermediate partition 32 after being rotated by a certain angle around the axis a-a in the circumferential direction.
The impact path of the flyaway mass m impacting the containment structure 3 of the blade flyaway test is described below in conjunction with fig. 4.
As shown in fig. 4, after the flyoff m which flies tangentially from the point E of the top end of the rotor blade 2 hits the inner ring plate 31 at B on the inner ring plate 31 and enters one chamber 3a of the plurality of chambers 3a, since the flyoff m which has punctured the inner ring plate 31 still has large kinetic energy, it can continue flying and continue puncturing the intermediate diaphragm 32 at the point C of the intermediate diaphragm 32 and enter another chamber 3a adjacent to the one chamber 3 a; thereafter, the kinetic energy of the flyoff block m is not sufficient to break through the next intermediate diaphragm 32 in its flight path again at point D, but is bounced by the next intermediate diaphragm 32 at point D and falls to the bottom of the other chamber 3a to be accommodated by the other chamber 3 a.
As can be seen from the above analysis, the bottom of the other chamber 3a, i.e. the portion of the inner ring plate 31 that forms the other chamber 3a, is not broken down by the flyoff block m, so that the flyoff block m can be well accommodated, and does not slide to other regions of the inner ring plate 31 where there is a breakdown point (e.g. the bottom of the one chamber 3a) and further does not return to the region where the rotor blade 2 rotates, thereby preventing the rotor blade 2 from being damaged due to collision with the flyoff block m.
After completion of the one-time test, the flight path can be determined from the collision points of the inner ring plate 31 and the intermediate partition plate 32, and the flight azimuth, the collision attitude, and the like can be estimated.
In one embodiment, the intermediate diaphragm 32 is inclined in a direction opposite to the direction of rotation R of said rotor 4 and at an angle to the radial direction of the centre line of the rotor 4 to ensure that the flyweights m impact positively with the intermediate diaphragm 32 to enable the flyweights m to break through the first intermediate diaphragm 32.
The containment structure 3 of the blade fly-off test is described in more detail next.
With reference to fig. 1, 2 and 3, the containing structure 3 further comprises a first end bracket 34 and a second end bracket 35;
the first end bracket 34 includes a first outer ring plate fixing member 343, a first inner ring plate fixing member 341, and a plurality of first middle spacer fixing members 342; second end bracket 35 includes a second outer ring plate mount 353, a second inner ring plate mount 351, and a plurality of second mid-diaphragm mounts 352; first outer ring plate fixing members 343 and second outer ring plate fixing members 353 are fixed by being clamped to both axial ends of the outer ring plate 33, first inner ring plate fixing members 341 and second inner ring plate fixing members 351 are fixed by being clamped to both axial ends of the inner ring plate 31, first intermediate diaphragm fixing members 342 and second intermediate diaphragm fixing members 352 are fixed by being clamped to both axial ends of the intermediate diaphragm 32, and a plurality of first intermediate diaphragm fixing members 342 are respectively connected to the first inner ring plate fixing members 341 and the first outer ring plate fixing members 343; a plurality of second middle spacer fixing members 352 are respectively connected to the second inner ring plate fixing member 351 and the second outer ring plate fixing member 353.
First intermediate bulkhead securing member 342 and second intermediate bulkhead securing member 352 may be angled to allow intermediate bulkhead 32 to assume a desired angle when clamped and secured.
In one embodiment, the radially inner side of the first inner ring web mounting member 341 is provided with a first annular fixing portion 341a, the radially inner side of the second inner ring web mounting member 351 is provided with a second annular fixing portion 351a, the first and second annular fixing portions 341a, 351a being for mounting the first and second inner ring web mounting members 341, 351 and thus the containment structure 3. In another embodiment, the first annular fixing portion 341 and the second annular fixing portion 351 are both provided with through holes for installation.
Fig. 7, 8, 9, 10, 11, 12, 13, 14 show in more detail the specific structure of containment structure 3 of a rotor blade fly-off test in an embodiment of the invention.
