CN114563166B - Aeroengine nacelle ventilation cooling port grid angle test device - Google Patents
Aeroengine nacelle ventilation cooling port grid angle test device Download PDFInfo
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- CN114563166B CN114563166B CN202011356609.4A CN202011356609A CN114563166B CN 114563166 B CN114563166 B CN 114563166B CN 202011356609 A CN202011356609 A CN 202011356609A CN 114563166 B CN114563166 B CN 114563166B
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- connecting shaft
- cooling port
- angle
- clamping groove
- vent
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- 238000009423 ventilation Methods 0.000 title claims abstract description 38
- 238000012360 testing method Methods 0.000 title claims abstract description 37
- 238000001816 cooling Methods 0.000 title claims abstract description 36
- 238000009434 installation Methods 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 238000010998 test method Methods 0.000 claims 8
- 239000007788 liquid Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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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
-
- 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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to an aero-engine nacelle ventilation cooling port grid angle test device, which comprises: a vent base (1) having a vent; and the grating plate (3) is installed in the ventilation opening of the ventilation opening base (1) in an angle adjustable way. The grating plate (3) is installed in the vent of the vent base (1) in an angle-adjustable manner, and the air quantity of the nacelle when the grating plates with different angles are installed at the ventilation cooling port of the nacelle can be measured by changing the angle of the grating plate (3), so that the problem of higher cost of preparing independent grating vent test pieces with different angles in the related technology is solved.
Description
Technical Field
The invention relates to the field of aeroengines, in particular to an aeroengine nacelle ventilation cooling port grid angle test device.
Background
The engine nacelle comprises an air inlet channel, a fan cover and a thrust reverser, wherein the fan cover and the engine form the fan nacelle. Various accessories and combustible liquid pipelines are arranged in the fan cabin. The accessories transfer a lot of heat to the fan nacelle during operation of the engine. If the heat cannot be timely dissipated, the temperature in the cabin can be rapidly increased, so that the accessory cannot work normally; meanwhile, when the liquid pipeline in the nacelle leaks, the liquid forms combustible steam under the action of high temperature, and if the liquid is not evacuated in time, fire can be possibly caused. It is necessary to develop a ventilation cooling design for the fan compartment of the power plant. The nacelle ventilation cooling system can cool various accessories arranged in the fan nacelle on one hand, and can provide ventilation air for the fan nacelle on the other hand, so as to prevent combustible gas from gathering in the nacelle and eliminate fire hazards.
The air outlet of the nacelle ventilating and cooling system is generally arranged on the fan housing, and the nacelle ventilating and cooling system can be directly opened on the skin to serve as an air outlet, or can be connected to the skin of the fan housing by adopting a separate grid type air outlet. The flow coefficient of the grid type exhaust port is insensitive to the flow state of the external flow field, and the grid type exhaust port has the advantage of ensuring that the flow coefficient of the outlet of the aircraft is relatively stable during operation, so that the grid type exhaust port is more widely applied.
The angle of the different exhaust grilles can have a large influence on the flow coefficient of the exhaust port. The influence trend of different grating angles on the flow coefficient of the exhaust port is researched through analysis and combination test, so that the most suitable grating angle is designed and optimized, and the ventilation cooling air efficiency in the fan cabin is ensured. On the other hand, the independent grille vent test pieces with different angles are prepared, and the cost is high.
Disclosure of Invention
The invention aims to provide an aeroengine nacelle ventilation cooling port grating angle test device so as to solve the problem that the cost for preparing independent grating exhaust port test pieces with different angles is high in the related art.
According to an aspect of an embodiment of the present invention, there is provided an aero-engine nacelle ventilation cooling port grille angle test apparatus, including:
a vent base having a vent;
The grating plate is installed in the ventilation opening of the ventilation opening base in an angle adjustable mode.
Optionally, the aero-engine nacelle ventilation cooling port grid angle test device further comprises a connecting shaft, a through hole allowing the connecting shaft to pass through is formed in the vent base, and the connecting shaft passes through the through hole and is connected with the first end of the grid plate.
Optionally, the aero-engine nacelle ventilation cooling port grid angle test device further comprises:
a plurality of first positioning portions arranged along a circumferential direction of the connecting shaft;
The second positioning part can be matched with any first positioning part in a positioning way so as to limit the grating plate at an installation angle,
One of the first positioning part and the second positioning part is arranged on the vent base, and the other is arranged on the connecting shaft.
Optionally, the second positioning portion is a plurality of.
Alternatively, the process may be carried out in a single-stage,
The first positioning part comprises a first clamping groove arranged on the vent base;
the second positioning part comprises a second clamping groove arranged on the connecting shaft;
The test device further comprises a stop block arranged in the first clamping groove and the second clamping groove.
