CN117516943A - High-temperature environment simulation equipment for aircraft engine accessories - Google Patents
High-temperature environment simulation equipment for aircraft engine accessories Download PDFInfo
- Publication number
- CN117516943A CN117516943A CN202311291348.6A CN202311291348A CN117516943A CN 117516943 A CN117516943 A CN 117516943A CN 202311291348 A CN202311291348 A CN 202311291348A CN 117516943 A CN117516943 A CN 117516943A
- Authority
- CN
- China
- Prior art keywords
- mounting surface
- surface component
- temperature environment
- mounting
- surface assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 39
- 239000011521 glass Substances 0.000 claims abstract description 7
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 238000004321 preservation Methods 0.000 claims description 3
- 239000000565 sealant Substances 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 239000007921 spray Substances 0.000 abstract description 12
- 230000005540 biological transmission Effects 0.000 abstract description 8
- 238000007599 discharging Methods 0.000 abstract description 4
- 238000009413 insulation Methods 0.000 abstract description 4
- 239000000203 mixture Substances 0.000 description 8
- 230000000694 effects Effects 0.000 description 3
- 239000007858 starting material Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
-
- 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
- G01M13/02—Gearings; Transmission mechanisms
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to high-temperature environment simulation equipment for an aircraft engine accessory, and belongs to the field of aircraft engine accessory tests. The invention solves the technical problems of uneven heat temperature, poor sealing property and poor heat insulation property in the high-temperature environment inside the equipment in the existing transmission experiment system equipment. According to the technical scheme, an upper mounting surface assembly, a front mounting surface assembly, a left mounting surface assembly, a right mounting surface assembly, a lower mounting surface assembly and a rear mounting surface assembly are surrounded to form a closed square body, an input port is arranged in the middle of the upper mounting surface assembly, glass windows are arranged on the left mounting surface assembly and the right mounting surface assembly, an air charging port and an air discharging port are arranged on the lower mounting surface assembly, and hot air spray heads are arranged on the front mounting surface assembly, the left mounting surface assembly, the right mounting surface assembly and the rear mounting surface assembly. The hot air is sprayed to the periphery, so that the internal equipment of the high-temperature environment simulation equipment is heated uniformly, and the heat is prevented from being radiated outwards. The invention is used for the high-temperature environment simulation test of the aircraft engine accessory.
Description
Technical Field
The invention relates to high-temperature environment simulation equipment for an aircraft engine accessory, and belongs to the field of aircraft engine accessory tests.
Background
The accessory case of the aeroengine is one of important components of the engine, and is provided with a starter, a hydraulic pump, a generator and the like, so that test pieces such as the starter, the hydraulic pump, the generator and the like need to simulate high-temperature environments with different temperatures inside an engine body and around the accessory case under different working conditions of the aeroplane in the normal operation test process, and the environment temperature is not lower than 200 ℃ and needs to be arranged in the existing transmission test system equipment.
In the prior art, the transmission test system equipment has uneven heat temperature in the high-temperature environment inside the equipment, so that the simulation test results of test pieces such as a starter, a hydraulic pump and a generator are easily influenced, and the tightness and the heat insulation in the transmission test system equipment are not high, so that the high temperature influences surrounding transmission equipment.
In summary, the existing transmission experimental system equipment has the technical problems of uneven heat temperature in the high-temperature environment inside the equipment and poor tightness and heat insulation.
Disclosure of Invention
The invention aims to solve the technical problems of uneven heat temperature, poor sealing property and poor heat insulation property in the high-temperature environment in equipment in the existing transmission experimental system equipment, and further provides high-temperature environment simulation equipment for accessories of an aeroengine.
The technical scheme of the invention is that the high-temperature environment simulation equipment for the aircraft engine accessory comprises an upper mounting surface component, a front mounting surface component, a left mounting surface component, a right mounting surface component, a lower mounting surface component and a rear mounting surface component which are enclosed to form a closed square body, wherein an input port is arranged in the middle of the upper mounting surface component, the left mounting surface component and the right mounting surface component are both provided with glass windows, an air charging port and an air discharging port are arranged on the lower mounting surface component, and hot air spray heads are arranged on the front mounting surface component, the left mounting surface component, the right mounting surface component and the rear mounting surface component.
