Step-by-step verification method for bird / ice foreign object separation characteristics of particle separator

Abstract

The present invention discloses a method for progressively verifying the bird / ice foreign object separation characteristics of a particle separator, including: a flat plate test verification: after simplifying the inner wall structure of the front assembly of the particle separator, a flat plate test assembly is constructed, followed by a test bench and bird / ice impact tests to evaluate the surface rebound and action characteristics of bird / ice in a typical structure in an airflow; a sector test verification: obtaining a sector-shaped test piece, then constructing a test bench and conducting bird / ice impact and separation tests to evaluate the particle separator structure's bird / ice separation characteristics under similar operating conditions; and a full-ring test verification: obtaining a full-ring test piece, then constructing a test bench and conducting bird / ice impact and separation tests to evaluate the full-ring separation efficiency and structural response. The method of the present invention progressively evaluates the bird / ice foreign object separation performance through a three-level verification system of "flat plate-sector-full ring," gradually revealing the particle separator's bird / ice separation capabilities under different operating conditions, understanding its separation characteristics, and providing reliable data support for the design of engine intake protection systems.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine engines, and in particular to a step-by-step verification method for bird / ice foreign object separation characteristics of a particle separator. Background Art

[0002] Full-speed engines are characterized by high flight speed, large intake flow and frontal area. At the same time, the performance is highly sensitive due to the increase in the single-stage load of the compressor. After the engine swallows birds / ice, the damage to the particle separator and compressor is greater, the performance impact is more severe, and the risk to the engine itself is higher.

[0003] The inertial particle separator is used on the turboshaft engine and can effectively separate foreign objects such as sand, dust, birds, and ice. In a certain turboshaft engine usage scenario, due to the greatly increased speed of foreign objects, the structural strength, separation characteristics and separation efficiency of the original particle separator when facing high-speed bird / ice impacts are completely different from the existing medium and low-speed helicopter usage conditions.

[0004] Compared with low-speed engines, full-speed engines face more severe risks of bird / ice impact and ingestion. Due to the increase in intake speed and engine performance indicators, the shape and structure of the curved flow channel of the intake component have been improved, and the flow speed and flow state are highly complex, which has a significant impact on the motion state and posture of birds / ice foreign objects. The separation characteristics are unclear. The simulation verification and whole-machine verification technology of the separation characteristics of the engine intake protection component in the bird / ice swallowing state under high-speed conditions are difficult. At present, relevant research in the industry is basically blank and urgently needs a breakthrough. Summary of the Invention

[0005] The present invention provides a step-by-step verification method for the bird / ice foreign object separation characteristics of a particle separator to solve the technical problems that the existing simulation verification and whole-machine verification of the separation characteristics of the engine intake protection assembly in the bird / ice swallowing state under high-speed conditions are difficult, the relevant research in the industry is basically blank, and a breakthrough is urgently needed.

[0006] The technical solution adopted in the present invention is as follows:

[0007] A step-by-step verification method for the separation characteristics of bird / ice foreign objects in a particle separator comprises the following steps: a flat plate test verification: analyzing the front combined inner wall structure of the particle separator inner wall plate assembly, simplifying and constructing a flat plate test assembly of the front combined inner wall, and then building an impact contact-fluid-solid coupling test bench with a suction function according to the state of the engine intake duct flow channel, and finally carrying out a bird-ice impact test under the inclined state of the flat plate test piece in the intake flow channel to evaluate the rebound and action characteristics of the typical structure surface of bird / ice in the airflow under the action of impact contact-fluid-solid coupling; a sector test verification: obtaining a sector-shaped test piece with the structural and geometric parameter characteristics of the particle separator and a fan shape, and then building a A particle separator fan-shaped flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench is built, and finally a bird / ice impact and separation test of the fan-shaped test piece under the action of airflow is carried out to evaluate the bird / ice separation characteristics of the particle separator structure under approximate working conditions; full-ring test verification: a real part or a scaled-down part of the particle separator is obtained to form a full-ring test piece, and then a particle separator full-ring flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench is built, and finally a bird / ice impact and separation test of the full-ring test piece under the action of airflow is carried out to evaluate the full-ring separation efficiency and structural response of the scaled-down part under approximate working conditions or the real part under real working conditions.

[0008] Furthermore, the flat plate test assembly includes a first flat plate test piece and a second flat plate test piece; the first flat plate test piece and the second flat plate test piece both include a composite plate and a metal plate stacked up and down, and two edge rubber strips and a plurality of middle rubber strips connected between the composite plate and the metal plate; the two edge rubber strips are respectively close to both sides of the width direction of the composite plate to separate the middle parts of the composite plate and the metal plate; the plurality of middle rubber strips are sequentially arranged at intervals in the middle position of the composite plate to partially connect the middle parts of the composite plate and the metal plate; the first flat plate test piece and the second flat plate test piece are also each provided with a plurality of mounting holes spaced sequentially and passing through the plate surface on both sides close to the width direction, and the mounting holes sequentially pass through the composite plate, the edge rubber strips and the metal plate.

[0009] Furthermore, the first flat plate test piece and the second flat plate test piece differ only in the number and / or arrangement of the middle rubber strips, and the rest of the structural arrangements are exactly the same.

[0010] Furthermore, the impact contact-fluid-solid coupling test bench includes a first support assembly supported vertically, and an intake section, a test section and a suction device for generating suction force, which are supported on the first support assembly and arranged in sequence front and back and connected to form an engine intake air duct, as well as an air cannon for launching projectiles and a high-speed photographic recorder for high-speed photography; the first flat test piece or the second flat test piece is fixed on the bottom plate of the test section, and the bottom plate of the test section gradually extends upward to align the first flat test piece or the second flat test piece fixed thereon with the air inlet of the intake section, and part of the wall surface of the test section is a transparent plate made of transparent material; the air cannons are arranged at intervals in front of the intake section, and the high-speed photographic recorder is located on the outside of the test section.