Optionally, the vent base includes:
the frame encloses the ventilation opening; and
And the annular component is arranged on the outer side of the frame and sleeved on the connecting shaft, and the first clamping groove is formed in the annular component.
Optionally, the first clamping groove penetrates the annular component along the radial direction of the connecting shaft.
Alternatively, the process may be carried out in a single-stage,
The first clamping groove is arranged on the inner peripheral surface of the through hole;
The second clamping groove extends from the end face of the connecting shaft, which is positioned outside the vent base, towards the vent base along the axial direction of the connecting shaft.
Optionally, an external thread is provided at one end of the connecting shaft, which connects the grating plates, and a threaded hole adapted to the external thread is provided at the first end of the grating plates.
Optionally, the second end of the grating plate is connected to the vent base by a screw.
By applying the technical scheme of the invention, the grating plate angle is adjustably arranged in the ventilation opening of the ventilation opening base, and the air quantity when the ventilation cooling opening of the nacelle is provided with grating plates with different angles can be measured by changing the angle of the grating plate, so that the problem of higher cost for preparing independent grating exhaust port test pieces with different angles in the related technology is solved.
Other features of the present invention and its advantages will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the related art, the drawings that are required to be used in the embodiments or the related technical descriptions will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort to those skilled in the art.
FIG. 1 shows a schematic structural view of an aero-engine nacelle ventilated cooling port grille angle test apparatus in accordance with an embodiment of the present invention;
FIG. 2 shows an enlarged view at A in FIG. 1;
FIG. 3 shows a schematic structural view of a vent base of an aircraft engine nacelle ventilated cooling port grill angle test device according to an embodiment of the invention;
FIG. 4 shows a schematic structural view of a grid plate of an aero-engine nacelle ventilated cooling port grid angle test device of an embodiment of the invention;
FIG. 5 shows a schematic structural view of a connecting shaft of an aero-engine nacelle ventilated cooling port grille angle test apparatus according to an embodiment of the invention;
FIG. 6 shows a schematic block diagram of an aircraft engine nacelle ventilated cooling port grid angle test device according to an embodiment of the invention;
FIG. 7 shows a schematic perspective view of another angle of an aircraft engine nacelle ventilated cooling port grill angle test device according to an embodiment of the invention;
FIG. 8 shows a schematic perspective view of an aero-engine nacelle ventilated cooling port grid angle test apparatus (grid plate uninstalled in place) of an embodiment of the invention; and
Fig. 9 shows an enlarged view at B in fig. 8.
In the figure:
1. a vent base; 2. an annular member; 3. a grating plate; 4. a threaded hole; 5. an external thread; 6. a second positioning portion; 7. a connecting shaft; 8. a stop block; 9. a screw; 10. a first positioning portion; 11. and a through hole.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
1-2 And 7-9, the aero-engine nacelle ventilation cooling port grid angle test apparatus of the present embodiment includes a vent base 1 and a grid plate 3, the vent base 1 having a vent; the grating plates 3 are mounted angularly adjustable in the ventilation openings of the ventilation opening base 1.
In this embodiment, the grating plate 3 is installed in the ventilation opening of the ventilation opening base 1 in an angle adjustable manner, and the air quantity when the ventilation cooling opening of the nacelle is installed with grating plates of different angles can be measured by changing the angle of the grating plate 3, so that the problem of higher cost of preparing independent grating air outlet test pieces of different angles in the related art is improved.
The aero-engine nacelle ventilation cooling port grid angle test device also comprises a connecting shaft 7. As shown in fig. 3, the vent base 1 is provided with a through hole 11 allowing the connection shaft 7 to pass therethrough, and the connection shaft 7 is connected to the first end of the grid plate 3 through the through hole 11.
As shown in fig. 4, the end of the grating plate 3 is provided with threaded holes 4. As shown in fig. 5, the first end of the connecting shaft 7 is provided with an external thread 5, which external thread 5 is adapted to the threaded hole 4 of the grating plate 3.
In some embodiments, the through hole 11 is a threaded hole, and the external thread 5 of the connecting shaft 7 is matched with the through hole 11. The parameters of the internal thread of the through hole 11 are identical to the parameters of the threaded hole 4.
The first end of the connecting shaft 7 is connected to the threaded hole 4 of the first end of the grating plate 3 through the through hole 11. The first end of the connection shaft 7 is connected to the grating plates 3 such that the grating plates 3 can rotate with the connection shaft 7.
In some embodiments, through holes 11 are provided on both opposite sides of the vent base 1. Both ends of the grating plate 3 are provided with threaded holes 4. The screw holes 4 at both ends of the grating plate 3 are respectively opposed to the through holes 11 on both sides of the vent base 1. As shown in fig. 7, the second end of the grating plate 3 is connected to the vent base 1 by means of screws 9 passing through the through holes 11.
