CN217331619U - Aeroengine ground test bench - Google Patents
Aeroengine ground test bench Download PDFInfo
- Publication number
- CN217331619U CN217331619U CN202220304695.2U CN202220304695U CN217331619U CN 217331619 U CN217331619 U CN 217331619U CN 202220304695 U CN202220304695 U CN 202220304695U CN 217331619 U CN217331619 U CN 217331619U
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- support
- fixedly connected
- engine
- bracket
- aircraft engine
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- 238000012360 testing method Methods 0.000 title claims abstract description 32
- 238000009434 installation Methods 0.000 claims abstract description 14
- 230000007246 mechanism Effects 0.000 claims description 11
- 230000003014 reinforcing effect Effects 0.000 claims description 7
- 239000011159 matrix material Substances 0.000 claims description 3
- 239000000725 suspension Substances 0.000 claims 2
- 230000002787 reinforcement Effects 0.000 claims 1
- 238000011160 research Methods 0.000 abstract description 8
- 230000008878 coupling Effects 0.000 abstract description 7
- 238000010168 coupling process Methods 0.000 abstract description 7
- 238000005859 coupling reaction Methods 0.000 abstract description 7
- 238000012549 training Methods 0.000 abstract description 3
- 238000013461 design Methods 0.000 abstract description 2
- 238000001514 detection method Methods 0.000 abstract description 2
- 238000003745 diagnosis Methods 0.000 abstract description 2
- 238000012544 monitoring process Methods 0.000 abstract description 2
- 238000011161 development Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Testing Of Engines (AREA)
Abstract
The utility model is suitable for an aviation test technical field provides an aeroengine ground test bench, include: a mounting frame, a support foot, having: first support and second support, wherein, the rigid coupling that first support was erect in on the installation frame, just the second support set up in one side of first support, and with swing joint between the installation frame to and, aeroengine, its swing joint in first support with between the second support, this aeroengine testboard size is little, the simple structure has significance in daily teaching and scientific research, not only can develop conventional teaching practice courses such as engine structure, engine degree of depth detection, engine failure diagnosis and state monitoring, can realize moreover that the experimental training project that can't be carried out in the real standard of traditional engine, equipment is based on teaching research design, the high specially adapted teaching research of degree of safety.
Description
Technical Field
The utility model belongs to the technical field of the aviation test, especially, relate to an aeroengine ground test bench.
Background
The performance of the aircraft engine, which is a core component of the aircraft, directly determines the overall performance of the aircraft, and in order to ensure the excellent performance of the aircraft engine and ensure the smooth implementation of various procedures such as the design, development and maintenance of the aircraft engine, the ground test of the aircraft engine becomes an important task.
Due to the rapid development of aeronautical science and technology in recent years, the requirements and standards for test benches for aircraft engine testing are constantly increasing. The method mainly shows that the test content is more and more complex, the test requirement of the aero-engine is more and more, the types of test items and parameters are more and more, and different parameters of the aero-engine during working are required to be recorded in most laboratory or research institute environments.
Therefore, the test rig must be able to satisfy the tests of different flight conditions of the aircraft engine. Furthermore, there is a need for a ground trial test platform for aircraft engines to meet the above parameters.
SUMMERY OF THE UTILITY MODEL
The utility model provides an aeroengine ground test bench aims at solving the problem of mentioning in the above-mentioned background art.
The utility model discloses a realize like this, an aeroengine ground test bench that tries on bus, include: a mounting frame, a support foot, having: first support and second support, wherein, the rigid coupling that first support was erect in on the installation frame, just the second support set up in one side of first support, and with swing joint between the installation frame to and, aeroengine, its swing joint in first support with between the second support.
Preferably, the installation frame is enclosed to close the concatenation by a plurality of support fixing bases along the rectangle structure and forms, just first support includes: erect rigid coupling in the both sides that the symmetry set up support the first stand on the fixing base top end face, and two horizontal rigid coupling has the horizontal pole between the top of first stand, the second support includes: the first stand columns are arranged on one sides of the two first stand columns in parallel, the second stand columns are detachably connected with the supporting and fixing seats, and mounting mechanisms movably connected with the aero-engine are arranged at the top ends of the two second stand columns.
Preferably, each of the mounting mechanisms has: lower mount pad, its rigid coupling in corresponding the top of second stand, the top of mount pad is down gone up the mount pad in detachable fixedly connected with still, wherein, corresponds the setting down the mount pad with the centre gripping is fixed with the connecting axle between the last mount pad, the connecting axle is close to fixed mounting has the stores pylon of hanging on an aeroengine's a tip, just hang the stores pylon with aeroengine's outer wall fixed connection.
Preferably, the bottom fixed mounting of horizontal pole has fixed knot, just fixed knot with can dismantle the connection between aeroengine's the outer wall.