[0011] Furthermore, the sector-shaped test piece is formed by cutting a sector-shaped area from a real particle separator, or is specially designed and prepared, and the prepared sector-shaped test piece has the structural and geometric parameter characteristics of a particle separator; the sector-shaped test piece includes an inner wall plate assembly and an outer wall plate assembly that are spaced apart inside and outside and are fan-shaped, and the gap between the outer wall plate assembly and the inner wall plate assembly forms a sector-shaped main flow channel with a fan-shaped cross section and a curved extension, and the outer wall plate assembly has a sector-shaped separation flow channel with a fan-shaped cross section and connected to the sector-shaped main flow channel; the full-ring test piece includes an inner wall plate ring and an outer wall plate ring that are spaced apart inside and outside and are annular, and the gap between the outer wall plate ring and the inner wall plate ring forms a full-ring main flow channel with a ring shape and a curved extension, and the outer wall plate ring has a full-ring separation flow channel with a ring shape and connected to the full-ring main flow channel.

[0012] Furthermore, the particle separator fan-shaped flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench includes a vertically supported second support assembly, a front support and a rear support connected to the front and rear ends of the fan-shaped test piece, a plurality of closing plates, two groups of collecting and suction devices for collecting separated materials and generating suction force respectively, an air cannon for launching projectiles, and a high-speed photographic recorder for high-speed photography; the plurality of closing plates are respectively connected between the outer wall plate assembly and the inner wall plate assembly to close the circumference of the fan-shaped main channel and the fan-shaped separation flow channel, and some of the closing plates are transparent plates made of transparent materials; the air inlet on the front support is connected to the air inlet end of the fan-shaped main channel, and the air outlet on the rear support is connected to the air outlet end of the fan-shaped main channel on one side and connected to a group of collecting and suction devices on the other side, and the other group of collecting and suction devices is connected to the air outlet end of the fan-shaped separation flow channel; the air cannons are arranged at intervals in front of the front support, and the high-speed photographic recorder is located on the outside of the fan-shaped test piece.

[0013] Furthermore, the particle separator full-ring flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench includes a vertically supported fixed support, an adapter tube inner tube and an adapter tube outer tube which are arranged in an inner and outer manner and whose first ends are respectively connected to the fixed support, two groups of collecting and suction devices for collecting separated materials and generating suction force respectively, an air cannon for launching projectiles, and a high-speed photographic recorder for high-speed photography; the second ends of the adapter tube inner tube and the adapter tube outer tube extend axially into the inner wall plate ring member and are respectively connected to two groups of adapter flanges in the inner wall plate ring member; the two groups of collecting and suction devices are respectively connected to the air outlet ends of the full-ring main flow channel and the full-ring separation flow channel; the air cannons are arranged at intervals in front of the fixed support, and the high-speed photographic recorder is located on the outside of the full-ring test piece.

[0014] Furthermore, the suction device includes a transition section connected to the air outlet end of the inlet air duct, and a suction fan connected to the transition section; the collection and suction device includes a transition section connected to the fan-shaped main channel or the fan-shaped separation channel or the full-ring main channel or the full-ring separation channel, a suction pipe connected to the transition section, a collection device connected to the suction pipe, and a suction fan connected to the collection device; the test verification processes of the flat plate test verification, the sector test verification and the full-ring test verification all include a flow rate calibration step for calibrating the test flow rate, a bullet velocity calibration step for calibrating the test target bullet velocity, and a trajectory testing step for obtaining the separation trajectory.

[0015] Furthermore, the flow velocity calibration step specifically includes: S101: arranging the pressure difference anemometer probe in the inlet flow channel, the fan-shaped main flow channel and the fan-shaped separation flow channel, the full-ring main flow channel and the full-ring separation flow channel; S102: turning on the suction fan and slowly adjusting the power of the suction fan until the wind speed value required by the test is reached and recorded; S103: recording the power of the suction fan corresponding to the test wind speed that reaches the wind speed value required by the test; After the flow velocity calibration step is completed, the spring velocity calibration step is started, specifically including: S201: making Artificial birdshot and ice hockey projectiles of the same mass as those used in actual working conditions; S202: Setting up and debugging a high-speed camera recorder and a speed measurement system connected to the high-speed camera recorder; S203: Determining the required inflation pressure based on the air cannon projectile velocity curve and the actual projectile mass; S204: Launching the projectile using the calculated inflation pressure to test the projectile ejection velocity; S205: Adjusting the inflation pressure based on the target projectile velocity and launching the projectile again to test the projectile velocity; S206: Repeating steps S201-S205 until the inflation pressure corresponding to the test target projectile velocity is calibrated.

[0016] Furthermore, after the bullet speed calibration step is completed, the trajectory test step is started, which specifically includes: S301: setting up the test bench, debugging the speed measurement and shooting system, and cleaning the test tools next to the test bench; S302: weighing the prepared cartridge case, taking out the projectile and placing it in the cartridge case and weighing it again, and recording the two weighing values on the record sheet; S303: turning on the suction fan to the calibrated power; S304: after ensuring that the speed of the high-speed camera recorder is reset to 0 and the signal analysis software and the high-speed camera image are correct, inflation can be started. After the loading is completed, the high-speed camera recorder is operated to record the impact process; S305: turning off the suction motor after the impact is completed; S306: performing preliminary data processing, extracting the impact velocity and movement process of the projectile, recording the projectile velocity and the launch pressure of the air cannon on the test record sheet, and assigning test numbers according to the projectile type, projectile velocity, and flow rate; S307: removing the cartridge case and projectile fragments, cleaning them, and then reassembling them for the next set of tests.