As another improvement of the invention, the head shape of the hot air nozzle is a hemispherical shape.
As another improvement of the invention, the front mounting surface component and the rear mounting surface component are provided with a connecting port.
As another improvement of the present invention, the number of the hot air shower nozzles is 5 in the front mounting surface assembly, the number of the hot air shower nozzles is 5 in the rear mounting surface assembly, the number of the hot air shower nozzles is 2 in the left mounting surface assembly, and the number of the hot air shower nozzles is 2 in the right mounting surface assembly.
As another improvement of the invention, the outer surfaces of the front mounting surface component, the left mounting surface component, the right mounting surface component, the lower mounting surface component and the rear mounting surface component are all provided with heat preservation insulating plates.
As another improvement of the invention, the connection parts among the upper mounting surface component, the front mounting surface component, the left mounting surface component, the right mounting surface component, the lower mounting surface component and the rear mounting surface component are all provided with mounting interfaces, and the upper mounting surface component, the front mounting surface component, the left mounting surface component, the right mounting surface component, the lower mounting surface component and the rear mounting surface component are detachably connected through the mounting interfaces.
As another improvement of the invention, a sealing rubber strip is arranged at the mounting interface.
As another improvement of the invention, high-temperature sealant is smeared at the mounting interface.
As another improvement of the invention, the charging port is connected with an external fan through a flange, and the exhaust port is connected with an external exhaust pipeline through a flange.
The invention has the beneficial effects that:
1. the front mounting surface component, the left mounting surface component, the right mounting surface component and the rear mounting surface component are all provided with hot air spray heads, so that hot air is sprayed to the periphery, and compared with a single spray head, the hot air spray head is easier to uniformly heat internal equipment of the high-temperature environment simulation equipment.
2. Glass windows are arranged on the left mounting surface component and the right mounting surface component, and the function is to observe the equipment state in the high-temperature environment simulation equipment through the windows.
3. The lower mounting surface component is provided with an exhaust port and an inflation port, and the exhaust port can be respectively connected with the exhaust port for exhausting hot air in the high-temperature environment simulation equipment and the blower fan so as to charge normal-temperature air into the equipment for cooling, so that the real test environment is simulated.
4. The external surfaces of the front mounting surface component, the left mounting surface component, the right mounting surface component, the lower mounting surface component and the rear mounting surface component are all provided with heat preservation insulating plates, so that the effect of outwards dispersing back heat of high-temperature environment simulation equipment is avoided, and meanwhile, the effect of preventing the equipment surface from being excessively high in temperature and injuring workers is achieved.
5. The sealing rubber strip is arranged at the mounting interface and smeared with sealing rubber, so that the leakage of hot air in the mounting interface is avoided, and the real test environment is simulated.
Drawings
FIG. 1 is a schematic diagram of a high temperature environment simulation device for an aircraft engine accessory according to the present invention.
FIG. 2 is a schematic structural view of an aircraft engine accessory high temperature environment simulation device of the present invention.
FIG. 3 is a schematic view of the structure of an aircraft engine accessory high temperature environment simulation device of the present invention.
Fig. 4 is a schematic structural view of an aircraft engine accessory high-temperature environment simulation device.
Fig. 5 is a schematic diagram of the internal structure of the high-temperature environment simulation device for the accessory of the aero-engine.