Preferably, each second stand is far away from one side of first stand, still is provided with the strengthening rib of slope, wherein, the top of strengthening rib with the outer wall rigid coupling of second stand, and the bottom with support the fixing base rigid coupling.
Preferably, a plurality of universal wheels are fixedly mounted on the bottom of the mounting frame in a matrix manner, wherein each universal wheel is provided with a locking braking mechanism.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses an aeroengine ground test bench:
the aero-engine test bench is small in size and simple in structure, has important significance in daily teaching and scientific research, can be used for developing conventional teaching practice courses such as engine structure, engine depth detection, engine fault diagnosis and state monitoring, can be used for realizing experimental practical training items which cannot be developed in the traditional engine practical training, is designed based on teaching research, and is high in safety degree and particularly suitable for teaching research.
Compared with the existing finished product test bed, the self-made test bed is more suitable for university teaching and research, and has low operation cost, low later maintenance cost and easy later upgrading/modification; meanwhile, the device has a high commercial popularization value and is engine ground testing equipment which is currently lacking in other aviation universities and small and medium-sized navigation enterprises which lack test beds.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is an enlarged view of a portion A of FIG. 1;
fig. 3 is a front view of the present invention;
fig. 4 is a top view of the present invention;
fig. 5 is a left side view of the present invention;
fig. 6 is a right side view of the present invention;
in the figure:
1. a mounting frame; 11. a supporting fixed seat;
2. a support leg; 21. a first bracket; 211. a first upright post; 212. a cross bar; 213. a fixing buckle; 22. a second bracket; 221. a second upright post; 222. reinforcing ribs;
3. an aircraft engine;
4. an installation mechanism; 41. a lower mounting seat; 42. an upper mounting seat; 43. a connecting shaft; 44. hanging a hanging rack; 5. a universal wheel.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments, it is to be understood that the specific embodiments described herein are only used for explaining the present invention, and are not used for limiting the present invention.
Referring to fig. 1, 3, and 5-6, the present invention provides a technical solution:
an aeroengine ground test run testboard, includes:
the installation frame 1 is formed by encircling and splicing a plurality of supporting fixed seats 11 along a rectangular structure;
the bottom of the installation frame 1 is also provided with a plurality of universal wheels 5 in a matrix, wherein each universal wheel 5 is provided with a locking brake mechanism.
Specifically, in this embodiment, the mounting frame 1 is formed by splicing at least four supporting fixing seats 11 along a rectangular frame structure, the connection stability between the two supporting fixing seats 11 is enhanced by welding at the joint of the two adjacent supporting fixing seats 11, meanwhile, a plurality of universal wheels 5 are further mounted and fixed at the bottom of the mounting frame 1, the mounting frame 1 can be moved to any position in a work place through the universal wheels 5, so that the aero-engine 3 can be moved, and furthermore, a locking braking mechanism is further arranged on the universal wheels 5, and can effectively stop the mounting frame 1 at a current preset position, so that unnecessary shaking or displacement of the mounting frame is avoided.
Referring to fig. 1-6, the supporting leg 2 has: the aeroengine comprises a first bracket 21, a second bracket 22 and an aeroengine 3, wherein the first bracket 21 is vertically and fixedly connected to the mounting frame 1, the second bracket 22 is arranged on one side of the first bracket 21 and is movably connected with the mounting frame 1, and the aeroengine 3 is movably connected between the first bracket 21 and the second bracket 22;
and the first bracket 21 includes: the first upright posts 211 are vertically and fixedly connected to the top end surfaces of the two symmetrically arranged two side supporting fixing seats 11, and a cross rod 212 is horizontally and fixedly connected between the top ends of the two first upright posts 211;
the second bracket 22 includes: the second upright columns 221 are arranged on one sides of the two first upright columns 211 in parallel and detachably connected with the supporting and fixing seat 11, and the top ends of the two second upright columns 221 are respectively provided with an installation mechanism 4 movably connected with the aircraft engine 3;
each mounting mechanism 4 has: the lower mounting seat 41 is fixedly connected to the top of the corresponding second upright column 221, the upper mounting seat 42 is also detachably and fixedly connected above the lower mounting seat 41, a connecting shaft 43 is clamped and fixed between the correspondingly arranged lower mounting seat 41 and the upper mounting seat 42, a hanging rack 44 is fixedly mounted at one end part of the connecting shaft 43 close to the aircraft engine 3, and the hanging rack 44 is fixedly connected with the outer wall of the aircraft engine 3;
the bottom of the cross rod 212 is fixedly provided with a fixing buckle 213, and the fixing buckle 213 is detachably connected with the outer wall of the aero-engine 3;
an inclined reinforcing rib 222 is further disposed on one side of each second upright column 221, which is far away from the first upright column 211, wherein the top end of the reinforcing rib 222 is fixedly connected with the outer wall of the second upright column 221, and the bottom end of the reinforcing rib is fixedly connected with the support fixing seat 11.