[0017] The present invention has the following beneficial effects:

[0018] The present invention provides a step-by-step verification method for the bird / ice separation characteristics of a particle separator. The method uses a bird-ice impact test on a typical front composite inner wall of a particle separator inner wall panel assembly in an airflow channel, with a flat plate in an inclined state, to determine the surface rebound and action characteristics of a typical bird / ice structure in an airflow under impact contact and fluid-structure coupling. Furthermore, bird / ice impact and separation tests are conducted on a sector-shaped test piece with the structural and geometric parameters of a particle separator under airflow to determine the bird / ice separation characteristics of the sector-shaped test piece under approximate operating conditions. Furthermore, bird / ice impact and separation tests are conducted on a full-ring test piece formed from a real or scaled-down particle separator under airflow to determine the full-ring separation efficiency and structural response of the scaled-down piece under approximate operating conditions or the real piece under actual operating conditions. Consequently, the method uses a three-level verification system (flat plate-sector-full ring) to progressively evaluate bird / ice separation performance, gradually revealing the particle separator's bird / ice separation capabilities under different operating conditions and understanding its separation characteristics, providing reliable data support for the design of engine air intake protection systems.

[0019] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0021] Figure 14 is a flow chart of a step-by-step verification method for bird / ice foreign object separation characteristics of a particle separator according to a preferred embodiment of the present invention;

[0022] Figure 2 It is a schematic diagram of the top view of the metal plate in the flat test assembly;

[0023] Figure 3a 1 is a schematic diagram of the top view of the first flat plate test piece;

[0024] Figure 3b yes Figure 3a AA-direction cross-sectional structural diagram;

[0025] Figure 3c yes Figure 3b A schematic diagram of the partially enlarged structure at point B in the middle;

[0026] Figure 3d yes Figure 3b Schematic diagram of the local enlarged structure at C in the middle;

[0027] Figure 4a is a schematic diagram of the top view of the second flat plate test piece;

[0028] Figure 4b yes Figure 4a AA-direction cross-sectional structural diagram;

[0029] Figure 4c yes Figure 4b A schematic diagram of the partially enlarged structure at point B in the middle;

[0030] Figure 4d yes Figure 4b Schematic diagram of the local enlarged structure at C in the middle;

[0031] Figure 5a This is the main view of the local structure of the impact contact-fluid-solid coupling test bench;

[0032] Figure 5b yes Figure 5a AA-direction cross-sectional structural diagram;

[0033] Figure 5c This is a schematic diagram of the main structure of the impact contact-fluid-solid coupling test bench;

[0034] Figure 6a This is the main view of the local structure of the particle separator fan-shaped flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench;

[0035] Figure 6b yes Figure 6a AA-direction cross-sectional structural diagram;

[0036] Figure 6cThis is a schematic diagram of the main structure of the particle separator fan-shaped flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench;

[0037] Figure 7a This is the main view of the partial structure of the particle separator full-circle flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench;

[0038] Figure 7b yes Figure 7a AA-direction cross-sectional structural diagram;

[0039] Figure 7c This is a schematic diagram of the main structure of the particle separator full-circle flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench.

[0040] Legend:

[0041] 101. Composite plate; 102. Metal plate; 103. Edge rubber strip; 104. Middle rubber strip; 105. Mounting hole; 11. First flat test piece; 12. Second flat test piece;

[0042] 2. Sector-shaped test piece; 201. Sector-shaped main channel; 202. Sector-shaped separation channel; 21. Inner wall panel assembly; 22. Outer wall panel assembly;

[0043] 3. Full-ring test piece; 301. Full-ring main channel; 302. Full-ring separation channel; 31. Inner wall plate ring; 32. Outer wall plate ring;

[0044] 41. First support assembly; 42. Air intake section; 43. Test section; 44. Air cannon; 45. High-speed camera recorder; 46. Second support assembly; 47. Front support; 48. Rear support; 49. Closing plate; 51. Fixed support; 52. Inner tube of adapter tube; 53. Outer tube of adapter tube; 54. Adapter section; 55. Suction duct; 56. Collecting device; 57. Suction fan; 58. Front mounting edge; 59. Rear mounting edge. DETAILED DESCRIPTION

[0045] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0046] Reference Figure 1 A preferred embodiment of the present invention provides a step-by-step verification method for bird / ice foreign object separation characteristics of a particle separator, comprising the following steps:

[0047] Flat plate test verification: The front combined inner wall structure of the particle separator inner wall plate assembly 21 was analyzed and simplified to construct a flat plate test assembly of the front combined inner wall. Then, an impact contact-fluid-solid coupling test bench with suction function was built according to the flow state of the engine intake duct. Finally, a bird-ice impact test was carried out in the intake flow duct under the inclined state of the flat plate test piece to evaluate the rebound and action characteristics of the typical structural surface of birds / ice in the airflow under the action of impact contact-fluid-solid coupling.

[0048] Sector test verification: A sector-shaped test piece 2 with the structural and geometric parameter characteristics of a particle separator and in a fan shape is obtained, and then a test bench for the high-speed bird / ice swallowing and aerodynamic separation characteristics of the particle separator sector flow channel is built. Finally, a bird / ice impact and separation test of the sector-shaped test piece 2 under the action of airflow is carried out to evaluate the bird / ice separation characteristics of the particle separator structure of the sector-shaped test piece 2 under approximate working conditions.

[0049] Full-ring test verification: A real or scaled-down particle separator is obtained to form a full-ring test piece 3. A full-ring flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench for the particle separator is then constructed. Finally, bird / ice impact and separation tests are conducted on the full-ring test piece 3 under the action of airflow to evaluate the full-ring separation efficiency and structural response of the scaled-down piece under approximate working conditions or the real piece under real working conditions.