The aero-engine nacelle ventilation cooling port grid angle test device further comprises a plurality of first positioning portions 10 and second positioning portions 6. The plurality of first positioning portions 10 are arranged side by side in the circumferential direction of the connecting shaft 7; the second positioning portions 6 may be in positioning engagement with any of the first positioning portions 10 to define the grid plate 3 at an installation angle.
One of the first positioning portion 10 and the second positioning portion 6 is provided on the vent base 1, and the other is provided on the connecting shaft 7. In the present embodiment, the first positioning portion 10 is provided on the vent base 1, and the second positioning portion 6 is provided on the connecting shaft 7.
In some embodiments, the second positioning portion 6 and the first positioning portion 10 are each a plurality of positioning portions arranged along the axial direction of the connecting shaft 7 to position the grid plate 3 at more angles, which is advantageous in making the data of the test more and more intensive.
The first positioning part 10 comprises a first clamping groove arranged on the vent base 1; the second positioning part 6 comprises a second clamping groove arranged on the connecting shaft 7; the test device further comprises a stopper 8 provided in the first and second card grooves, into which the stopper is inserted to prevent the connection shaft 7 from rotating with respect to the vent base 1, thereby defining the grating plate 3 at a specific installation angle. Fig. 6 shows a schematic structural view of the stopper 8 of the present embodiment.
The vent base 1 comprises a frame and an annular component 2, wherein the frame encloses a vent; the annular component 2 is mounted on the outer side of the frame and sleeved on the connecting shaft 7, and the first clamping groove is formed in the annular component 2.
In the present embodiment, the through holes 11 are formed on the opposite side frames of the frame, the ring-shaped member 2 is mounted on one of the two side frames on which the through holes 11 are provided, and the portion of the connecting shaft 7 extending outside the frame is fitted inside the ring-shaped member 2.
The first clamping groove penetrates through the annular component 2 along the radial direction of the connecting shaft 7, the second clamping groove is formed in the peripheral surface of the connecting shaft 7, and the stop block 8 can be sequentially inserted into the first clamping groove and the second clamping groove along the radial direction of the connecting shaft 7.
In other embodiments, the first clamping groove is provided on the inner peripheral surface of the through hole 11 and extends from the outer surface of the vent base 1 toward the inside of the vent base 1; the second locking groove extends from the end surface of the connecting shaft 7 located outside the vent base 1 toward the vent base 1 along the axial direction of the connecting shaft 7. The stopper 8 is insertable into the first and second catching grooves in the axial direction of the connecting shaft 7.
The assembling steps of the aero-engine nacelle ventilation cooling port grid angle test device of the embodiment include:
the first step: the annular member 2 may be connected to either side of the rim of the vent base 1 by welding, ensuring that the annular member 2 is aligned with the through-holes 11 on the side of the rim, and that the inner diameter of the annular member 2 is slightly larger than the inner diameter of the through-holes 11.
And a second step of: the grating plate 3 is placed in the middle of the vent base 1 such that the holes of both end surfaces of the screw holes 4 are aligned with the through holes 11 on both side surfaces of the vent base 1. The diameters of the threaded holes 4 and the through holes 11 are consistent. The connecting shaft 7 is then screwed into the threaded bore 4 through the through bore 11. As in fig. 8 and 9.
And a third step of: after the angle of each grid plate is adjusted to reach the target value, the stopper 8 is used to engage the first engagement groove of the annular member 2 and the second engagement groove of the connecting shaft, as shown in fig. 1 and 2.
Fourth step: a corresponding number of screws 9 are screwed into the threaded holes on the other side of the vent base 1, so that the grid plate 3 and the vent base 1 are relatively fixed.
Finally, the gap between the grating plate 3 and the vent base 1 may be filled with a putty or the like.
The foregoing is illustrative of the present invention and is not to be construed as limiting thereof, but rather, any modification, equivalent replacement, improvement or the like which comes within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (8)
1. A test method of an aero-engine nacelle ventilation cooling port grid angle test device is characterized by comprising the following steps:
a vent base (1) having a vent;
The grating plate (3) is arranged in the ventilation opening of the ventilation opening base (1) in an angle adjustable way, the air quantity of the ventilation cooling opening of the nacelle when the grating plate (3) with different angles is arranged can be measured by changing the angle of the grating plate (3) so as to study the influence of different grating angles on the flow coefficient of the exhaust opening,
A connecting shaft (7), a through hole (11) allowing the connecting shaft (7) to pass through is arranged on the vent base (1), the connecting shaft (7) passes through the through hole (11) to be connected with the first end of the grating plate (3),
A plurality of first positioning portions (10) arranged along a circumferential direction of the connecting shaft (7);
A second positioning part (6) which can be matched with any first positioning part (10) in a positioning way so as to limit the grating plate (3) at an installation angle,
One of the first positioning part (10) and the second positioning part (6) is arranged on the vent base (1), and the other is arranged on the connecting shaft (7).