As shown in fig. 7, the inner ring plate 31 is a circular plate, and in this embodiment, the inner ring plate 31 is formed by combining and splicing a plurality of arc plates, so as to facilitate replacement of a damaged portion of the inner ring plate 31. In designing the inner ring plate 31, a preferred embodiment is such that when the flyweight m hits the inner ring plate 31 at the angle that is most difficult to penetrate, as shown in fig. 6, the flyweight m can still penetrate the inner ring plate 31.
Fig. 8 shows the first and second end brackets 34, 35 arranged axially one behind the other, and fig. 9 shows a state in which the first and second end brackets 34, 35 clamp and fix the inner ring plate 31, wherein the first and second inner ring plate fixtures 341, 351 clamp and fix the inner ring plate 31 axially one behind the other.
Fig. 10 shows a state in which the plurality of intermediate bulkheads 32 are arranged in a dispersed manner in the circumferential direction, and fig. 11 shows a state in which the first end bracket 34 and the second end bracket 35 clamp and fix the inner ring plate 31 and the plurality of intermediate bulkheads 32, in which the first intermediate bulkhead fixing member 342 and the second intermediate bulkhead fixing member 352 clamp and fix the intermediate bulkheads 32 in axial tandem. In designing and manufacturing the plurality of intermediate bulkheads 32, a preferred embodiment is that the plurality of intermediate bulkheads 32 allow the flyweight m to penetrate one layer, not both layers.
Fig. 12 shows an outer ring plate 33 having a circular plate shape, and the outer ring plate 33 is formed by combining and splicing a plurality of arc plates to facilitate replacement of a damaged portion of the outer ring plate 33. In designing the outer ring plate 33, a preferred embodiment is where the flyoff blocks m may not yet penetrate the outer ring plate 33 when they strike the outer ring plate 33 at the angle of easiest penetration as shown in fig. 5.
Fig. 13 shows the containment structure 3 of a complete rotor blade fly-off test, in which the outer ring plate is clamped in place by a first end bracket 34 and a second end bracket 35. Specifically, the first outer ring plate fixing member 343 and the second outer ring plate fixing member 353 clamp the fixed outer ring plate 33 in axial tandem.
FIG. 14 is a front view of containment structure 3 for a rotor blade fly-off test of the present invention, wherein rotor 4 used for the test has been installed in place. The direction of rotation of the rotor 4 is indicated by arrow R.
When the containing structure 3 of the rotor blade flying test is used for a repeatability test, only the impacted part needs to be replaced; when different magnitude fly-off tests are carried out, the lamina with corresponding thickness can be replaced.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make modifications and variations without departing from the spirit and scope of the present invention.
Claims (9)
1. A containment structure for a rotor blade fly-off test, for being arranged around a rotor (4) at the periphery of the rotor (4) to accommodate a fly-off mass (m) flying off a rotor blade (2) of the rotor (4);
the test method is characterized in that the containing structure (3) of the rotor blade flying test comprises an inner ring plate (31), an outer ring plate (33) and a plurality of middle partition plates (32); an inner wall surface (31a) of the inner ring plate (31) is arranged opposite to the rotor blade (2), and an outer wall surface (31b) of the inner ring plate (31) is arranged opposite to an inner wall surface (33a) of the outer ring plate (33); the middle clapboards (32) are arranged at intervals in a distributed mode along the circumferential direction between the inner ring plate (31) and the outer ring plate (33), and are respectively connected with the outer wall surface (31b) of the inner ring plate (31) and the inner wall surface (33a) of the outer ring plate (33) so as to form a plurality of chambers (3a) which are continuously distributed along the circumferential direction between the inner ring plate (31) and the outer ring plate (33);
the middle partition plate (32) of the straight plate structure is inclined along the direction opposite to the rotating direction (R) of the rotor (4) and forms a certain angle with the radial direction of the central line of the rotor (4) so as to ensure that the flyoff block (m) is collided with the front surface of the middle partition plate (32).
2. The containment structure for rotor blade fly-off test according to claim 1, wherein one of said chambers (3a) is defined between said inner ring plate (31) and said outer ring plate (33) and said intermediate partition (32) adjacent thereto.