[0050] The present invention provides a step-by-step verification method for the bird / ice separation characteristics of a particle separator. The method uses a bird-ice impact test on a typical front composite inner wall of a particle separator's inner wall panel assembly in an airflow channel, with a flat plate in an inclined state, to determine the surface rebound and action characteristics of a typical bird / ice structure in an airflow under impact contact and fluid-structure coupling. Furthermore, bird / ice impact and separation tests are conducted on a sector-shaped test piece 2, which has the structural and geometric parameters of a particle separator and is fan-shaped, under airflow. The bird / ice separation characteristics of the sector-shaped test piece 2 under approximate operating conditions are determined. Furthermore, bird / ice impact and separation tests are conducted on a full-ring test piece 3, formed from a real or scaled-down particle separator, under airflow. The full-ring separation efficiency and structural response of the scaled-down piece under approximate operating conditions or the real piece under actual operating conditions are determined. Consequently, the method uses a three-level verification system (flat plate-sector-full ring) to progressively evaluate bird / ice separation performance, gradually revealing the particle separator's bird / ice separation capabilities under different operating conditions and understanding its separation characteristics, providing reliable data support for the design of engine air intake protection systems.

[0051] Optionally, the step of "plate test verification" specifically includes:

[0052] Based on the front combined inner wall structure of the particle separator inner wall plate assembly 21, a simplified design was carried out to prepare a flat test assembly with similar dimensions and typical composition. The design principle is that the thickness of the metal plate and the composite plate are consistent with the original standard parts, the size is consistent with the diameter of the particle separator, and there is an intermediate rubber strip structure and the same installation edge scheme;

[0053] According to the flow state of a turboshaft engine inlet, an impact contact-fluid-structure coupling test bench with suction function was designed;

[0054] Carry out bird-ice impact tests and evaluations on the flat-plate test piece in the intake duct in an inclined state.

[0055] In this option, if Figure 2 、 Figure 3a 、 Figure 3b 、 Figure 3c 、 Figure 3d 、 Figure 4a 、 Figure 4b 、 Figure 4c and Figure 4d As shown, the flat plate test assembly includes a first flat plate test piece 11 and a second flat plate test piece 12. Each of the first and second flat plate test pieces 11 and 12 includes a composite plate 101 and a metal plate 102 stacked one above the other, and two edge rubber strips 103 and a plurality of intermediate rubber strips 104 connecting the composite plate and the metal plate 102. The two edge rubber strips 103 are located adjacent to either side of the composite plate 101 in the width direction, separating the intermediate portions of the composite plate 101 and the metal plate 102. The plurality of intermediate rubber strips 104 are sequentially spaced apart in the middle of the composite plate 101, partially connecting the intermediate portions of the composite plate 101 and the metal plate 102. The first and second flat plate test pieces 11 and 12 are each provided with a plurality of mounting holes 105 spaced apart and extending through the plate surfaces on either side of the plate 11 and 12 in the width direction. The mounting holes 105 sequentially extend through the composite plate 101, the edge rubber strips 103, and the metal plate 102.

[0056] Preferably, if Figure 3a and Figure 4a As shown, the first flat test piece 11 and the second flat test piece 12 only differ in the number and / or arrangement of the middle rubber strips 104, and the rest of the structural settings are exactly the same. While reducing the difficulty of processing and improving processing efficiency, the macroscopic dimensions are kept unchanged and the number and position of the middle rubber strips 104 are designed to ensure that a typical failure mode is obtained, thereby improving the accuracy and reliability of the test.

[0057] In this option, if Figure 5a 、 Figure 5b and Figure 5cAs shown, the impact contact-fluid-structure interaction test bench includes a vertically supported first support assembly 41, an intake section 42 supported on the first support assembly 41 and arranged in a front-to-rear manner and connected to form the engine intake airflow duct, a test section 43, a suction device for generating suction force, an air cannon 44 for launching projectiles, and a high-speed video recorder 45 for high-speed photography. The first flat test piece 11 or the second flat test piece 12 is fixed to the bottom plate of the test section 43. The bottom plate of the test section 43 gradually extends upward to align the first flat test piece 11 or the second flat test piece 12 fixed thereto with the air inlet of the intake section 42. Part of the wall surface of the test section 43 is a transparent plate made of transparent material. The air cannons 44 are arranged at intervals in front of the intake section 42, and the high-speed video recorder 45 is located outside the test section 43. In this optional solution, the suction device includes a transition section 54 connected to the outlet end of the intake airflow duct and a suction fan 57 connected to the transition section 54.

[0058] In this optional solution, the test evaluation process in the step "Flat Plate Test Verification" includes: in the bird / hail projection test, the high-pressure gas in the air cannon 44 pushes the cartridge case containing the bird / hail to accelerate forward, the cartridge case separates from the projectile at the muzzle separator, and the projectile moves forward at a calibrated speed; the bird / ice projectile moves in a straight line in the horizontal direction and enters the air intake duct, and the high-speed camera recorder 45 mounted on the outside records the bird / ice movement process; the suction fan 57 provides a low-pressure suction air source for the high-speed airflow suction channel; the evaluation criterion is that the high-speed camera recorder 45 records the complete bird / ice movement trajectory to determine that the test is valid. The specific process includes: flow rate calibration step, projectile speed calibration step and trajectory testing step. The specific operation of each step is as follows:

[0059] The flow rate calibration steps specifically include:

[0060] S101: placing a pressure differential anemometer probe in the intake air duct;

[0061] S102: Turn on the suction fan 57 and slowly adjust the power of the suction fan 57 until the wind speed reaches the required test speed and records it;

[0062] S103: Recording the power of the suction fan 57 corresponding to the test wind speed that reaches the test required wind speed value;

[0063] After the flow rate calibration step is completed, the bullet velocity calibration step begins, which includes:

[0064] S201: Produce artificial birdshot and ice ball pellets of the same mass as in actual working conditions;

[0065] S202: Setting up and debugging the high-speed camera recorder 45 and the speed measurement and shooting system connected to the high-speed camera recorder 45;

[0066] S203: Calculating the required inflation pressure based on the air cannon 44 bullet velocity curve and the actual projectile mass;

[0067] S204: Using the calculated inflation pressure, launch the projectile to test the projectile ejection velocity;

[0068] S205: Adjust the inflation pressure according to the target bullet speed, and fire the projectile again to test the bullet speed;

[0069] S206: Repeat steps S201-S205 until the inflation pressure of the test target bullet velocity is calibrated.