Detailed Description
The first embodiment is as follows: referring to fig. 1 to 5, the high-temperature environment simulation device for an aircraft engine accessory according to the present embodiment includes an upper mounting surface assembly 1, a front mounting surface assembly 2, a left mounting surface assembly 3, a right mounting surface assembly 4, a lower mounting surface assembly 5, and a rear mounting surface assembly 6, wherein the upper mounting surface assembly 1 is horizontally fixed, the upper mounting surface assembly 1, the front mounting surface assembly 2, the left mounting surface assembly 3, the right mounting surface assembly 4, the lower mounting surface assembly 5, and the rear mounting surface assembly 6 are enclosed to form a closed square, the uppermost plane assembly is an upper mounting surface assembly, and is a fixed base of the whole high-temperature environment simulation device, and the upper mounting plane assembly is also a front, rear, left, and right 4-surface mounting base; the left mounting plane and the right mounting plane are mounted on a left interface and a right interface of an upper mounting plane, the lower mounting plane component is mounted on the interfaces of the left mounting plane and the right mounting plane, a square structure lacking a front mounting plane component and a rear mounting plane component is integrally formed with the upper mounting plane, the front mounting plane and the rear mounting plane are mounted on the mounting interfaces of the square structure consisting of the upper plane component, the lower plane component, the left plane component and the right plane component, and are the last mounting planes when the equipment is assembled, the high-temperature environment simulation equipment for the aircraft engine accessory further comprises an input port 11, a glass window 8, an air charging port 51, an air outlet 52 and a hot air spray nozzle 9, the middle part of the upper mounting plane component 1 is provided with the input port 11 for inputting power required by a test, and the glass windows 8 are arranged on the left mounting plane component 3 and the right mounting plane component 4, and are made of high-temperature resistant materials, so that the equipment state in the high-temperature environment simulation equipment can be observed through the windows; the lower mounting surface assembly 5 is provided with an inflation inlet 51 and an exhaust outlet 52, and the lower mounting surface assembly is used for being respectively connected with the exhaust outlet to exhaust hot air in the high-temperature environment simulation equipment and is connected with a fan to charge normal-temperature air into the equipment for cooling, so that a real test environment is simulated, the front mounting surface assembly 2, the left mounting surface assembly 3, the right mounting surface assembly 4 and the rear mounting surface assembly 6 are all provided with hot air spray heads 9, the hot air spray heads 9 penetrate through all the assemblies, and the lower mounting surface assembly is used for spraying hot air to the surroundings, so that compared with a single spray head, the lower mounting surface assembly is easier to uniformly heat the internal equipment of the high-temperature environment simulation equipment.
The second embodiment is as follows: the present embodiment is described with reference to fig. 5, and one difference between the present embodiment and the specific embodiment is that the head shape of the hot air shower head 9 is a hemispherical shape. The hemispherical spray heads are uniformly provided with hot air nozzles, so that the hot air blown out by the hemispherical spray heads is more uniformly distributed, and the simulation of a real test environment is facilitated. Other compositions and connection modes are the same as in the first embodiment.
And a third specific embodiment: the present embodiment will be described with reference to fig. 1 to 4, and one difference between the present embodiment and the specific embodiment is that the front mounting surface assembly 2 and the rear mounting surface assembly 6 are each provided with a coupling interface. When the internal temperature of the high-temperature environment simulation equipment is too high, the loading accessory installed through the connecting port extends out of the box body, so that the influence of high temperature on the loading accessory is avoided. Other compositions and connection modes are the same as those of the first or second embodiment.
The specific embodiment IV is as follows: the present embodiment is described with reference to fig. 1 and 5, and is different from the specific embodiment in that the number of the hot air shower nozzles 9 provided in the front mounting surface assembly 2 is 5, the number of the hot air shower nozzles 9 provided in the rear mounting surface assembly 6 is 5, the number of the hot air shower nozzles 9 provided in the left mounting surface assembly 3 is 2, and the number of the hot air shower nozzles 9 provided in the right mounting surface assembly 4 is 2. The hot air spray heads 9 on the mounting surfaces are distributed. The function is to make the internal heating of the high temperature environment simulation equipment more uniform. Other compositions and connection modes are the same as those of the first, second or third embodiments.
Fifth embodiment: the present embodiment will be described with reference to fig. 2 and 4, and one difference between the present embodiment and the specific embodiment is that the outer surfaces of the front mounting surface assembly 2, the left mounting surface assembly 3, the right mounting surface assembly 4, the lower mounting surface assembly 5, and the rear mounting surface assembly 6 are each provided with a heat insulating plate 7. The back heat of the high-temperature environment simulation equipment is prevented from being outwards dispersed, and meanwhile the effect of preventing the surface temperature of the equipment from being too high to hurt workers is achieved. Other compositions and connection modes are the same as any one of the first to fourth embodiments.