3. The containment structure for rotor blade fly-off test according to claim 2, wherein the inner ring plate (31), the outer ring plate (33) and the rotor (4) are disposed concentrically.
4. Containment structure for rotor blade fly-off tests according to claim 1, characterised in that the containment structure (3) further comprises a first end bracket (34) and a second end bracket (35);
the first end bracket (34) includes a first outer ring plate securing member (343), a first inner ring plate securing member (341), and a plurality of first middle barrier securing members (342);
the second end bracket (35) includes a second outer ring plate mount (353), a second inner ring plate mount (351), and a plurality of second mid-diaphragm mounts (352);
the first outer ring plate fixing member (343) and the second outer ring plate fixing member (353) are clamped and fixed at both axial ends of the outer ring plate (33), the first inner ring plate fixing member (341) and the second inner ring plate fixing member (351) are clamped and fixed at both axial ends of the inner ring plate (31), the first middle diaphragm fixing member (342) and the second middle diaphragm fixing member (352) are clamped and fixed at both axial ends of the middle diaphragm (32),
the first middle clapboard fixing pieces (342) are respectively connected with the first inner ring plate fixing piece (341) and the first outer ring plate fixing piece (343);
the second middle spacer fixing members (352) are respectively connected to the second inner ring plate fixing member (351) and the second outer ring plate fixing member (353).
5. The containment structure for rotor blade flying test according to claim 1, wherein the inner ring plate (31) and the outer ring plate (33) are formed by combining and splicing a plurality of arc-shaped plates.
6. The containment structure for rotor blade fly-off tests according to claim 3, wherein a plurality of said intermediate bulkheads (32) are arranged rotationally symmetrically with respect to said centerline.
7. The containment structure of a rotor blade fly-off test according to claim 4, wherein a radially inner side of the first inner ring plate fixture (341) is provided with a first annular fixing portion (341a), and a radially inner side of the second inner ring plate fixture (351) is provided with a second annular fixing portion (351a), the first annular fixing portion (341a) and the second annular fixing portion (351a) being used for mounting the first inner ring plate fixture (341) and the second inner ring plate fixture (351) and further mounting the containment structure (3).
8. The containment structure for the rotor blade fly-off test according to claim 7, wherein the first annular fixing portion (341a) and the second annular fixing portion (351a) are each provided with a through hole for mounting.
9. Containment structure for rotor blade fly-off tests according to claim 1, characterised in that the containment structure (3) for rotor blade fly-off tests further comprises a drive system for driving the rotor (4) in rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810111786.2A CN110118658B (en) | 2018-02-05 | 2018-02-05 | Containing structure for rotor blade flying-off test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810111786.2A CN110118658B (en) | 2018-02-05 | 2018-02-05 | Containing structure for rotor blade flying-off test |
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| Publication Number | Publication Date |
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| CN110118658A CN110118658A (en) | 2019-08-13 |
| CN110118658B true CN110118658B (en) | 2021-04-02 |
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| WO2023197243A1 (en) * | 2022-04-14 | 2023-10-19 | 威刚科技股份有限公司 | Test device for rotary object |
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| US6182531B1 (en) * | 1998-06-12 | 2001-02-06 | The Boeing Company | Containment ring for flywheel failure |
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| WO2013149626A1 (en) * | 2012-04-03 | 2013-10-10 | Babcock Noell Gmbh | Safety device for the container of a flywheel mass |
| CN103368324A (en) * | 2012-04-03 | 2013-10-23 | 波音公司 | Lightweight composite safety containment for flywheel energy storage |
| CN105510044A (en) * | 2015-12-31 | 2016-04-20 | 苏州东菱科技有限公司 | High-speed rotor blade flying-off test device and test method |
| CN205560243U (en) * | 2016-03-18 | 2016-09-07 | 苏州东菱科技有限公司 | High -speed rotation test protection casing |
| CN107462416A (en) * | 2017-08-17 | 2017-12-12 | 沧州巨擎汽车配件有限公司 | Domino formula blasting protection storehouse |
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| CN110118658A (en) | 2019-08-13 |
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