[0070] After the velocity calibration step is completed, the trajectory test step begins, which includes:

[0071] S301: Set up the test bench, debug the speed measurement and camera system, and clean the test tools next to the test bench;

[0072] S302: Weigh the prepared sabot, remove the projectile, place it in the sabot, and weigh it again, and record the two weighing values on a record sheet;

[0073] S303: Turn on the suction fan 57 to the rated power;

[0074] S304: After ensuring that the speed of the high-speed camera recorder 45 is reset to 0 and the signal analysis software and high-speed camera images are correct, inflation can begin. After loading is completed, the high-speed camera recorder 45 is operated to record the impact process. Specifically, the high-speed camera recorder 45 is synchronously triggered by the trigger key of the air cannon control system in the form of a high level to record the impact process.

[0075] S305: Turn off the suction motor after the impact is completed;

[0076] S306: Perform preliminary data processing to extract the impact velocity and motion process of the projectile, record the projectile velocity and the launch pressure of the air cannon 44 on the test record sheet, and assign a test number based on the projectile type, projectile velocity, and flow rate;

[0077] S307: Remove the sabot and projectile fragments, clean them, and then reassemble them for the next set of tests.

[0078] Alternatively, as Figure 6a As shown, the sector-shaped test piece 2 is formed by cutting a sector-shaped area of a real particle separator, or is specially designed and prepared, and the prepared sector-shaped test piece 2 has the structural and geometric parameter characteristics of the particle separator. Figure 6bAs shown, the sector-shaped test piece 2 includes an inner wall panel assembly 21 and an outer wall panel assembly 22 that are spaced apart and are sector-shaped. The gap between the outer wall panel assembly 22 and the inner wall panel assembly 21 forms a sector-shaped main flow channel 201 with a sector-shaped cross section and extending in a curve. The outer wall panel assembly 22 has a sector-shaped separation flow channel 202 in its cross section that is connected to the sector-shaped main flow channel 201. Figure 7a and Figure 7b As shown, the full-ring test piece 3 includes an inner wall plate ring 31 and an outer wall plate ring 32 that are spaced apart and are annular, and the gap between the outer wall plate ring 32 and the inner wall plate ring 31 forms an annular and curved full-ring main flow channel 301, and the outer wall plate ring 32 has a full-ring separation flow channel 302 that is annular and connected to the full-ring main flow channel 301.

[0079] Alternatively, as Figure 6a 、 Figure 6b and Figure 6c As shown, the particle separator sector flow channel bird / ice high-speed swallowing and aerodynamic separation performance test bench includes a vertically supported second support assembly 46, a front support 47 and a rear support 48 connected to the front and rear ends of the sector test specimen 2, multiple sealing plates 49, two sets of collection and suction devices for collecting separated materials and generating suction, respectively, an air cannon 44 for launching projectiles, and a high-speed video recorder 45 for high-speed photography. The multiple sealing plates 49 are connected between the outer wall panel assembly 22 and the inner wall panel assembly 21 to circumferentially seal the sector main flow channel 201 and the sector separation flow channel 202. Some of the sealing plates 49 are transparent plates made of transparent material. The air inlet on the front support 47 is connected to the air inlet end of the sector main flow channel 201. The air outlet on the rear support 48 is connected to the air outlet end of the sector main flow channel 201 on one side and to one set of collection and suction devices on the other side. The other set of collection and suction devices is connected to the air outlet end of the sector separation flow channel 202. Air cannons 44 are spaced in front of front supports 47, and high-speed camera recorders 45 are located outside the sector-shaped test piece 2. In this alternative, the collection and suction device includes a transition section 54 connected to the sector-shaped main channel 201 or the sector-shaped separation channel 202, a suction pipe 55 connected to the transition section 54, a collection device 56 connected to the suction pipe 55, and a suction fan 57 connected to the collection device 56.

[0080] Furthermore, the step “sector test verification” specifically includes the following steps:

[0081] A sector test piece 2 is formed by using a real separator sector cut piece or a specially designed and prepared sector test piece;

[0082] Particle separator fan-shaped flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench;

[0083] Carry out bird / ice impact and separation tests and evaluations on a fan-shaped test piece 2 with particle separator structure and geometric parameter characteristics under the action of airflow.

[0084] Specifically, the test and evaluation include: in the bird / hail projection test, the high-pressure gas in the air cannon 44 pushes the sabot containing the bird / hail to accelerate forward, the sabot separates from the projectile at the muzzle separator, and the projectile moves forward at a calibrated speed; the bird / ice projectile moving in a straight line in the horizontal direction enters the fan-shaped main channel 201, and the high-speed camera recorder 45 mounted on the outside records the bird / ice movement process; a bird / ice collection device 56 is installed behind the high-speed airflow suction channel. After each set of tests, the bird / ice projectile can be recovered and processed. Each collection device 56 is connected to a suction fan 57 to provide a low-pressure suction air source for the high-speed airflow suction channel. The specific process includes: flow rate calibration step, bullet speed calibration step and trajectory testing step. The specific operation of each step is as follows:

[0085] The flow rate calibration steps specifically include:

[0086] S101: placing a differential pressure anemometer probe in the fan-shaped main flow channel 201 and the fan-shaped separation flow channel 202;

[0087] S102: Turn on the suction fan 57 and slowly adjust the power of the suction fan 57 until the wind speed reaches the required test speed and records it;

[0088] S103: Record the power of the suction fan 57 corresponding to the test wind speed that reaches the test required wind speed value.

[0089] After the flow rate calibration step is completed, the bullet velocity calibration step begins, which includes:

[0090] S201: Produce artificial birdshot and ice ball pellets of the same mass as in actual working conditions;

[0091] S202: Setting up and debugging the high-speed camera recorder 45 and the speed measurement and shooting system connected to the high-speed camera recorder 45;

[0092] S203: Calculating the required inflation pressure based on the air cannon 44 bullet velocity curve and the actual projectile mass;

[0093] S204: Using the calculated inflation pressure, launch the projectile to test the projectile ejection velocity;

[0094] S205: Adjust the inflation pressure according to the target bullet speed, and fire the projectile again to test the bullet speed;

[0095] S206: Repeat steps S201-S205 until the inflation pressure of the test target bullet velocity is calibrated.

[0096] After the velocity calibration step is completed, the trajectory test step begins, which includes:

[0097] S301: Set up the test bench, debug the speed measurement and camera system, and clean the test tools next to the test bench;

[0098] S302: Weigh the prepared sabot, remove the projectile, place it in the sabot, and weigh it again, and record the two weighing values on a record sheet;

[0099] S303: Turn on the suction fan 57 to the rated power;

[0100] S304: After ensuring that the speed of the high-speed camera recorder 45 is reset to 0 and the signal analysis software and high-speed camera images are correct, inflation can begin. After loading is completed, the high-speed camera recorder 45 is operated to record the impact process. Specifically, the high-speed camera recorder 45 is synchronously triggered by the trigger key of the air cannon control system in the form of a high level to record the impact process.

[0101] S305: Turn off the suction motor after the impact is completed;

[0102] S306: Perform preliminary data processing to extract the impact velocity and motion process of the projectile, record the projectile velocity and the launch pressure of the air cannon 44 on the test record sheet, and assign a test number based on the projectile type, projectile velocity, and flow rate;

[0103] S307: Remove the sabot and projectile fragments, clean them, and then reassemble them for the next set of tests.

[0104] Alternatively, as Figure 7a 、 Figure 7b and Figure 7c As shown, the particle separator full-circle flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench includes a vertically supported fixed support 51, an inner adapter tube 52 and an outer adapter tube 53, which are arranged in an inner and outer manner and connected to the fixed support 51 at their first ends, two sets of collection and suction devices for collecting separated materials and generating suction force, respectively, an air cannon 44 for launching projectiles, and a high-speed video recorder 45 for high-speed photography. The second ends of the inner adapter tube 52 and the outer adapter tube 53 extend axially into the inner wall plate ring member 31 and are respectively connected to the front mounting edge 58 and the rear mounting edge 59 at both ends of the inner wall plate ring member 31. The two sets of collection and suction devices are respectively connected to the air outlet ends of the full-circle main flow channel 301 and the full-circle separation flow channel 302. The air cannons 44 are arranged in front of the fixed support 51 at intervals, and the high-speed video recorder 45 is located on the outside of the full-circle test piece 3. In this optional solution, the collection and suction device includes a transition section 54 connected to the full-ring main channel 301 or the full-ring separation channel 302, a suction pipe 55 connected to the transition section 54, a collection device 56 connected to the suction pipe 55, and a suction fan 57 connected to the collection device 56.

[0105] Furthermore, the step “full-ring test verification” specifically includes the following steps:

[0106] Design a scaled-down part that reflects the actual structure of the particle separator or a real part of the particle separator;

[0107] Construct a particle separator full-circle flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench;

[0108] Conduct bird / ice impact and separation tests and evaluate actual or scaled-down particle separators under airflow.

[0109] Specifically, the test and evaluation include: During the bird / hail projection test, the high-pressure gas in the air cannon 44 pushes the sabot containing the bird / hail forward to accelerate. The sabot separates from the projectile at the muzzle separator, and the projectile moves forward at a calibrated speed; the bird / hail moving in a straight line in the horizontal direction enters the full-circular main channel 301, and the high-speed camera recorder 45 installed on the side records the bird / hail movement process; a bird / hail collection device 56 is installed behind the high-speed airflow suction channel. After each set of tests, the bird / hail projectile can be recovered and processed. Each collection device 56 is connected to a suction fan 57 to provide a low-pressure suction air source for the high-speed airflow suction channel. The specific process includes: flow rate calibration step, bullet speed calibration step and trajectory testing step. The specific operation of each step is as follows:

[0110] S101: placing a pressure differential anemometer probe in the full-ring main flow channel 301 and the full-ring separation flow channel 302;

[0111] S102: Turn on the suction fan 57 and slowly adjust the power of the suction fan 57 until the wind speed reaches the required test speed and records it;

[0112] S103: Record the power of the suction fan 57 corresponding to the test wind speed that reaches the test required wind speed value.

[0113] After the flow rate calibration step is completed, the bullet velocity calibration step begins, which includes:

[0114] S201: Produce artificial birdshot and ice ball pellets of the same mass as in actual working conditions;

[0115] S202: Setting up and debugging the high-speed camera recorder 45 and the speed measurement and shooting system connected to the high-speed camera recorder 45;

[0116] S203: Calculating the required inflation pressure based on the air cannon 44 bullet velocity curve and the actual projectile mass;

[0117] S204: Using the calculated inflation pressure, launch the projectile to test the projectile ejection velocity;

[0118] S205: Adjust the inflation pressure according to the target bullet speed, and fire the projectile again to test the bullet speed;

[0119] S206: Repeat steps S201-S205 until the inflation pressure of the test target bullet velocity is calibrated.

[0120] After the velocity calibration step is completed, the trajectory test step begins, which includes:

[0121] S301: Set up the test bench, debug the speed measurement and camera system, and clean the test tools next to the test bench;

[0122] S302: Weigh the prepared sabot, remove the projectile, place it in the sabot, and weigh it again, and record the two weighing values on a record sheet;

[0123] S303: Turn on the suction fan 57 to the rated power;

[0124] S304: After ensuring that the speed of the high-speed camera recorder 45 is reset to 0 and the signal analysis software and high-speed camera images are correct, inflation can begin. After loading is completed, the high-speed camera recorder 45 is operated to record the impact process. Specifically, the high-speed camera recorder 45 is synchronously triggered by the trigger key of the air cannon control system in the form of a high level to record the impact process.