Specifically, two vertical first vertical columns 211 are symmetrically and fixedly mounted on the mounting frame 1, a cross bar 212 is horizontally arranged between the tops of the two first vertical columns 211, meanwhile, fixing buckles 213 are fixedly mounted at the bottoms of the cross bar 212, and the outer wall of the aircraft engine 3 can be fixed through the fixing buckles 213, so that the aircraft engine 3 is lifted;
further, on one side of the first bracket 21, two second brackets 22 are further provided, each second bracket 22 including: erect and set up in first stand 211 one side, and the perpendicular to supports second stand 221 of fixing base 11, mount pad 41 under the top installation of second stand 221 is fixed, simultaneously, corresponding being provided with on mount pad 41 down, it is provided with connecting axle 43 (the preferred mode that adopts the centre gripping of connecting axle 43) to go up between mount pad 42 and the mount pad 41 down, simultaneously, connecting axle 43 is provided with on being close to aircraft engine 3's a tip and hangs stores pylon 44, through hanging stores pylon 44 and fixed knot 213 mutually supporting, can realize the hoist and mount to aircraft engine 3, thereby guaranteed follow-up measurement to experimental parameter.
It should be noted that second upright 221 may be adjusted according to the specific size and installation manner of aircraft engine 3, and specifically, may be horizontally displaced along the top end surface of support fixing seat 11 on one side of first upright 211, so as to determine the specific installation position thereof.
It should be understood that, by installing and fixing the reinforcing ribs 222 which are obliquely arranged at positions on one side of the two second vertical columns 221 away from the corresponding first vertical column 211, the overall structural strength of the second bracket 22 can be improved, and thus, the stable hoisting of the aircraft engine 3 can be realized.
The utility model discloses a theory of operation and use flow: the utility model discloses install the back:
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (6)
1. The utility model provides an aeroengine ground test bench of taking a trial run which characterized in that includes:
a mounting frame (1);
a support foot (2) having:
a first bracket (21) and a second bracket (22);
the first support (21) is vertically and fixedly connected to the mounting frame (1), and the second support (22) is arranged on one side of the first support (21) and is movably connected with the mounting frame (1);
and an aircraft engine (3) which is movably connected between the first bracket (21) and the second bracket (22).
2. An aircraft engine ground test run test bench according to claim 1, characterized in that the mounting frame (1) is formed by a plurality of supporting fixing seats (11) which are spliced together along a rectangular structure;
and the first bracket (21) comprises:
the first vertical columns (211) are vertically and fixedly connected to the top end faces of the two symmetrically arranged supporting and fixing seats (11), and a cross rod (212) is horizontally and fixedly connected between the top ends of the two first vertical columns (211);
the second bracket (22) includes:
the second upright columns (221) are arranged on one sides of the two first upright columns (211) in parallel and are detachably connected with the supporting and fixing seat (11);
the top ends of the two second upright columns (221) are respectively provided with an installation mechanism (4) movably connected with the aero-engine (3).
3. An aircraft engine ground test rig according to claim 2, wherein each of said mounting mechanisms (4) has:
a lower mounting seat (41) fixedly connected to the top of the corresponding second upright column (221);
an upper mounting seat (42) is also detachably and fixedly connected above the lower mounting seat (41);
a connecting shaft (43) is clamped and fixed between the lower mounting seat (41) and the upper mounting seat (42) which are correspondingly arranged;
the connecting shaft (43) is close to one end part of the aero-engine (3) and is fixedly provided with a suspension rack (44), and the suspension rack (44) is fixedly connected with the outer wall of the aero-engine (3).
4. An aircraft engine ground test run according to claim 2, characterized in that a fixing buckle (213) is fixedly installed at the bottom of the cross bar (212), and the fixing buckle (213) is detachably connected with the outer wall of the aircraft engine (3).
5. An aircraft engine ground test run according to claim 2, characterized in that each of said second uprights (221), on the side remote from said first upright (211), is further provided with an inclined reinforcement bar (222);
the top end of the reinforcing rib (222) is fixedly connected with the outer wall of the second upright post (221), and the bottom end of the reinforcing rib is fixedly connected with the supporting and fixing seat (11).
6. An aircraft engine ground test run according to claim 1, characterized in that a plurality of universal wheels (5) are fixedly mounted in a matrix at the bottom of the mounting frame (1);
wherein each universal wheel (5) is provided with a locking braking mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220304695.2U CN217331619U (en) | 2022-02-15 | 2022-02-15 | Aeroengine ground test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220304695.2U CN217331619U (en) | 2022-02-15 | 2022-02-15 | Aeroengine ground test bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217331619U true CN217331619U (en) | 2022-08-30 |
Family
ID=82996455
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220304695.2U Expired - Fee Related CN217331619U (en) | 2022-02-15 | 2022-02-15 | Aeroengine ground test bench |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217331619U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
-
2022
- 2022-02-15 CN CN202220304695.2U patent/CN217331619U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220830 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |