Intake and exhaust system for indoor aero-engine complex attitude and high overload test

Abstract

The invention discloses an air intake and exhaust system for an indoor aero-engine complex attitude and high overload test. The air intake and exhaust system comprises a foundation balance weight, a test plant, an exhaust system, an air intake system, a fuel oil system, a trench system and the like. Wherein the foundation balance weight is used for providing fixing, supporting, balance weight and vibration isolation conditions for test equipment; the test plant accommodates an engine test platform and related test equipment, and is provided with an equipment foundation, a crane and an overhaul ladder stand. The air intake and exhaust system is composed of an annular exhaust passage, an exhaust hole, a silencing exhaust tower, an air intake tower rainproof cover, an air intake trench and the like, the air intake and exhaust flow field of the engine is optimized, and the stability of test data is improved; the fuel oil system, the trench system and the equipment foundation guarantee oil supply, power distribution and equipment support of the test. By integrating the functional modules, ground tests on the aero-engine under various complex postures and high overload working conditions in a safe and controllable indoor environment can be achieved, and the aero-engine ground test platform has the advantages of being safe, reliable, high in adaptability, complete in function and the like.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft engine strength testing, and relates to the design of a ground test environment under complex engine attitudes and high overload conditions, and in particular to an indoor aircraft engine complex attitude and high overload test intake and exhaust system, which meets the requirements of various types of engine gyroscopes, attitude and overload tests for explosion protection, impact resistance, rotating intake / exhaust, noise reduction, power supply / oil, anti-overturning, installation, maintenance, etc. Background Art

[0002] Good maneuverability is one of the important indicators for measuring aircraft performance, which requires that the engine must be able to work stably in various attitudes. The general specification requires that the engine should be able to work continuously and satisfactorily in these attitudes, and at the same time, it should work for at least a certain period of time in certain attitudes, and can start and stop smoothly in certain attitudes. The engine should be tested in attitude according to the methods and procedures specified in the specification.

[0003] In recent years, the requirements for aircraft maneuverability have been continuously improved, and engines need to operate under more complex attitudes and overload conditions. High-maneuverability aircraft will produce a variety of complex attitudes during operation, such as large angles of attack, large sideslips, and rapid pitching, which will have a significant impact on the performance and reliability of the engine. Especially under high overload conditions, the engine rotor components and stator components will be subjected to loads far exceeding normal working conditions, which puts higher requirements on the structural strength and service life of the engine.

[0004] In order to verify the working performance of the engine under complex attitude and overload conditions, comprehensive ground test verification is required. Traditional engine tests are mostly carried out on fixed test benches, which cannot simulate the complex attitudes and overload conditions encountered by the engine in actual work. Special complex attitude and overload tests require special test equipment and test environment, and such tests are highly dangerous. During the test, due to the complex loads on the high-speed rotating parts of the engine, there is a risk of parts flying off, and the flying objects may have high kinetic energy, posing a serious threat to the test facilities and personnel safety.

[0005] At present, considering the safety of the test, high-risk engine tests (such as bird swallowing, ice swallowing, etc.) are usually carried out in open areas outdoors, while engine tests with lower risk (such as ground tests and high-altitude tests) are carried out indoors. However, the complex attitude and overload tests of the engine have their own particularities: on the one hand, the test process is extremely dangerous, and once an accident occurs, the consequences are serious; on the other hand, the relevant test data are highly sensitive and need to be kept strictly confidential. If such tests are carried out outdoors, it is not only difficult to deal with possible accidents in a timely manner, but also there is a risk of technical data leakage. In addition, the complex attitude and overload tests of the engine put forward special requirements for the test facilities. During the test, the engine works in a continuously changing attitude, which brings great challenges to the design of the intake and exhaust system. At the same time, the test facilities also need to have functions such as explosion-proof, impact-resistant, and noise reduction, and meet the process requirements such as power supply and oil supply. Traditional engine test plants are difficult to meet these special requirements.

[0006] In summary, the existing engine test plant and equipment are difficult to meet the needs of complex attitude and overload tests, especially in terms of safety, environmental adaptability, supporting facilities, scalability, noise control, and multi-degree-of-freedom coupling test capabilities. Therefore, developing a test plant system that can meet the needs of complex attitude and overload tests of aircraft engines, with high safety, good environmental adaptability, complete supporting facilities, strong scalability, excellent noise control, and multi-degree-of-freedom coupling test capabilities is a technical problem that needs to be solved in the field of aircraft engine testing. Summary of the invention

[0007] 1. Purpose of the invention In view of the above-mentioned defects and shortcomings in the prior art, the present invention provides an indoor aircraft engine complex attitude and high overload test intake and exhaust system. By integrating the foundation counterweight, plant protection structure, intake and exhaust system, fuel system and its supporting facilities, the plant can meet the requirements of various types of engine gyroscopes, attitude and overload tests for explosion protection, impact resistance, rotating intake / exhaust, noise reduction, power supply / oil, anti-overturning, installation, maintenance, etc. It has the characteristics of good safety, strong confidentiality, full functionality and wide application range, and provides a reliable test verification environment for complex attitude and overload tests of aircraft engines.

[0008] (II) Technical solution In order to achieve the purpose of the invention and solve the technical problems, the present invention adopts the following technical solutions: An indoor aircraft engine complex attitude and high overload test intake and exhaust system is used to meet the ground test requirements of aircraft engines under complex attitudes (such as pitch, sideslip, roll, etc.) and high overload conditions, and provide a safe, stable and controllable indoor test space, including at least foundation counterweights, test workshops, exhaust systems and intake systems, including: The foundation counterweight is set on the ground, including a load-bearing bottom plate and an anti-overturning counterweight block, which is used to provide fixation, support, counterweight and vibration isolation conditions for the test equipment, bear the dynamic load of the engine test platform, and reduce the influence of external interference on the test accuracy; The test plant is arranged on the foundation counterweight and is used to accommodate the engine test platform and related test equipment. The bottom surface is provided with a foundation pit and an equipment foundation arranged in the foundation pit and used to install and fix the engine test platform. The overall structural size is determined according to the size and layout requirements of the test platform to ensure the safety of the test and meet the test operation space requirements; The exhaust system is arranged on the roof of the test plant, and is used to collect, guide and discharge high-temperature exhaust gas generated during the engine test, including an annular exhaust duct arranged on the roof of the test plant and extending downward to the top of the test platform, and a plurality of exhaust holes arranged on the roof of the test plant and distributed circumferentially and connected to the annular exhaust duct, wherein the annular exhaust duct is composed of an inner wall of the annular exhaust duct and an outer wall of the annular exhaust duct, wherein the outer wall of the annular exhaust duct is surrounded by the wall of the test plant, and the inner wall of the annular exhaust duct is a tubular structure and its inner diameter is adapted to the size of the foundation pit; The air intake system is arranged on the foundation counterweight, and is used to provide a stable test air intake flow in the test building. It includes at least one air intake trench and multiple air intake ducts. The air intake trench is an open trench which is opened on the periphery of the foundation pit in the test building and is generally annular. A plurality of foundation pit air intake holes connecting the air intake trench and the foundation pit are circumferentially opened on the wall surface between the air intake trench and the foundation pit. The multiple air intake ducts are circumferentially distributed on the outer wall of the air intake trench, and each air intake duct extends outward to the outside of the test building, and is used to guide the airflow into the inside of the test building.

[0009] (III) Technical Effect Compared with the prior art, the indoor aircraft engine complex attitude and high overload test intake and exhaust system of the present invention has the following beneficial and significant technical effects: (1) The indoor aircraft engine complex attitude and high overload test intake and exhaust system proposed in the present invention effectively solves the problems of huge inertial force, high-temperature and high-speed gas emission and complex attitude simulation caused by the engine high overload test through the foundation counterweight, test plant structure and efficient exhaust and intake system design. It provides a safe, stable and controllable indoor test space for aircraft engine complex attitude and high overload test, and can meet the test verification intake and exhaust requirements of various types of engines with arbitrary gyro speed, arbitrary flight attitude (pitch, yaw and roll), arbitrary overload value and their coupling state. It can fundamentally solve the problem that there is no plant for engine gyro, attitude and overload test equipment at present, and fill the technical gap to a certain extent.

[0010] (2) The indoor aircraft engine complex attitude and high overload test intake and exhaust system proposed by the present invention realizes the orderly organization of the airflow in the test plant by rationally arranging the intake and exhaust system. The intake system adopts a circular intake trench and a circumferentially distributed intake duct structure to ensure uniform and stable intake; the exhaust system adopts a circular exhaust duct, a diverter cone and a silencer exhaust tower to ensure the efficient collection and orderly discharge of high-temperature exhaust gas, avoid the formation of backflow vortices and dead zones, and ensure the exhaust stability of the engine under different attitudes and high overload conditions. In addition, the present invention significantly improves the safety performance of the test plant through the coordinated design of foundation counterweights, containment load-bearing walls, and pneumatic load-bearing walls.

[0011] (3) The indoor aircraft engine complex attitude and high overload test intake and exhaust system proposed by the present invention can effectively prevent the leakage of sensitive technical data by placing the test in an indoor controllable environment, and can meet the protection requirements of aircraft engines for technical secrets; at the same time, the indoor test environment also reduces the interference of external environmental factors (such as weather, wind direction, etc.) on the test results, and improves the test efficiency and data accuracy. In addition, the present invention improves the stability and seismic resistance of the system by optimizing the design of the foundation counterweight and the test plant structure, which can effectively prevent the parts from flying off or being damaged by impact in abnormal conditions during the engine test, and improve the safety of the test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 An isometric view of an indoor aircraft engine complex attitude and high overload test intake and exhaust system provided by an embodiment of the present invention; Figure 2 A top view of an indoor aircraft engine complex posture and high overload test intake and exhaust system provided by an embodiment of the present invention; Figure 3 This is an AA cross-sectional view of the air intake and exhaust system in the plant system provided in an embodiment of the present invention, focusing on the relevant structure of the test plant; Figure 4 This is an AA cross-sectional view of an air intake and exhaust system in a plant system provided in an embodiment of the present invention, focusing on the relevant structure of the exhaust system; Figure 5 This is a BB cross-sectional view of an air intake and exhaust system in a plant system provided in an embodiment of the present invention, focusing on the relevant structure of the air intake system; Figure 6 This is a front view of the air intake and exhaust system in the plant system provided by the embodiment of the present invention, focusing on the relevant structure of the fuel system; Figure 7 A CC cross-sectional view of an intake and exhaust system in a plant system provided in an embodiment of the present invention; Figure 8 A DD cross-sectional view of an air intake and exhaust system in a plant system provided in an embodiment of the present invention; Fig. 9 This is a schematic diagram of the equipment foundation in the factory system provided in an embodiment of the present invention, wherein (A) is a top view and (B) is an EE cross-sectional view.

[0013] Description of reference numerals: 1. Foundation counterweight; 2. Porch; 3. Test plant; 4. Supporting plant; 5. Exhaust system; 6. Air intake system; 7. Fuel system; 8. Trench system; 9. Foundation pit ladder; 10. Plant ladder; 11. Traveling crane; 12. Equipment foundation; 2-1. Silence door; 2-2. Switch installation position for distribution box, lighting, crane, etc.; 2-3. Tool cabinet; 2-4. Removable containment wall; 2-5. Pneumatic structure door; 3-1, inclusive load-bearing wall; 3-2, pneumatic load-bearing wall; 3-3, exhaust load-bearing roof; 4-1, measurement and control room; 4-2, electrical room; 4-3, box-type transformer room; 5-1, annular exhaust duct; 5-1-1, outer wall of annular exhaust duct; 5-1-2, inner wall of annular exhaust duct; 5-2, diverter cone; 5-3, exhaust hole; 5-4, rain cover; 5-5, silencer exhaust tower; 6-1, rain cover of air intake tower; 6-2, air intake fan; 6-3, air intake duct; 6-4, air intake duct protection net; 6-5, air intake trench; 6-6, air intake trench grille plate; 6-7, foundation pit; 6-8, foundation pit air intake hole; 6-9, foundation pit grille plate; 6-10, air intake trench grille plate support; 6-11, foundation pit grille plate support; 7-1, fuel oil skid; 7-2, fuel oil skid plant shed; 8-1, outdoor box transformer cable trench; 8-2, electrical room cable trench; 8-3, process equipment high-voltage trench; 8-4, test equipment low-voltage trench; 8-5, air intake fan high-voltage trench; 8-6, fuel trench; 8-7, ring distribution trench; 12-1. Pre-embedded anchor bolts; 12-2. Pre-embedded fixing steel plates. DETAILED DESCRIPTION

[0014] The present invention aims to provide an indoor aircraft engine complex attitude and high overload test intake and exhaust system, which can meet the explosion-proof, impact-resistant, rotating intake / exhaust, noise reduction, power supply / oil, anti-overturning, installation, maintenance and other requirements of various types of aircraft engine gyroscopes, attitude and overload tests, and has the characteristics of good safety, strong confidentiality, and full functionality, providing a reliable test verification environment for aircraft engine complex attitude and overload tests. The technical solutions in the embodiments will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative labor are within the scope of protection of the present invention.

[0015] like Figure 1 to Figure 9 As shown, in an illustrative embodiment of the indoor aircraft engine complex attitude and high overload test intake and exhaust system of the present invention, the plant system mainly includes a foundation counterweight 1, a porch 2, a test plant 3, a supporting plant 4, an exhaust system 5, an intake system 6, a fuel system 7, a trench system 8, a foundation pit ladder 9, a plant ladder 10, a crane 11, an equipment foundation 12 and other twelve parts. The main functions of each part are briefly introduced as follows: The foundation counterweight 1 is mainly used to provide support, fixation and counterweight conditions for the aircraft engine test equipment to prevent the equipment from overturning and to isolate vibration; the porch 2 is arranged on the foundation counterweight and is connected to one side of the test workshop 3, mainly including pneumatic structure doors, detachable containment walls, silencer doors, tool cabinets, distribution boxes-lighting-travel cranes and other switch installation positions; the test workshop 3 is arranged on the foundation counterweight and mainly includes containment bearing walls, pneumatic bearing walls, exhaust bearing roofs, etc.; the supporting workshop 4 is arranged on the foundation counterweight The exhaust system 5 is arranged on the roof of the test building 3, which is used to discharge the exhaust gas of the aircraft engine out of the building, and mainly includes an annular exhaust duct composed of an inner wall of the annular exhaust duct and an outer wall of the annular exhaust duct, a diverter cone, an exhaust hole, a rain cover for a silencer exhaust tower, a silencer exhaust tower, etc.; the air intake system 6 is arranged on the foundation counterweight to replenish air for the internal space of the test building 3, including an air intake tower rain cover, an air intake fan, an air intake duct, an air intake duct protection net, an air intake trench, an air intake trench grille plate, The foundation pit air inlet, foundation pit grille, air intake trench grille support, foundation pit grille support, etc.; the fuel system 7, which is arranged on the foundation counterweight, including the fuel skid and the fuel skid shed; the trench system 8, which is arranged on the foundation counterweight and is used for laying the strong and weak cables and oil pipes in the box transformer room, electrical room, measurement and control room, factory building, air intake trench and foundation pit, including the outdoor box transformer cable trench, the electrical room cable trench, the process equipment strong and weak trench, the test equipment weak trench, the air intake fan strong and strong trench, the fuel Oil trench, ring distribution trench; foundation pit ladder 9, which is arranged on the side wall of the foundation pit and is used for daily inspection of the equipment in the foundation pit; plant ladder 10, which is arranged on the wall of the test plant 3 and is used for daily inspection of the silencer exhaust tower; overhead crane 11, which is arranged on the roof of the test plant 3 and is used for the up and down installation of test pieces and the disassembly and maintenance of equipment; equipment foundation 12, which is arranged on the bottom surface of the foundation pit, comprises pre-embedded anchor bolts and pre-embedded fixing steel plates, which are used to connect the aircraft engine test equipment to the foundation counterweight.

[0016] In the above-mentioned exemplary embodiment, the present invention provides an indoor aircraft engine complex attitude and high overload test intake and exhaust system. The plant system realizes the test verification of various types of engines at any gyro speed, any flight attitude (pitch, yaw and roll), any overload value and its coupling state, as well as the needs of protecting technical secrets, plant intake and exhaust, control, testing, power supply, fuel supply, gas supply, etc. through the mutual coordination of multiple facilities such as foundation counterweight, porch, plant, local supporting plant, exhaust system, intake system, fuel system, trench system, equipment foundation, etc.

[0017] The following will describe in detail the various components in the above-mentioned plant system of the present invention: Foundation counterweight 1. The present invention provides the required test equipment support, fixation and counterweight conditions for the test device by setting the foundation counterweight to prevent the equipment from overturning and is used for vibration isolation. It may include main structures such as a load-bearing base plate and an anti-overturning counterweight block to bear the dynamic load of the engine test platform, offset the huge inertia force generated by the engine during high overload tests, and reduce the impact of external interference on the test accuracy. The size of the counterweight is determined according to the maximum thrust of the test engine and the maximum overload of the test platform.

[0018] like Figure 2 As shown, the porch 2 in the embodiment of the present invention is arranged on the foundation counterweight 1, connected to one side of the test plant 3, and mainly includes a pneumatic structure door 2-5, a detachable containment wall 2-4, a soundproof door 2-1, a tool cabinet 2-3, and a distribution box-lighting-crane and other switch installation positions 2-2. The present invention provides the required installation and maintenance entrance and exit channels for the test device by setting up the porch 2, stores and installs tool cabinets, fire-fighting equipment and indoor electrical switches, and isolates the test noise.

[0019] More specifically, the pneumatic structure door 2-5 in the porch 2, the containment load-bearing wall 3-1, the pneumatic load-bearing wall 3-2, and the exhaust load-bearing roof 3-3 of the test plant 3 together form the cylindrical pneumatic space of the test plant 3. By setting the pneumatic structure door 2-5, the requirements of the aerodynamic flow field in the test plant for complex attitude and high overload tests of aircraft engines can be met. The detachable containment wall 2-4 is set opposite the pneumatic structure door 2-5. By setting the detachable containment wall 2-4, the requirements of disassembly and maintenance of test equipment in and out of the plant can be met, and it is also used to resist the impact load of parts, components and complete machines flying off during the test. The sound-absorbing door 2-1 is arranged on the wall of the porch 2 on any side except the pneumatic structure door 2-5 and the removable containment wall 2-4. By setting the sound-absorbing door 2-1, the demand for reducing noise pollution during the test can be met. The sound-absorbing door 2-1 can be prepared with multi-layer sound-absorbing materials and sound-absorbing devices, which can reduce the impact of high-frequency noise and infrasound on the surrounding environment and ensure that the test environment meets the noise standard requirements. The tool cabinet 2-3 is arranged near the sound-absorbing door 2-1 to store the tools and accessories required for the test, which can meet the test platform's demand for tool storage. The switch installation position 2-2 for the distribution box, lighting, crane, etc. is arranged near the sound-absorbing door 2-1 to meet the needs of power supply, power extraction and electrical control in the test project.

[0020] like Figure 3As shown, the test plant 3 in the embodiment of the present invention is arranged on the foundation counterweight 1, and its bottom surface is provided with a foundation pit 6-7 and an equipment foundation arranged in the foundation pit 6-7 and used to install and fix the engine test platform, and its overall structural size is determined according to the size and layout requirements of the test platform to ensure the safety of the test and meet the test operation space requirements. Specifically, the test plant 3 is a cylindrical structure as a whole, and includes, from bottom to top, a containing load-bearing wall 3-1, a pneumatic load-bearing wall 3-2, and an exhaust load-bearing roof 3-3. By setting up the test plant 3, the present invention provides the required protection of technical secrets for the test device and the intake and exhaust requirements for the engine test, and provides physical isolation protection for the engine parts-components-whole machine to fly off.

[0021] More specifically, the test plant 3 of the present invention does not allow the installation of electrical switches and sockets such as heating, water pipes, toilets, and lighting. The plant is cylindrical, wherein: the containment load-bearing wall 3-1 is located at the lower side of the test plant 3, fixedly set on the foundation counterweight 1 and arranged around the test area, and its height is consistent with the height of the center line of the aircraft engine on the test platform from the ground, and is used to resist the impact load of parts, components, and the whole machine that may fly off during the test. The pneumatic load-bearing wall 3-2 is located above the containment load-bearing wall 3-1, and its inner surface is formed as the outer wall 5-1-1 of the annular exhaust duct, which together with the inner wall 5-1-2 of the annular exhaust duct constitutes the annular exhaust duct 5-1 (such as Figure 4 As shown in FIG. 1 ), the test platform can meet the requirements of the annular exhaust duct. The pneumatic load-bearing wall 3-2 can be equipped with a crane 11, an exhaust load-bearing roof 3-3, and a workshop ladder 10 (as shown in FIG. 1 ). Figure 5 As shown in the figure, the test platform can meet the requirements of installation, disassembly, exhaust and workshop maintenance. The exhaust load-bearing roof 3-3 is located above the pneumatic load-bearing wall 3-2, and a certain number of exhaust holes are opened along the circumference of the upper edge thereof, and together with the pneumatic structure door 2-5, the containing load-bearing wall 3-1 and the pneumatic load-bearing wall 3-2, a cylindrical pneumatic space of the test workshop 3 is formed, which can meet the requirements of the pneumatic flow field in the test workshop.

[0022] In addition, if Fig. 9 As shown, the equipment foundation 12 is arranged on the bottom surface of the foundation pit 6-7, including embedded anchor bolts 12-1 and embedded fixing steel plates 12-2, which are used to connect the test equipment with the foundation counterweight 1. Its layout position and specifications match the installation requirements of the engine test platform, and the strength and rigidity of the fixing steel plate 12-2 meet the dynamic load requirements during the test, ensuring the installation accuracy and operation stability of the test platform.

[0023] like Figure 3As shown, the supporting plant 4 in the embodiment of the present invention is arranged on the foundation counterweight 1, including a transformer room 4-3, an electrical room 4-2, and a measurement and control room 4-1. The supporting plant 4 is provided to provide the required oil-electricity-gas requirements and control-test requirements for the test device. Specifically, the supporting plant 4 is arranged near the test plant 3, not far from the plant, so that it is convenient to have a secondary protection function when an abnormal condition occurs in the test, and at the same time, it rushes to the scene in time for processing after the abnormal condition occurs, including a transformer room, an electrical room, and a measurement and control room. Among them, the transformer room 4-3 is used to install the power supply and transformer equipment of the test equipment, and perform voltage conversion, power transmission, power protection and power distribution for the test facilities; the electrical room 4-2 is used to store the power distribution instruments and meters of the test equipment, and provide power for the test equipment, test equipment, control equipment, detection equipment, video monitoring equipment, etc. The measurement and control room 4-1 is used to store the test host computer, control host computer, video monitoring host computer, detection host computer, etc., to control, test, monitor and command the test platform.

[0024] like Figure 4 As shown, the exhaust system 5 in the embodiment of the present invention is arranged on the roof of the test building 3, and is used for exhausting the aircraft engine exhaust gas from the test building 3 during the test process, including an annular exhaust duct 5-1 arranged on the roof of the test building and extending downward to the top of the test platform, and a plurality of exhaust holes 5-3 arranged on the roof of the test building and distributed circumferentially and connected to the annular exhaust duct. The annular exhaust duct 5-1 is composed of an annular exhaust duct inner wall 5-1-2 and an annular exhaust duct outer wall 5-1-1, wherein the annular exhaust duct outer wall 5-1-1 is surrounded by the wall of the test building 3, and the annular exhaust duct inner wall 5-1-2 is a tubular structure and its inner diameter is adapted to the size of the foundation pit.

[0025] More specifically, the exhaust system 5 mainly includes an annular exhaust duct 5-1 composed of an annular exhaust duct inner wall 5-1-2 and an annular exhaust duct outer wall 5-1-1, a diverter cone 5-2, an exhaust hole 5-3, a rain cover 5-4, a silencer exhaust tower 5-5 and other components. The present invention provides the required exhaust, noise reduction and rain protection requirements for the test device by setting up the exhaust system 5. The annular exhaust duct outer wall 5-1-1 is the inner surface of the pneumatic load-bearing wall 3-2, and the annular exhaust duct inner wall 5-1-2 is a lightweight metal sheet structure, which is used to discharge the high-temperature exhaust gas of the engine. The diverter cone 5-2 is a lightweight metal sheet structure, which is located on the pneumatic load-bearing wall 3-2 between the exhaust holes 5-3 in the circumferential direction, and is used to guide the airflow into the exhaust hole 5-3, and a certain airflow channel space is left between the diverter cone 5-2 and the exhaust load-bearing roof 3-3, which is used to overflow the periodic instantaneous gas flow peak to other exhaust holes. The exhaust hole 5-3 is a vent hole opened along the circumference of the exhaust load-bearing roof 3-3. The number can be 1 or several. When it is designed to be 1, it is located at the center of the exhaust load-bearing roof. When the number is set to several, it is evenly distributed around the edge of the exhaust load-bearing roof 3-3 for gas to flow out of the factory roof. The silencer exhaust tower 5-5 is located on the exhaust load-bearing roof 3-3, facing the exhaust hole 5-3, and the number is the same as the exhaust hole 5-3. The rain cover 5-4 is located on the silencer exhaust tower 5-3 to prevent rainwater from flowing into the silencer exhaust tower.

[0026] like Figure 5 As shown, the air intake system 6 in the embodiment of the present invention is arranged on the foundation counterweight 1, and is used to replenish air in the test building 3. It includes at least one air intake trench 6-5 and multiple air intake ducts 6-3. The air intake trench 6-5 is an open trench which is opened on the periphery of the foundation pit 6-7 in the test building 3 and is annular as a whole. A plurality of foundation pit air intake holes 6-8 connecting the air intake trench 6-5 and the foundation pit 6-7 are circumferentially opened on the wall surface between the air intake trench 6-5 and the foundation pit 6-7. A plurality of air intake ducts 6-3 are circumferentially distributed on the outer wall of the air intake trench 6-5, and each air intake duct 6-3 extends outward to the outside of the test building 3 to guide the airflow into the inside of the test building.

[0027] More specifically, the air intake system 6 mainly includes an air intake tower rain cover 6-1, an air intake fan 6-2, an air intake duct 6-3, an air intake duct protection net 6-4, an air intake trench 6-5, an air intake trench grille plate 6-6, a foundation pit air intake hole 6-8, a foundation pit grille plate 6-9, an air intake trench grille plate support 6-10, a foundation pit grille plate support 6-11 and other components and supporting structures. The present invention provides the required air intake, noise reduction and rain protection requirements for the test device by setting up the air intake system 6. Among them: The air intake tower rain shield 6-1 is located above the air intake fan 6-2, and the number is the same as the number of air intake fans 6-2, which is used to prevent rainwater from flowing into the air intake fan 6-2. The air intake fans 6-2 are located on the foundation counterweight 1, and several of them are evenly distributed outside the test plant in the circumferential direction to provide power for the external airflow to flow into the test plant. Generally, the air intake fan can be designed vertically or horizontally. The vertical design can effectively save floor space and reduce the entry of foreign objects such as fallen leaves, sand and gravel or mice.

[0028] The air inlet 6-3 passes through the foundation counterweight 1, and the number is the same as the number of the air inlet fans 6-2. It is radially distributed along the center of the air inlet trench 6-5, and its air inlet is located below the air inlet fan 6-2. The air inlet 6-3 first extends downward for a distance, then turns horizontally and extends all the way to the air inlet trench 6-5. The air outlet is located on the outer wall of the air inlet trench, providing a channel for the external air flow to flow into the factory building. The air inlet protection net 6-4 is located at the air outlet of the air inlet 6-3, and the number is the same as the number of the air inlet fans 6-2. It is made of a plate with dense small holes, which can reduce and prevent the entry of foreign objects such as fallen leaves, sand and gravel or mice.

[0029] The air intake trench 6-5 is located inside the factory building. It is a circular semi-open trench dug on the foundation counterweight, which is used to diffuse the gas that passes through the air intake fan, the air intake duct, and the air intake duct protection net in a circular direction. The air intake trench grille plate support 6-10 is located above the air intake trench. It can be made of T-shaped steel, square steel, etc., with the plane facing upward. Several of them are radially distributed along the center of the air intake trench and laid above the air intake trench 6-5 to support the air intake trench grille plate 6-6. The air intake trench grille plate 6-5 is located above the air intake trench grille plate support 6-10. It is composed of several segmented circular thin plates spliced ​​into a circular ring. A large number of small holes are distributed on the thin plates in a certain regular pattern, which are used to further evenly distribute the airflow diffused in the circumferential direction through the air intake trench 6-5 into the test plant 3.

[0030] The foundation pit air inlet holes 6-8 are cylindrical pipes dug on the foundation counterweight. The number is consistent with the number of air intake fans and are radially distributed along the center of the plant. Each foundation pit air inlet hole 6-8 is located between two adjacent air intake ducts 6-3, with one end outlet located on the inner wall of the air intake trench and the other end located on the side wall of the foundation pit 6-7. A portion of the airflow can be introduced into the foundation pit 6-7, which is used for cooling the driving equipment on the one hand, and flows into the test plant 3 through the top of the foundation pit 6-7 on the other hand, for gas replenishment in the central part of the plant. The foundation pit grid plate support 6-11 is located above the foundation pit 6-7 and can be made of T-shaped steel, square steel, etc., with the plane facing upward. Several of them are radially distributed and laid above the foundation pit with the centroid of the foundation pit 6-7 as the center, and are used to support the foundation pit grid plate 6-6. The foundation pit grille plate 6-6 is located on the foundation pit grille plate support 6-11, and is composed of several segmented circular ring thin plates spliced ​​into a circular ring. A large number of small holes are distributed in a certain pattern on the thin plate, which are used to further evenly distribute the airflow passing through the foundation pit 6-7 into the test plant 3.

[0031] like Figure 6 As shown, the fuel system 7 in the embodiment of the present invention is arranged on the foundation counterweight 1 and is set outside the test plant 3, including a fuel skid 71 and a fuel skid shed 72. The present invention provides the required fuel supply for the test device by setting up a fuel system, and facilitates emergency handling in the event of a fire.

[0032] like Figure 7 As shown, the trench system 8 in the embodiment of the present invention is arranged on the foundation counterweight 1, and is used for laying high-voltage cables, low-voltage cables and oil pipes in the transformer room 4-3, the electrical room 4-3, the measurement and control room 4-1, the test plant 3, the air intake trench 6-5 and the foundation pit 6-7, including the outdoor transformer cable trench 8-1, the electrical room cable trench 8-2, the process equipment high-voltage trench 8-3, the test equipment low-voltage trench 8-4, the air intake fan high-voltage trench 8-5, the fuel trench 8-6, and the ring distribution trench 8-7. The present invention provides the required high-voltage cables, low-voltage cables and oil pipe laying space for the test device by setting up the trench system, and the direction and depth of all trenches are determined according to actual wiring requirements.

[0033] As a preference, Figure 7As shown, the plant system of the present invention also includes a traveling crane 11 arranged on the top of the test plant, a foundation pit ladder 9 arranged on the side wall of the foundation pit, and a plant ladder 10 arranged on the outer wall of the test plant, wherein: the foundation pit ladder 9 is arranged on the side wall of the foundation pit of the air intake system 6. The present invention provides the test device with the required daily inspection needs of going up and down the foundation pit by arranging the foundation pit ladder; the plant ladder 10 is arranged on the wall of the plant 3 and is used for the daily inspection of the silencer exhaust tower 4. The present invention provides the test device with the required daily inspection needs of going up and down the plant by arranging the plant ladder; the traveling crane 11 is arranged on the roof of the foundation plant 3. The present invention provides the required lifting for the installation of the test pieces on the upper and lower platforms and the disassembly and maintenance of the equipment by arranging the traveling crane.

[0034] The following is combined with Figures 1 to 9 The working process of one embodiment of the present invention is described as follows: When the test device and the tested engine are installed on the foundation pit 6-7, the exhaust duct is facing the circular exhaust duct 5-1, the equipment outdoor box transformer is installed in the box transformer room 4-3, the incoming power cabinet, frequency conversion electrical cabinet, PLC control cabinet and fan system cabinet are installed in the electrical room 4-3, the equipment test and control system is installed in the measurement and control room 4-1, the air intake fan is installed in the air intake system 6, and the strong and weak current cables and fuel pipelines are installed through the outdoor box transformer cable trench 8-1, the electrical room cable trench 8-2, the process equipment strong current trench 8-3, the test equipment weak current trench 8-4, the air intake fan strong current trench 8-5, the fuel trench 8-6, and the circular power distribution trench 8-7, and the tool cabinet, fire fighting equipment and indoor electrical switches are installed in the porch 2. Through the electrical control module, use the host computer to send instructions to the equipment to complete the test engine test.

[0035] The above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, ordinary technicians in the field should understand that the specific implementation methods of the present invention can still be modified or some technical features can be replaced by equivalents without departing from the spirit of the technical solution of the present invention, which should be included in the scope of the technical solution for protection of the present invention.

Claims

1. An indoor aircraft engine complex attitude and high overload test intake and exhaust system, comprising at least a foundation counterweight, a test plant, an exhaust system and an intake system, characterized in that: The foundation counterweight is arranged on the ground, including a load-bearing bottom plate and an anti-overturning counterweight block, to provide fixing, supporting, counterweighting and vibration isolation conditions for the test equipment; The test plant is arranged on a foundation counterweight, and its bottom surface is provided with a foundation pit and an equipment foundation arranged in the foundation pit and used for installing and fixing the engine test platform; The exhaust system is arranged on the roof of the test plant, including an annular exhaust duct arranged on the roof of the test plant and extending downward to the top of the test platform, and a plurality of exhaust holes arranged on the roof of the test plant and distributed circumferentially and connected to the annular exhaust duct, the annular exhaust duct is composed of an annular exhaust duct inner wall and an annular exhaust duct outer wall, wherein the annular exhaust duct outer wall is surrounded by the wall of the test plant, and the annular exhaust duct inner wall is a tubular structure and its inner diameter is adapted to the size of the foundation pit; The air intake system is arranged on the foundation counterweight, and includes at least one air intake trench and multiple air intake ducts. The air intake trench is an open groove which is opened on the periphery of the foundation pit in the test plant and is generally annular. A plurality of foundation pit air intake holes connecting the air intake trench and the foundation pit are circumferentially opened on the wall surface between the air intake trench and the foundation pit. The multiple air intake ducts are circumferentially distributed on the outer wall of the air intake trench, and each air intake duct extends outward to the outside of the test plant.

2. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1 is characterized by: The test plant has an overall cylindrical structure, and includes, from bottom to top, a containment load-bearing wall, a pneumatic load-bearing wall, and an exhaust load-bearing roof, wherein: the containment load-bearing wall is fixedly arranged on the foundation counterweight and is arranged around the test area, and its height is not lower than the height of the center line of the engine on the test platform from the ground; the pneumatic load-bearing wall is fixedly arranged above the containment load-bearing wall, and its inner wall surface is formed as the outer wall of the annular exhaust duct, and together with the inner wall of the annular exhaust duct constitutes an annular exhaust duct; the exhaust load-bearing roof is arranged on the top of the pneumatic load-bearing wall, and a plurality of exhaust holes connected to the annular exhaust duct are opened circumferentially along its upper edge.

3. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1 is characterized by: The equipment foundation is arranged at the bottom of the foundation pit, including pre-embedded anchor bolts and pre-embedded fixing steel plates, which are used to connect the test equipment with the foundation counterweight. Its layout position and specifications match the installation requirements of the engine test platform, and the strength and rigidity of the fixing steel plate meet the dynamic load requirements during the test, ensuring the installation accuracy and operation stability of the test platform.

4. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1 is characterized by: The exhaust system also includes a diverter cone, a silencer exhaust tower, and a rain cover, wherein: a plurality of diverter cones are provided, which are circumferentially distributed near the outlet position of the annular exhaust duct, each diverter cone is circumferentially located between two adjacent exhaust holes and fixedly arranged on the pneumatic load-bearing wall, and a gap is left between each diverter cone and the exhaust load-bearing roof; the silencer exhaust towers are arranged on the outside of the exhaust load-bearing roof, one-to-one corresponding to the exhaust holes; and the rain cover is arranged on the top of each silencer exhaust tower.

5. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1 is characterized by: In the air intake system, the air inlet of each air intake duct is located outside the test plant, and each air intake duct first extends downward for a distance and then turns horizontally to extend to the outer wall of the air intake trench; and the air intake system also includes an air intake fan, an air intake tower rain cover, an air intake duct protection net, an air intake trench grille plate, and a foundation pit grille plate, wherein: the air intake fans are arranged one by one at the air inlet position of each air intake duct; the air intake tower rain cover is arranged one by one on the top of each air intake fan; the air intake duct protection net is arranged one by one at the air outlet of each air intake duct; the air intake trench grille plate covers the top of the air intake trench, and the foundation pit grille plate covers the outer top surface of the foundation pit, and both are composed of several segmented circular ring-shaped thin plates spliced ​​into a circular ring, and a large number of small holes are regularly distributed on the thin plates.

6. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1 is characterized by: The plant system also includes a porch, which is arranged on the foundation counterweight and connected to one side of the test plant, including a pneumatic structure door, a detachable containment wall, and a sound-absorbing door, wherein: the pneumatic structure door and the containment load-bearing wall, the pneumatic load-bearing wall, and the exhaust load-bearing roof together constitute a cylindrical pneumatic space of the test plant, the detachable containment wall is arranged opposite to the pneumatic structure door, and the sound-absorbing door is arranged on any side wall of the porch except the wall where the pneumatic structure door and the detachable containment wall are located, and multiple layers of sound-absorbing materials and / or sound-absorbing devices are arranged on it.

7. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1 is characterized by: The plant system is also provided with a supporting plant, which is set on the foundation counterweight and arranged adjacent to the test plant, including a box transformer room, an electrical room, and a measurement and control room, wherein: the box transformer room is used to install the power supply and transformer equipment of the test equipment, the electrical room is used to store the power distribution instruments of the test equipment, and the measurement and control room is used to store the test host computer, control host computer, video monitoring host computer and / or detection host computer of the test equipment.

8. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1 is characterized by: The plant system is also provided with a trench system arranged on the foundation counterweight, including at least an outdoor box transformer cable trench, an electrical room cable trench, a process equipment high-voltage trench, a test equipment low-voltage trench, an intake fan high-voltage trench, a fuel trench, and a ring distribution trench, which are used to achieve the reasonable layout of various cables and pipelines, and the direction and depth of all trenches are determined according to actual wiring requirements.

9. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 8, characterized in that: The plant system is also provided with a fuel system arranged on the foundation counterweight. The fuel system is arranged outside the test plant and at least includes a fuel skid and a fuel skid shed, and is connected to the test plant through a fuel trench arranged in the foundation counterweight.

10. The indoor aircraft engine complex attitude and high overload test intake and exhaust system according to claim 1, characterized in that: The plant system also includes a crane installed on the top of the test plant, a foundation pit ladder installed on the side wall of the foundation pit, and a plant ladder installed on the outer wall of the test plant, wherein the crane is used for the upper and lower installation of test pieces and the disassembly and maintenance of equipment, the foundation pit ladder is used for daily inspection of equipment in the pit, and the plant ladder is used for the inspection and maintenance of rooftop equipment.

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