2. The test method of an aero-engine nacelle ventilation cooling port grid angle test device according to claim 1, wherein the number of second positioning parts (6) is plural.
3. The test method of the aero-engine nacelle ventilating and cooling port grille angle test apparatus according to claim 1, wherein,
The first positioning part (10) comprises a first clamping groove arranged on the vent base (1);
the second positioning part (6) comprises a second clamping groove arranged on the connecting shaft (7);
the test device further comprises a stop block (8) arranged in the first clamping groove and the second clamping groove.
4. A test method of an aero-engine nacelle ventilation cooling port grid angle test device according to claim 3, wherein the vent base (1) comprises:
The frame surrounds the ventilation opening; and
And the annular component (2) is arranged on the outer side of the frame and sleeved on the connecting shaft (7), and the first clamping groove is formed in the annular component (2).
5. The test method of an aero-engine nacelle ventilating cooling port grille angle test apparatus according to claim 4, wherein said first clamping groove penetrates said annular member (2) in a radial direction of said connecting shaft (7).
6. A test method for an aero-engine nacelle ventilating cooling port grille angle test apparatus as defined in claim 3, wherein,
The first clamping groove is arranged on the inner peripheral surface of the through hole (11);
The second clamping groove extends from the end face of the connecting shaft (7) located on the outer side of the vent base (1) towards the vent base (1) along the axial direction of the connecting shaft (7).
7. The test method of the aeroengine nacelle ventilating and cooling port grating angle test device according to claim 1, wherein one end of the connecting shaft (7) connected with the grating plate (3) is provided with an external thread (5), and a first end of the grating plate (3) is provided with a threaded hole (4) matched with the external thread (5).
8. Test method of an aeroengine nacelle ventilation cooling port grid angle test device according to claim 1, characterized in that the second end of the grating plate (3) is connected to the vent base (1) by means of screws (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011356609.4A CN114563166B (en) | 2020-11-27 | 2020-11-27 | Aeroengine nacelle ventilation cooling port grid angle test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011356609.4A CN114563166B (en) | 2020-11-27 | 2020-11-27 | Aeroengine nacelle ventilation cooling port grid angle test device |
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| Publication Number | Publication Date |
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| CN114563166A CN114563166A (en) | 2022-05-31 |
| CN114563166B true CN114563166B (en) | 2024-06-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011356609.4A Active CN114563166B (en) | 2020-11-27 | 2020-11-27 | Aeroengine nacelle ventilation cooling port grid angle test device |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN210881611U (en) * | 2019-11-25 | 2020-06-30 | 昆山耀致辉机电科技有限公司 | Automobile ventilation opening device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP4809116B2 (en) * | 2006-04-27 | 2011-11-09 | 川崎重工業株式会社 | Crosswind test facility |
| FR2975255B1 (en) * | 2011-05-13 | 2013-06-14 | Airbus Operations Sas | METHOD AND APPARATUS FOR COOLING AIR FILTRATION FOR ELECTRICAL EQUIPMENT MOUNTED IN AVIONIC AND AIRCRAFT BAY EQUIPPED WITH SUCH A BAY |
| CN202256070U (en) * | 2011-07-20 | 2012-05-30 | 辽宁忠旺集团有限公司 | Pressure test device for skirt plate ventilation opening grating of motor train unit equipment cabin |
| CN204730424U (en) * | 2015-03-12 | 2015-10-28 | 珠海格力电器股份有限公司 | Air deflector, air deflector rotating structure and air conditioner comprising air deflector and air deflector rotating structure |
| CN205861717U (en) * | 2016-07-20 | 2017-01-04 | 国网山西省电力公司电力科学研究院 | A kind of generator amature ventilating duct wind speed tester |
| SI3367009T1 (en) * | 2017-02-28 | 2023-10-30 | Soler & Palau Research, S.L. | Centrifugal fan |
| CN107757348A (en) * | 2017-11-22 | 2018-03-06 | 怡得乐电子(杭州)有限公司 | A kind of adjustable air-inlet grille for automobile of opening angle |
| CN210440875U (en) * | 2019-07-26 | 2020-05-01 | 李爱兰 | Display device for education software convenient to angle regulation |
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2020
- 2020-11-27 CN CN202011356609.4A patent/CN114563166B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104713213A (en) * | 2015-03-12 | 2015-06-17 | 珠海格力电器股份有限公司 | Air deflector, air deflector rotating structure and air conditioner comprising air deflector and air deflector rotating structure |
| CN210881611U (en) * | 2019-11-25 | 2020-06-30 | 昆山耀致辉机电科技有限公司 | Automobile ventilation opening device |
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| CN114563166A (en) | 2022-05-31 |
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