[0125] S305: Turn off the suction motor after the impact is completed;

[0126] S306: Perform preliminary data processing to extract the impact velocity and motion process of the projectile, record the projectile velocity and the launch pressure of the air cannon 44 on the test record sheet, and assign a test number based on the projectile type, projectile velocity, and flow rate;

[0127] S307: Remove the sabot and projectile fragments, clean them, and then reassemble them for the next set of tests.

[0128] Furthermore, in step S307, the specific operations are as follows: first, turn off the fill light, start disassembling the sabot separator, remove the inner block of the sabot separator, take out the sabot, ensure that there are no broken sabots and foam in the sabot separator, wipe the inner wall of the sabot separator, and reinstall the sabot separator; then open the projectile collection device 56, take out the bird / ice projectile debris, and reseal the collection device 56; finally, turn on the fill light again, tighten the stop of the sabot separator, and start the next set of tests.

[0129] In the aforementioned "sector test verification" and "full-ring test" steps, the particle separator's bird / ice separation efficiency is calculated as the ratio of the rejected weight (i.e., the weight of the bird discharged into the sector separation channel 202 or the full-ring separation channel 302) to the total weight. The rejected bird weight is collected by the collection device 56 and then weighed. During ice ball bombing, if the ice ball completely breaks apart, it is considered completely rejected. The collection device 56, with its filter structure inside the cylindrical housing, is located between the suction pipe 55 and the suction fan 57, ensuring air source stability while collecting bird debris.

[0130] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A step-by-step verification method for the bird / ice foreign object separation characteristics of a particle separator, characterized in that: The following steps are involved: Flat plate test verification: The front combined inner wall structure of the particle separator inner wall plate assembly (21) is analyzed and simplified to construct a flat plate test assembly of the front combined inner wall, and then an impact contact-fluid-solid coupling test bench with a suction function is built according to the engine intake duct flow state. Finally, a bird-ice impact test is carried out in the intake duct under the inclined state of the flat plate test piece to evaluate the rebound and action characteristics of the bird / ice surface in the airflow under the impact contact-fluid-solid coupling effect; Sector test verification: obtain a sector-shaped test piece (2) with the structural and geometric parameter characteristics of the particle separator and in a sector shape, then build a particle separator sector flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench, and finally carry out bird / ice impact and separation tests on the sector-shaped test piece (2) under the action of airflow to evaluate the separation characteristics of the particle separator structure of the sector-shaped test piece (2) on birds / ice under similar working conditions; Full-ring test verification: obtain the real part or scaled part of the particle separator to form a full-ring test piece (3), then build a full-ring flow channel bird / ice high-speed swallowing and aerodynamic separation characteristics test bench for the particle separator, and finally carry out bird / ice impact and separation tests on the full-ring test piece (3) under the action of airflow to evaluate the full-ring separation efficiency and structural response of the scaled part under approximate working conditions or the real part under real working conditions.

2. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 1, characterized in that: The flat plate test assembly includes a first flat plate test piece (11) and a second flat plate test piece (12); the first flat plate test piece (11) and the second flat plate test piece (12) both include a composite plate (101) and a metal plate (102) stacked up and down, and two edge strips (103) and a plurality of middle strips (104) connected between the composite plate and the metal plate (102); the two edge strips (103) are respectively close to both sides of the composite plate (101) in the width direction, so that the composite plate (101) and the metal plate (102) are spaced apart. 2) the middle portions of the two are spaced apart; a plurality of middle rubber strips (104) are sequentially spaced apart in the middle position of the composite plate (101) so that the middle portions of the composite plate (101) and the metal plate (102) are partially connected; a plurality of mounting holes (105) are also provided on both sides of the first flat test piece (11) and the second flat test piece (12) close to the width direction, and are sequentially spaced apart and penetrate the plate surface, and the mounting holes (105) sequentially penetrate the composite plate (101), the edge rubber strips (103) and the metal plate (102).

3. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 2, characterized in that: The first flat test piece (11) and the second flat test piece (12) differ only in the number and / or arrangement of the middle rubber strips (104), and the rest of the structural arrangements are identical.

4. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 2, characterized in that: The impact contact-fluid-solid coupling test bench comprises a first supporting assembly (41) supported vertically, an intake section (42) supported on the first supporting assembly (41) and arranged in sequence front and back and connected to form an engine intake airway, a test section (43) and a suction device for generating suction force, as well as an air cannon (44) for launching projectiles and a high-speed photography recorder (45) for high-speed photography; a first flat test piece (11) or a second flat test piece (12) is fixed on the bottom plate of the test section (43), the bottom plate of the test section (43) gradually extends upward to make the first flat test piece (11) or the second flat test piece (12) fixed thereon align with the air inlet of the intake section (42), and part of the wall surface of the test section (43) is a transparent plate made of transparent material; the air cannon (44) is arranged in front of the intake section (42) at intervals, and the high-speed photography recorder (45) is located outside the test section (43).

5. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 4, characterized in that: The sector-shaped test piece (2) is formed by cutting a sector-shaped area of a real particle separator, or is specially designed and prepared, and the prepared sector-shaped test piece (2) has the structural and geometric parameter characteristics of the particle separator; the sector-shaped test piece (2) includes an inner wall plate component (21) and an outer wall plate component (22) that are spaced apart and are sector-shaped, and the gap between the outer wall plate component (22) and the inner wall plate component (21) forms a sector-shaped main flow channel (201) with a sector-shaped cross section and a curved extension, and the outer wall plate component (2 2) having a sector-shaped separation flow channel (202) with a sector-shaped cross section and connected to the sector-shaped main flow channel (201); the full-ring test piece (3) includes an inner wall plate ring member (31) and an outer wall plate ring member (32) that are spaced apart and annular, and a gap between the outer wall plate ring member (32) and the inner wall plate ring member (31) forms an annular and curved full-ring main flow channel (301), and the outer wall plate ring member (32) has an annular full-ring separation flow channel (302) in annular shape and connected to the full-ring main flow channel (301).

6. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 5, characterized in that: The particle separator fan-shaped flow channel bird / ice high-speed swallowing and aerodynamic separation characteristic test bench comprises a second support assembly (46) vertically supported, a front support (47) and a rear support (48) connected to the front and rear ends of the fan-shaped test piece (2), a plurality of closing plates (49), two sets of collecting and suction devices for collecting separated objects and generating suction force respectively, an air cannon (44) for launching projectiles, and a high-speed photography recorder (45) for high-speed photography; the plurality of closing plates (49) are respectively connected between the outer wall plate assembly (22) and the inner wall plate assembly (21) to adjust the fan-shaped main flow channel (201) to the desired effect. The circumference of the fan-shaped separation flow channel (202) is closed, and the partially closed plate (49) is a transparent plate made of transparent material; the air inlet on the front support (47) is connected to the air inlet end of the fan-shaped main flow channel (201), and the air outlet on the rear support (48) is connected to the air outlet end of the fan-shaped main flow channel (201) on one side, and is connected to a group of collecting and suction devices on the other side, and the other group of collecting and suction devices is connected to the air outlet end of the fan-shaped separation flow channel (202); the air cannons (44) are arranged at intervals in front of the front support (47), and the high-speed photography recorder (45) is located on the outside of the fan-shaped test piece (2).

7. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 6, characterized in that: The particle separator full-circle flow channel bird / ice high-speed swallowing and aerodynamic separation characteristic test bench comprises a vertically supported fixed support (51), an adapter tube inner tube (52) and an adapter tube outer tube (53) which are arranged in an inner and outer manner and whose first ends are respectively connected to the fixed support (51), two groups of collecting and suction devices for collecting separated materials and generating suction force, an air cannon (44) for launching projectiles, and a high-speed photography recorder (45) for high-speed photography; the second ends of the adapter tube inner tube (52) and the adapter tube outer tube (53) are axially extended into the inner wall plate ring member (31) and are respectively connected to two groups of adapter flanges in the inner wall plate ring member (31); the two groups of collecting and suction devices are respectively connected to the air outlet ends of the full-circle main flow channel (301) and the full-circle separation flow channel (302); the air cannon (44) is arranged in front of the fixed support (51) at intervals, and the high-speed photography recorder (45) is located on the outside of the full-circle test piece (3).

8. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 7, characterized in that: The suction device includes a transfer section (54) connected to the air outlet end of the inlet flow channel, and a suction fan (57) connected to the transfer section (54); the collection suction device includes a transfer section (54) connected to the fan-shaped main channel (201) or the fan-shaped separation channel (202) or the full-ring main channel (301) or the full-ring separation channel (302), a suction pipe (55) connected to the transfer section (54), a collection device (56) connected to the suction pipe (55), and a suction fan (57) connected to the collection device (56); the test verification processes of the flat plate test verification, the sector test verification and the full-ring test verification all include a flow rate calibration step for calibrating the test flow rate, a bullet velocity calibration step for calibrating the test target bullet velocity, and a trajectory testing step for obtaining the separation trajectory.

9. The method for stepwise verification of bird / ice foreign object separation characteristics of a particle separator according to claim 8, characterized in that: The flow rate calibration steps specifically include: S101: arranging a pressure differential anemometer probe in the inlet flow channel, the fan-shaped main flow channel (201), the fan-shaped separation flow channel (202), the full-annular main flow channel (301), and the full-annular separation flow channel (302); S102: Turn on the suction fan (57) and slowly adjust the power of the suction fan (57) until the wind speed value required by the test is reached and recorded; S103: Recording the power of the suction fan (57) corresponding to the test wind speed that reaches the test required wind speed value; After the flow rate calibration step is completed, the bullet velocity calibration step begins, which includes: S201: Produce artificial birdshot and ice ball pellets of the same mass as in actual working conditions; S202: Setting up and debugging the high-speed camera recorder (45), and the speed measurement and shooting system connected to the high-speed camera recorder (45); S203: Calculating the required inflation pressure based on the air cannon (44) bullet velocity curve and the actual projectile mass; S204: Using the calculated inflation pressure, launch the projectile to test the projectile ejection velocity; S205: Adjust the inflation pressure according to the target bullet speed, and fire the projectile again to test the bullet speed; S206: Repeat steps S201-S205 until the inflation pressure of the test target bullet velocity is calibrated.

10. The step-by-step verification method for the bird / ice foreign object separation characteristics of a particle separator according to claim 9, characterized in that: After the velocity calibration step is completed, the trajectory test step begins, which includes: S301: Set up the test bench, debug the speed measurement and camera system, and clean the test tools next to the test bench; S302: Weigh the prepared sabot, remove the projectile, place it in the sabot, and weigh it again, and record the two weighing values on a record sheet; S303: Turn on the suction fan (57) to the rated power; S304: After ensuring that the speed of the high-speed camera recorder (45) is reset to 0 and the signal analysis software and the high-speed camera image are correct, inflation can be started. After the loading is completed, the high-speed camera recorder (45) is operated to record the impact process; S305: Turn off the suction motor after the impact is completed; S306: Perform preliminary data processing to extract the impact velocity and motion process of the projectile, record the projectile velocity and the launch pressure of the air cannon (44) on the test record sheet, and assign test numbers according to the projectile type, projectile velocity, and flow rate; S307: Remove the sabot and projectile fragments, clean them, and then reassemble them for the next set of tests.

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