Specific embodiment six: the present embodiment is described with reference to fig. 1 to 4, and one difference between the present embodiment and the specific embodiment is that the joints between the upper mounting surface component 1, the front mounting surface component 2, the left mounting surface component 3, the right mounting surface component 4, the lower mounting surface component 5 and the rear mounting surface component 6 are all provided with mounting interfaces, and the upper mounting surface component 1, the front mounting surface component 2, the left mounting surface component 3, the right mounting surface component 4, the lower mounting surface component 5 and the rear mounting surface component 6 are detachably connected through the mounting interfaces. The function is compact structure, simple to operate. Other compositions and connection modes are the same as those of any one of the first to fifth embodiments.
Seventh embodiment: the present embodiment will be described with reference to fig. 1 to 4, and one difference between the present embodiment and the specific embodiment is that a joint strip is provided at the mounting interface. The function is to avoid the leakage of the hot air inside. Other compositions and connection modes are the same as those of any one to six of the embodiments.
Eighth embodiment: the present embodiment is described with reference to fig. 1 to 4, and one difference between the present embodiment and the specific embodiment is that the high-temperature sealant is applied to the mounting interface. The function is to avoid the leakage of the hot air inside. Other compositions and connection modes are the same as those of any one of the first to seventh embodiments.
Detailed description nine: the air charging port 51 is connected with an external fan through a flange, and the air discharging port 52 is connected with an external air discharging pipeline through a flange. The flange connection is convenient to install. Other compositions and connection modes are the same as those of any one of the first to eighth embodiments.
The working principle of the present invention is explained with reference to fig. 1 to 5:
the upper mounting surface component is fixed on the lower mounting surface of the upper transmission device, the left mounting surface and the right mounting surface are mounted on the left interface and the right interface of the upper mounting surface, the lower mounting surface component is mounted on the interfaces of the left mounting surface and the right mounting surface, the front mounting surface and the rear mounting surface are mounted on the mounting interfaces of a square structure formed by the upper, the lower, the left and the right plane components, power required by a test is input through an input port, and the state of equipment in high-temperature environment simulation equipment is observed through a window to complete the test.
The above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (9)
1. The utility model provides an aeroengine accessory high temperature environment simulation equipment, includes mounting face subassembly (1), preceding mounting face subassembly (2), left side mounting face subassembly (3), right side mounting face subassembly (4), lower mounting face subassembly (5) and back mounting face subassembly (6), it is fixed to go up mounting face subassembly (1) level, go up mounting face subassembly (1), preceding mounting face subassembly (2), left side mounting face subassembly (3), right side mounting face subassembly (4), down mounting face subassembly (5) and back mounting face subassembly (6) surround into airtight square, a serial communication port, aeroengine accessory high temperature environment simulation equipment still includes input port (11), glass window (8), inflation inlet (51), gas vent (52) and hot air shower nozzle (9), it is provided with input port (11) to go up mounting face subassembly (1) middle part, all be provided with glass window (8) on left side mounting face subassembly (3) and the right side mounting face subassembly (4), be provided with inflation inlet (51) and gas vent (52) on lower mounting face subassembly (5), preceding mounting face subassembly (2), left side subassembly (3), right side mounting face subassembly (4) and back mounting face subassembly (6) all are provided with hot air shower nozzle (9).
2. An aeroengine accessory high temperature environment simulation device according to claim 1, wherein the head shape of the hot air jet (9) is hemispherical.
3. An aircraft engine accessory high temperature environment simulation device according to claim 1, wherein the front mounting surface component (2) and the rear mounting surface component (6) are provided with a coupling interface.
4. An aircraft engine accessory high temperature environment simulation apparatus according to claim 1, wherein the number of hot air jets (9) is 5 in the front mounting face assembly (2), the number of hot air jets (9) is 5 in the rear mounting face assembly (6), the number of hot air jets (9) is 2 in the left mounting face assembly (3), and the number of hot air jets (9) is 2 in the right mounting face assembly (4).
5. An aircraft engine accessory high temperature environment simulation device according to any one of claims 1-4, wherein the outer surfaces of the front mounting surface component (2), the left mounting surface component (3), the right mounting surface component (4), the lower mounting surface component (5) and the rear mounting surface component (6) are provided with heat preservation insulating plates (7).
6. The high-temperature environment simulation device for the aircraft engine accessory according to any one of claims 1 to 4, wherein the connection parts among the upper mounting surface component (1), the front mounting surface component (2), the left mounting surface component (3), the right mounting surface component (4), the lower mounting surface component (5) and the rear mounting surface component (6) are all provided with mounting interfaces, and the upper mounting surface component (1), the front mounting surface component (2), the left mounting surface component (3), the right mounting surface component (4), the lower mounting surface component (5) and the rear mounting surface component (6) are detachably connected through the mounting interfaces.
7. The aircraft engine accessory high temperature environment simulation device according to claim 6, wherein a sealing rubber strip is arranged at the mounting interface.
8. An aircraft engine accessory high temperature environment simulation device according to claim 7, wherein high temperature sealant is applied at the mounting interface.
9. An aeroengine accessory high temperature environment simulation device according to any of claims 1, 2, 3, 7 or 8, wherein the charging port (51) is connected to an external fan via a flange, and the exhaust port (52) is connected to an external exhaust line via a flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311291348.6A CN117516943A (en) | 2023-10-08 | 2023-10-08 | High-temperature environment simulation equipment for aircraft engine accessories |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311291348.6A CN117516943A (en) | 2023-10-08 | 2023-10-08 | High-temperature environment simulation equipment for aircraft engine accessories |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117516943A true CN117516943A (en) | 2024-02-06 |
Family
ID=89742795
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311291348.6A Pending CN117516943A (en) | 2023-10-08 | 2023-10-08 | High-temperature environment simulation equipment for aircraft engine accessories |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117516943A (en) |
-
2023
- 2023-10-08 CN CN202311291348.6A patent/CN117516943A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112747890B (en) | Pneumatic and thermal combined test system and test method | |
| CN117516943A (en) | High-temperature environment simulation equipment for aircraft engine accessories | |
| CN107416214A (en) | A kind of perflation ventilation structure for aircraft secondary power systems | |
| CN210071279U (en) | Temperature control wind tunnel device based on quartz lamp heating | |
| CN113606045B (en) | Large-bypass-ratio turbofan engine core cabin ventilation structure and ventilation method thereof | |
| CN114813156A (en) | High-altitude test bed cold-hot immersion test device and method for turboshaft engine | |
| CN115416880A (en) | Application method of thermal assessment test system for hypersonic aircraft | |
| CN210293611U (en) | Temperature control wind tunnel device based on electromagnetic heating | |
| CN207934996U (en) | A kind of engine heat dissipating device and unmanned plane | |
| CN213769016U (en) | Pneumatic thermal modal test device | |
| CN114264573B (en) | Visual controllable atmospheric boundary layer smoke and cloud diffusion simulation device and method | |
| CN217638811U (en) | Thermal examination device for structural member of hypersonic aircraft | |
| CN210882688U (en) | Aircraft wheel cooling vehicle | |
| CN110411704B (en) | Ejector module for intake and exhaust simulation test of low-speed wind tunnel aircraft | |
| CN204060937U (en) | A kind of aeroengine | |
| CN111017198B (en) | Nacelle for high-altitude flight aircraft wing mixed laminar flow control | |
| CN114112354A (en) | Test method of helicopter air inlet channel anti-icing system | |
| CN209506126U (en) | A kind of hypersonic power heat integration test cabin | |
| CN207969269U (en) | A kind of high power density satellite ground test cooling system | |
| CN219789635U (en) | Energy-saving quick-drying furnace for drying plates | |
| CN207470303U (en) | For the exhaust treatment system of high temperature and pressure big flow gas discharge | |
| CN115072012A (en) | Thermal examination test system for thermal protection structure of hypersonic aircraft | |
| CN212791580U (en) | External spraying equipment of integrated static high voltage generator | |
| CN105370395A (en) | Rainproof and dustproof silent generating set | |
| CN212304289U (en) | Electrical equipment automation control cabinet |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |