An aircraft bleed air on-line adjustment device

Abstract

The application provides an aircraft bleed air online adjusting device, and belongs to the technical field of aero-engines. The device comprises a measurement control system, an engine, a bleed air main pipe, a bleed air flow measurement and control device, a cabin simulator and a cabin pressure control valve. The bleed air main pipe is provided with a first gas temperature and pressure measurement point. The bleed air flow measurement and control device is provided with a second gas temperature and pressure measurement point. The cabin simulator is provided with a cabin pressure measurement point. The bleed air flow measurement and control device is used for online measurement and control of the bleed air flow of the engine. The first gas temperature and pressure measurement point, the second gas temperature and pressure measurement point and the cabin pressure measurement point are used for measurement of along-the-way gas parameters. The cabin simulator is used for simulation of the volume and pressure of the aircraft cabin. The cabin pressure control valve is used for online adjustment of the pressure of the cabin simulator. Through the processing scheme, the engine bleed air flow test and control are adjusted, the bleed air is consistent with the flight environment, and the adjustment and measurement accuracy are improved.

Description

Technical Field

[0001] This application relates to the field of aero-engine technology, and in particular to an online bleed air adjustment device for aircraft. Background Technology

[0002] Extracting bleed air load from aero-engines can expose weaknesses in the power unit in advance. Generally, engine bleed air is mainly used in cooling systems, pressurization systems, and engine anti-icing systems. Aircraft bleed air is used in engine inlet lip anti-icing systems, pressurizing liquid coolant tanks in aircraft environmental control systems, and pressurizing fuel tanks in aircraft fuel systems. Intelligent online adjustment and control of aircraft bleed air in aero-engines simulates the state of aircraft bleed air and engine bleed air by consuming engine bleed air.

[0003] Currently, the regulating valves and other structural components in the bleed air load extraction devices for aero engines are relatively large, requiring frequent replacement, resulting in high operational complexity and easily affecting measurement accuracy. Summary of the Invention

[0004] In view of this, the present application provides an online bleed air adjustment device for aircraft, which at least partially solves the problems of high operational complexity and easily affected measurement accuracy in the extraction of bleed air load from aero engines in the prior art.

[0005] This application provides an online bleed air adjustment device for aircraft, including a measurement and control system and an engine, a bleed air manifold, a bleed air flow measurement and control device, a cockpit simulator, and a cockpit pressure control valve connected in sequence. The bleed air manifold is provided with a first gas temperature and pressure measurement point, the bleed air flow measurement and control device is provided with a second gas temperature and pressure measurement point, and the cockpit simulator is provided with a cockpit pressure measurement point. The measurement and control system is connected to the cockpit pressure control valve, the first gas temperature and pressure measurement point, the second gas temperature and pressure measurement point, and the cockpit pressure measurement point, respectively.

[0006] The bleed air flow measurement and control device is used to measure and control the engine's bleed air flow online. The first gas temperature and pressure measurement point, the second gas temperature and pressure measurement point, and the cabin pressure measurement point are used to measure the gas parameters along the path. The cabin simulator is used to simulate the volume and pressure of the aircraft cabin. The cabin pressure control valve is used to adjust the pressure of the cabin simulator online. The measurement and control system adjusts the bleed air flow measurement and control device and the cabin pressure control valve by collecting the gas parameters along the path from the first gas temperature and pressure measurement point, the second gas temperature and pressure measurement point, and the cabin pressure measurement point, thereby realizing the measurement and online adjustment of the bleed air flow.

[0007] According to a specific implementation of an embodiment of this application, the bleed air flow measurement and control device includes an outer frame and a measurement and control device cooling pipe, a rectifier, a flow measuring device, and a bleed air flow control valve disposed inside the outer frame. The measurement and control device cooling pipe is disposed on the top of the outer frame and blows air to cool the rectifier, the flow measuring device, and the bleed air flow control valve. The rectifier, the flow measuring device, and the bleed air flow control valve are connected in sequence. The inlet end of the rectifier is connected to the bleed air main pipe through the measurement and control device inlet pipe, and the outlet end of the bleed air flow control valve is connected to the cabin simulator through the measurement and control device outlet pipe. A second gas temperature and pressure measurement point is disposed on the flow measuring device, and the bleed air flow control valve is connected to the measurement and control system.

[0008] According to a specific implementation of an embodiment of this application, the rectifier includes a rectifier inlet expansion section, a rectifier straight section, a rectifier contraction section, and a rectifier outlet straight section connected in sequence. The rectifier inlet expansion section is connected to the inlet pipe of the measurement and control device, and the rectifier outlet straight section is connected to the flow measurement device. A rectifier grid plate is provided between the rectifier inlet expansion section and the rectifier straight section. The inner diameters of the outlet of the rectifier inlet expansion section, the inlet of the rectifier straight section, and the inlet of the rectifier contraction section are the same. The rectifier contraction section adopts a transition contraction curve of arc-straight line-arc. The rectifier grid plate is provided with a plurality of evenly distributed circular holes of equal annular surface.

[0009] According to a specific implementation of this application, the expansion angle of the rectifier intake expansion section is 10°; the area of ​​all the circular holes on the rectifier grid plate is 70% of the area of ​​the inner circle of the rectifier straight section, and the length of the rectifier straight section is equal to its inner diameter.

[0010] According to a specific implementation of an embodiment of this application, the flow measurement device includes a first straight section for flow measurement, a second straight section for flow measurement, a constriction section for flow measurement, a throat section for flow measurement, a first expansion section for flow measurement, and a second expansion section for flow measurement connected in sequence. The first straight section for flow measurement is connected to a rectifier, and the second expansion section for flow measurement is connected to a bleed air flow control valve through a flow measurement outlet flange.

[0011] The second gas temperature and pressure measurement point includes a first measuring ring located at the axial midpoint of the first straight section of the flow measurement and a second measuring ring located at the axial midpoint of the throat section of the flow measurement.

[0012] According to a specific implementation of this application, a first static pressure point and a second static pressure point of the first measuring ring are respectively provided at two junctions between the first measuring ring and the first straight section of the flow measurement. A first measuring ring outlet is provided at the middle position of the ring body of the first measuring ring, and the wall static pressure of the second straight section of the flow measurement is obtained through the first measuring ring outlet. A second measuring ring first static pressure point and a second measuring ring second static pressure point are respectively provided at two junctions between the second measuring ring and the throat section of the flow measurement. A second measuring ring outlet is provided at the middle position of the ring body of the second measuring ring, and the wall static pressure of the throat section of the flow measurement is obtained through the second measuring ring outlet. The bleed gas flow rate is calculated based on the wall static pressure of the second straight section of the flow measurement, the wall static pressure of the throat section of the flow measurement, and the test results of the first gas temperature and pressure measurement point.

[0013] According to a specific implementation of this application, the length of the first straight section of the flow measurement is three times the inner diameter, the inner diameter of the front end of the flow measurement contraction section is the same as the inner diameter of the first straight section of the flow measurement, the inner diameter of the rear end of the flow measurement contraction section is half the inner diameter of the front end of the flow measurement contraction section, and the contraction angle of the flow measurement contraction section is 14°.

[0014] According to a specific implementation of an embodiment of this application, the bleed air flow control valve includes a control valve body, a drive mechanism, and a fixed frame. The drive mechanism is disposed on both sides of the control valve body. The control valve body includes a control valve inlet, a control valve body, and a control valve outlet that communicate with each other. The control valve inlet is connected to a flow measurement device, and the control valve outlet is connected to the outlet pipeline of the measurement and control device. A control valve core is connected inside the control valve body, and a control valve core drive rod is connected to the end of the control valve core. The end of the control valve core drive rod away from the control valve core is connected to the drive mechanism. The drive mechanism is fixed to the outside of the fixed frame. A control valve radiator is sleeved on the outside of the control valve core drive rod. The two ends of the control valve radiator are fixed inside the fixed frame through a first control valve mounting seat and a second control valve mounting seat, respectively. The first control valve mounting seat is fixed to the upper part of the control valve body.

[0015] According to a specific implementation of an embodiment of this application, the drive mechanism includes two sets, which are respectively disposed on both sides of the fixed frame. Each set of drive mechanisms includes a cylinder pusher base, a cylinder pusher motor, a cylinder pusher actuator, a cylinder pusher mounting seat, and a cylinder pusher force transmission rod. The cylinder pusher motor and the cylinder pusher actuator are connected side by side on the cylinder pusher base. One end of the cylinder pusher force transmission rod is fixed to the upper end of the cylinder pusher actuator, and the other end of the cylinder pusher force transmission rod passes through the cylinder pusher mounting seat and is connected to the force transmission beam on the fixed frame. The end of the control valve core drive rod away from the control valve core is fixed at the middle position of the force transmission beam. The fixed frame also includes a bottom adapter seat, a left adapter seat, a right adapter seat, and a top adapter seat. The bottom adapter seat, the left adapter seat, the right adapter seat, the top adapter seat, and the first control valve mounting seat form a ring structure for mounting the drive mechanism. The bottom adapter seat, the left adapter seat, and the right adapter seat are fixed on the first control valve mounting seat, and the top adapter seat is fixed on the second control valve mounting seat.

[0016] According to a specific implementation of an embodiment of this application, the cockpit simulator includes a cockpit shell and a cockpit partition disposed inside the cockpit shell. The cockpit shell has a cockpit inlet and a cockpit outlet on both sides. The cockpit inlet is connected to the outlet of the bleed air measurement and control device, and the cockpit outlet is connected to the inlet of the cockpit pressure control valve. The cockpit partition has multiple cockpit flow guide holes, and the lines connecting the cockpit flow guide holes to the cockpit inlet and the cockpit outlet are located at different positions.

[0017] Beneficial effects:

[0018] The aircraft bleed air online adjustment device in this embodiment can simulate the process of gas drawn from the intermediate stage of the engine compressor, passing through the aircraft environmental control system accessories and the aircraft cockpit, and being discharged to the atmosphere through the exhaust valve, according to the bleed air requirements of the engine test aircraft and the specific conditions of the engine bench. Through the pressure precision adjustment device, the rectifier device, and the back pressure feedback and adjustment device, the device can adjust the engine bleed air flow rate for testing and control, ensuring consistency with the bleed air in the flight environment. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a structural diagram of an aircraft bleed air online adjustment device according to an embodiment of the present invention;

[0021] Figure 2 This is a schematic diagram of an online bleed air adjustment device for an aircraft according to an embodiment of the present invention;

[0022] Figure 3This is a front view of an aircraft bleed air online adjustment device according to an embodiment of the present invention;

[0023] Figure 4 Three-view diagrams of an aircraft bleed air online adjustment device according to an embodiment of the present invention;

[0024] Figure 5 This is a cross-sectional view of an aircraft bleed air online adjustment device according to an embodiment of the present invention;

[0025] Figure 6 This is a structural diagram of the bleed air flow measurement section of an aircraft bleed air online regulating device according to an embodiment of the present invention;

[0026] Figure 7 This is a schematic diagram of the bleed air flow measurement point of an aircraft bleed air online adjustment device according to an embodiment of the present invention;

[0027] Figure 8 This is another schematic diagram of the bleed air flow measurement point of an aircraft bleed air online adjustment device according to an embodiment of the present invention;

[0028] Figure 9 This is a structural diagram of the flow measurement device of an aircraft bleed air online regulating device according to an embodiment of the present invention;

[0029] Figure 10 This is a structural diagram of a cockpit simulator for an aircraft bleed air online adjustment device according to an embodiment of the present invention.

[0030] In the diagram: 1-Engine, 2-Bleed air manifold, 3-Bleed air measurement and control device, 4-First gas temperature and pressure measurement point, 5-Second gas temperature and pressure measurement point, 6-Cockpit pressure measurement point, 7-Cockpit simulator, 8-Cockpit pressure control valve, 9-Measurement and control system, 310-Rectifier, 311-Rectifier intake expansion section, 312-Rectifier grid plate, 313-Rectifier straight section, 314-Rectifier contraction section, 315-Rectifier outlet straight section, 320-Flow measurement device, 321-Flow measurement first straight section, 322-Flow measurement contraction section, 323-Flow measurement throat section, 324-Flow measurement first... Expansion section, 325-Flow measurement second expansion section, 326-Flow measurement second straight section, 327-Flow measurement outlet flange, 328-First measuring ring, 329-Second measuring ring, 330-Break air flow control valve, 340-External frame, 341-Flow measurement mounting base, 350-Inlet pipe of measurement and control device, 351-Inlet straight section, 352-Inlet right-angle section, 360-Cooling pipe of measurement and control device, 361-Control valve cooling pipe, 362-Flow measurement cooling pipe, 363-Rectifier cooling pipe, 364-Motor cooling pipe, 365-Cooling gas inlet, 366-Box cooling pipe, 36 7-Cooling main pipe, 370-Control device outlet pipe, 501-First measuring loop outlet, 502-First measuring loop first static pressure point, 503-First measuring loop second static pressure point, 504-Second measuring loop first static pressure point, 505-Second measuring loop second static pressure point, 506-Second measuring loop outlet, 801-Control valve inlet, 802-Control valve body, 803-Control valve outlet, 805-Control valve first mounting base, 806-Control valve radiator, 807-Control valve second mounting base, 808-Control valve core drive rod, 811-First push cylinder base, 812-First push cylinder motor, 813 - First cylinder actuator, 814- First cylinder mounting base, 815- First cylinder force transmission rod, 821- Second cylinder base, 822- Second cylinder motor, 823- Second cylinder actuator, 824- Second cylinder mounting base, 825- Second cylinder force transmission rod, 831- Bottom adapter, 832- Left adapter, 833- Right adapter, 834- Top adapter, 835- Force transmission beam, 701- Cockpit inlet, 702- Cockpit shell, 703- Cockpit partition, 704- First cockpit guide hole, 705- Second cockpit guide hole, 706- Third cockpit guide hole, 707- Cockpit outlet. Detailed Implementation

[0031] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0032] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0033] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using other structures and / or functionalities besides one or more of the aspects set forth herein.

[0034] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0035] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0036] To meet the bleed air load test requirements in simulated experiments, this invention proposes an online bleed air adjustment device and method for aircraft, mainly including a bleed air flow measurement device, an online adjustment device, and a flow control device. The innovation of this invention is: based on the bleed air requirements of the engine test aircraft and combined with the specific conditions of the engine test bench, it simulates the process of gas drawn from the intermediate stage of the engine compressor, passing through the aircraft environmental control system accessories and the aircraft cockpit, and being discharged to the atmosphere through the exhaust valve. Through a pressure precision adjustment device, a rectification device, and a back pressure feedback and adjustment device, the bleed air flow rate of the engine is adjusted for testing and control, ensuring consistency with the bleed air in the flight environment.

[0037] This application provides an online bleed air adjustment device for aircraft, as described below. Figures 1 to 10 Provide a detailed description.

[0038] Reference Figure 1 The aircraft bleed air online adjustment device in this embodiment includes a measurement and control system 9 and an engine 1, a bleed air main pipe 2, a bleed air flow measurement and control device 3, a cockpit simulator 7, and a cockpit pressure control valve 8 connected in sequence. The bleed air main pipe 2 is provided with a first gas temperature and pressure measurement point 4, the bleed air flow measurement and control device 3 is provided with a second gas temperature and pressure measurement point 5, and the cockpit simulator 7 is provided with a cockpit pressure measurement point 6. The measurement and control system 9 is connected to the cockpit pressure control valve 8, the first gas temperature and pressure measurement point 4, the second gas temperature and pressure measurement point 5, and the cockpit pressure measurement point 6, respectively.

[0039] The bleed air flow measurement and control device 3 is used to measure and control the bleed air flow of engine 1 online. The first gas temperature and pressure measurement point 4, the second gas temperature and pressure measurement point 5, and the cabin pressure measurement point 6 are used to measure the gas parameters along the path. The cabin simulator 7 is used to simulate the volume and pressure of the aircraft cabin. The cabin pressure control valve 8 is used to adjust the pressure of the cabin simulator 7 online. The measurement and control system 9 adjusts the bleed air flow measurement and control device 3 and the cabin pressure control valve 8 by collecting the gas parameters along the path from the first gas temperature and pressure measurement point 4, the second gas temperature and pressure measurement point 5, and the cabin pressure measurement point 6, so as to realize the measurement and online adjustment of the bleed air flow.

[0040] After the bleed air from the engine 1 exits through the bleed air port, it passes through the bleed air manifold 2, the bleed air flow measurement and control device 3, the cockpit simulator 7, and the cockpit pressure control valve 8 before entering the test environment. The measurement and control system 9 analyzes the gas parameters along the path collected at the first gas temperature and pressure measurement point 4, the second gas temperature and pressure measurement point 5, and the cockpit pressure measurement point 6, and adjusts and controls the bleed air flow measurement and control device 3 and the cockpit pressure control valve 8 according to the target parameters, thereby realizing the measurement and online adjustment of the bleed air flow.

[0041] In one specific embodiment, refer to Figures 2 to 6The bleed air flow measurement and control device 3 includes an outer frame 340 and a measurement and control device cooling pipe 360, a rectifier 310, a flow measuring device 320, and a bleed air flow control valve 330 disposed inside the outer frame 340. The flow measuring device 320 is fixed to the outer frame 340 by a flow measuring mounting base 341 disposed at the bottom. The measurement and control device cooling pipe 360 ​​is disposed at the top of the outer frame 340, and the measurement and control device cooling pipe 360 ​​supplies power to the rectifier 310 and the flow measuring device 320. The bleed air flow control valve 330 is cooled by blowing air. The rectifier 310, flow measuring device 320, and bleed air flow control valve 330 are connected in sequence. The inlet end of the rectifier 310 is connected to the bleed air main pipe 2 through the inlet pipe 350 of the measurement and control device. The outlet end of the bleed air flow control valve 330 is connected to the cabin simulator 7 through the outlet pipe 370 of the measurement and control device. The second gas temperature and pressure measuring point 5 is set on the flow measuring device 320. The bleed air flow control valve 330 is connected to the measurement and control system 9. The inlet pipe 350 of the measurement and control device includes an inlet straight section 351 and an inlet right-angle section 352.

[0042] Specifically, the outer frame 340 serves as the load-bearing frame for the bleed air flow measurement and control device 3. The rectifier 310, flow measurement device 320, bleed air flow control valve 330, inlet pipe 350, cooling pipe 360, and outlet pipe 370 of the measurement and control device are all located inside the outer frame 340. The measurement and control system 9 is located on the upper part of the outer frame 340. Aircraft bleed air enters the bleed air flow measurement and control device 3 through the inlet pipe 350. Since bends in the pipe can cause uneven gas flow, affecting the accuracy of temperature, pressure, and flow measurement, a rectifier 310 is arranged after the inlet pipe 350 to rectify the gas flow and ensure that the gas entering the flow measurement device 320 is uniform. The bleed air flow control valve 330 is located downstream of the flow measurement device 320 to achieve online control of the bleed air flow. The outlet pipe 370 of the measurement and control device is connected to the cockpit simulator 7. The cooling pipe 360 ​​of the measurement and control device is used to cool the flow measurement device 320, bleed air flow control valve 330, etc.

[0043] Specifically, the cooling pipe 360 ​​of the measurement and control device includes a control valve cooling pipe 361, a flow measurement cooling pipe 362, a rectifier cooling pipe 363, a motor cooling pipe 364, a cooling air inlet 365, a housing cooling pipe 366, and a cooling main pipe 367. Cooling air enters the cooling main pipe 367 from the cooling air inlet 365, and blows air to cool the structure of the external frame 340 from the control valve cooling pipe 361, the flow measurement cooling pipe 362, the rectifier cooling pipe 363, the motor cooling pipe 364, and the housing cooling pipe 366.

[0044] In one specific embodiment, the rectifier 310 includes a rectifier inlet expansion section 311, a rectifier straight section 313, a rectifier contraction section 314, and a rectifier outlet straight section 315 connected in sequence. The rectifier inlet expansion section 311 is connected to the inlet pipe 350 of the measurement and control device, and the rectifier outlet straight section 315 is connected to the flow measurement device 320. A rectifier grid plate 312 is provided between the rectifier inlet expansion section 311 and the rectifier straight section 313. The inner diameters of the outlet of the rectifier inlet expansion section 311, the inlet of the rectifier straight section 313, and the inlet of the rectifier contraction section 314 are the same. The rectifier contraction section 314 adopts a transition contraction curve of arc-straight line-arc to accelerate the airflow and facilitate the measurement of flow field parameters by the flow measurement device 320. The rectifier grid plate 312 is provided with a plurality of evenly distributed circular holes of equal toroidal surfaces. For example, the rectifier grid plate 312 uses 5 evenly distributed circular holes of equal toroidal surfaces as airflow channels.

[0045] In one specific embodiment, the expansion angle of the rectifier inlet expansion section 311 is 10°, which effectively reduces the gas velocity and facilitates the subsequent rectifier grid plate 312 to divide the airflow and form a uniform pressure flow field. The area of ​​all the circular holes on the rectifier grid plate 312 is 70% of the area of ​​the inner circle of the rectifier straight section 313, and the length of the rectifier straight section 313 is equal to its inner diameter, ensuring that the gas after the rectifier grid plate 312 is fully mixed.

[0046] In one specific embodiment, the flow measurement device 320 includes a first straight section 321 for flow measurement, a second straight section 326 for flow measurement, a contraction section 322 for flow measurement, a throat section 323 for flow measurement, a first expansion section 324 for flow measurement, and a second expansion section 325 for flow measurement, connected in sequence. The first straight section 321 for flow measurement is connected to the rectifier 310. The second expansion section 325 for flow measurement is connected to the bleed air flow control valve 330 through the flow measurement outlet flange 327. The throat section 323 for flow measurement is connected to the contraction section 322 for flow measurement and is the part with the smallest flow area in the entire device, where the flow velocity is the largest. The first expansion section 324 for flow measurement and the second straight section 326 for flow measurement are mainly used to ensure the quality of the flow field and reduce the influence on the flow field of the throat section 323 for flow measurement. The outlet flange 327 for flow measurement is used to connect to the bleed air flow control valve 330.

[0047] Reference Figure 7 and Figure 8 The second gas temperature and pressure measurement point 5 includes a first measuring ring 328 located at the axial middle position of the first straight section 321 of the flow measurement and a second measuring ring 329 located at the axial middle position of the throat section 323 of the flow measurement. The second gas temperature and pressure measurement point 5 collects pressure through the first measuring ring 328 and the second measuring ring 329 respectively.

[0048] In one specific embodiment, the length of the first straight section 321 of the flow measurement is three times its inner diameter. The inner diameter of the front end of the flow measurement constriction section 322 is the same as the inner diameter of the first straight section 321 of the flow measurement. The function of the flow measurement constriction section 322 is to further increase the gas flow rate, which facilitates the improvement of the gas pressure measurement accuracy. The inner diameter of the rear end of the flow measurement constriction section 322 is half of the inner diameter of the front end of the flow measurement constriction section 322, and the constriction angle of the flow measurement constriction section 322 is 14°.

[0049] In one specific embodiment, refer to Figure 7 and Figure 8 The first measuring ring 328 and the first straight section 321 of the flow measurement are respectively provided with a first static pressure point 502 and a second static pressure point 503 at the two junctions. The first measuring ring 328 has a first measuring ring outlet 501 in the middle position of the ring body. The wall static pressure of the second straight section 326 of the flow measurement is obtained through the first measuring ring outlet 501. The second measuring ring 329 and the throat section 323 of the flow measurement are respectively provided with a second measuring ring first static pressure point 504 and a second measuring ring second static pressure point 505 at the two junctions. The second measuring ring 329 has a second measuring ring outlet 506 in the middle position of the ring body. The wall static pressure of the throat section 323 of the flow measurement is obtained through the second measuring ring outlet 506. The bleed gas flow rate is calculated by the wall static pressure of the second straight section 326 of the flow measurement, the wall static pressure of the throat section 323 of the flow measurement, and the test results of the first gas temperature and pressure measurement point 4.

[0050] Specifically, the first measuring ring 328 and the second measuring ring 329 are spaced 180° apart in the circumferential direction, so that the first static pressure point 502, the second static pressure point 503, the first static pressure point 504, and the second static pressure point 505 of the first measuring ring are evenly distributed on the circumference, and the circumferential angle between two adjacent static pressure measuring points differs by 90°. This arrangement can ensure the uniformity and accuracy of the measurement data; the first static pressure point 502 and the second static pressure point 503 of the first measuring ring are connected by the bend in the first measuring ring 328. The static pressure on the wall of the second straight section 326 of the flow measurement is averaged. The static pressure on the wall of the throat section 323 of the flow measurement is averaged through the bend of the second measuring ring 329 at the first static pressure point 504 and the second static pressure point 505 of the second measuring ring. The static pressure on the wall of the second straight section 326 of the flow measurement is obtained through the outlet 501 of the first measuring ring, and the static pressure on the wall of the throat section 323 of the flow measurement is obtained through the outlet 506 of the second measuring ring. The static pressure difference is obtained by comparison, and the bleed gas flow rate can be obtained by combining the results of the first gas temperature and pressure measurement point 4.

[0051] In one specific embodiment, refer to Figure 9The bleed air flow control valve 330 includes a control valve body, a drive mechanism, and a fixed frame. The drive mechanism is located on both sides of the control valve body. The control valve body includes a control valve inlet 801, a control valve body 802, and a control valve outlet 803, which are symmetrically distributed about the control valve body 802. The control valve inlet 801 is connected to the flow measurement device 320, and the control valve outlet 803 is connected to the outlet pipeline 370 of the measurement and control device. A control valve core 804 is connected inside the control valve body 802. The end of the control valve core 804... A control valve core drive rod 808 is connected. The end of the control valve core drive rod 808 away from the control valve core 804 is connected to the drive mechanism. The drive mechanism is fixed to the outside of the fixed frame. A control valve radiator 806 is sleeved on the outside of the control valve core drive rod 808. The two ends of the control valve radiator 806 are fixed to the inside of the fixed frame by the first control valve mounting seat 805 and the second control valve mounting seat 807, respectively. The first control valve mounting seat 805 is fixed to the upper part of the control valve body 802. The first control valve mounting seat 805 and the control valve body 802 can be connected by bolts.

[0052] In one specific embodiment, the drive mechanism includes two sets, which are respectively disposed on both sides of the fixed frame. Each set of drive mechanisms includes a cylinder pusher base, a cylinder pusher motor, a cylinder pusher actuator, a cylinder pusher mounting base, and a cylinder pusher force transmission rod. The cylinder pusher motor and the cylinder pusher actuator are connected side by side on the cylinder pusher base. One end of the cylinder pusher force transmission rod is fixed to the upper end of the cylinder pusher actuator, and the other end of the cylinder pusher force transmission rod passes through the cylinder pusher mounting base and is connected to the force transmission beam 835 on the fixed frame. The end of the control valve core drive rod 808 away from the control valve core 804 is fixed to the force transmission beam 835. The middle position of beam 835; the fixed frame also includes a bottom adapter 831, a left adapter 832, a right adapter 833 and a top adapter 834. The bottom adapter 831, the left adapter 832, the right adapter 833, the top adapter 834 and the first mounting seat of the control valve 805 form a ring structure for mounting the drive mechanism. The bottom adapter 831, the left adapter 832 and the right adapter 833 are fixed on the first mounting seat of the control valve 805, and the top adapter 834 is fixed on the second mounting seat of the control valve 807.

[0053] Specifically, the two drive mechanisms are a first drive mechanism and a second drive mechanism. The first drive mechanism includes a first cylinder pusher base 811, a first cylinder pusher motor 812, a first cylinder pusher actuator 813, a first cylinder pusher mounting base 814, and a first cylinder pusher force transmission rod 815. The second drive mechanism includes a second cylinder pusher base 821, a second cylinder pusher motor 822, a second cylinder pusher actuator 823, a second cylinder pusher mounting base 824, and a second cylinder pusher force transmission rod 825. The first cylinder pusher mounting base 814 of the first drive mechanism is fixed on the left transition base 832, and the second cylinder pusher mounting base 824 of the second drive mechanism is fixed on the right transition base 833. The first cylinder pusher motor 812 is connected side by side on the first cylinder pusher base 811. The first cylinder actuator 813 has a first cylinder transmission rod 815 fixed to its upper end. Similarly, the second drive mechanism has the same structure as the first drive mechanism. The left and right ends of the force transmission beam 835 are fixed to the first cylinder transmission rod 815 and the second cylinder transmission rod 825, respectively, and the middle of the force transmission beam 835 is fixed to the control valve core drive rod 808. This allows the driving force of the first and second drive mechanisms to be evenly transmitted to the control valve body. Through the action of the drive mechanism, the force transmission beam 835, the first cylinder transmission rod 815, the control valve core drive rod 808, and the second cylinder transmission rod 825 move up and down, achieving rapid and linear online adjustment of the bleed air flow and cabin back pressure.

[0054] In one specific embodiment, the cabin pressure control valve 8 is configured as a control valve with the same structure as the bleed air flow control valve 330.

[0055] In one specific embodiment, refer to Figure 10 The cockpit simulator 7 includes a cockpit shell 702 and a cockpit bulkhead 703 disposed inside the cockpit shell 702. The cockpit shell 702 has a cockpit inlet 701 and a cockpit outlet 707 on both sides. The cockpit inlet 701 is connected to the outlet of the bleed air monitoring and control device 3, and the cockpit outlet 707 is connected to the inlet of the cockpit pressure control valve 8. The cockpit bulkhead 703 is inclined at 45° and has multiple cockpit air guide holes. The lines connecting the cockpit air guide holes to the cockpit inlet 701 and the cockpit outlet 707 are located at different positions. (Refer to...) Figure 9 The cockpit airflow orifice includes a first cockpit airflow orifice 704, a second cockpit airflow orifice 705, and a third cockpit airflow orifice 706. The three orifices are of equal size and located on the upper part of the cockpit bulkhead 703 (the cockpit inlet 701 and the cockpit outlet 707 are located at the bottom of the cockpit), which can achieve uniform pressure distribution inside the cockpit.

[0056] The embodiments provided by this invention can simulate the process of gas drawn from the intermediate stage of the engine compressor, passing through the aircraft environmental control system accessories and the aircraft cabin, and being discharged to the atmosphere through the exhaust valve, according to the bleed air requirements of the engine test aircraft and the specific conditions of the engine test bench. Through the pressure precision adjustment device, the rectifier device, and the back pressure feedback and adjustment device, the engine bleed air flow rate can be adjusted for testing and control, ensuring consistency with the bleed air in the flight environment.

[0057] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An online bleed air adjustment device for aircraft, characterized in that, The system includes a measurement and control system (9) and sequentially connected components such as an engine (1), a bleed air main (2), a bleed air flow measurement and control device (3), a cockpit simulator (7), and a cockpit pressure control valve (8). The bleed air main (2) is equipped with a first gas temperature and pressure measurement point (4), the bleed air flow measurement and control device (3) is equipped with a second gas temperature and pressure measurement point (5), and the cockpit simulator (7) is equipped with a cockpit pressure measurement point (6). The measurement and control system (9) is connected to the cockpit pressure control valve (8), the first gas temperature and pressure measurement point (4), the second gas temperature and pressure measurement point (5), and the cockpit pressure measurement point (6) respectively. The bleed air flow measurement and control device (3) is used to measure and control the bleed air flow of the engine (1) online. The first gas temperature and pressure measurement point (4), the second gas temperature and pressure measurement point (5) and the cabin pressure measurement point (6) are used to measure the gas parameters along the path. The cabin simulator (7) is used to simulate the volume and pressure of the aircraft cabin. The cabin pressure control valve (8) is used to adjust the pressure of the cabin simulator (7) online. The measurement and control system (9) adjusts the bleed air flow measurement and control device (3) and the cabin pressure control valve (8) by collecting the gas parameters along the path from the first gas temperature and pressure measurement point (4), the second gas temperature and pressure measurement point (5) and the cabin pressure measurement point (6), so as to realize the measurement and online adjustment of the bleed air flow.

2. The aircraft bleed air online adjustment device according to claim 1, characterized in that, The bleed air flow measurement and control device (3) includes an outer frame (340) and a measurement and control device cooling pipe (360), a rectifier (310), a flow measuring device (320), and a bleed air flow control valve (330) disposed inside the outer frame (340). The measurement and control device cooling pipe (360) is located on the top of the outer frame (340). The measurement and control device cooling pipe (360) provides air cooling to the rectifier (310), the flow measuring device (320), and the bleed air flow control valve (330). The device (310), flow measurement device (320) and bleed air flow control valve (330) are connected in sequence. The inlet end of the rectifier (310) is connected to the bleed air main pipe (2) through the inlet pipe (350) of the measurement and control device. The outlet end of the bleed air flow control valve (330) is connected to the cabin simulator (7) through the outlet pipe (370) of the measurement and control device. The second gas temperature and pressure measurement point (5) is set on the flow measurement device (320). The bleed air flow control valve (330) is connected to the measurement and control system (9).

3. The aircraft bleed air online adjustment device according to claim 2, characterized in that, The rectifier (310) includes a rectifier inlet expansion section (311), a rectifier straight section (313), a rectifier contraction section (314), and a rectifier outlet straight section (315) connected in sequence. The rectifier inlet expansion section (311) is connected to the inlet pipe (350) of the measurement and control device, and the rectifier outlet straight section (315) is connected to the flow measurement device (320). A rectifier grid plate (312) is provided between the rectifier inlet expansion section (311) and the rectifier straight section (313). The inner diameters of the outlet of the rectifier inlet expansion section (311), the rectifier straight section (313), and the inlet of the rectifier contraction section (314) are the same. The rectifier contraction section (314) adopts a transition contraction curve of arc-straight line-arc. The rectifier grid plate (312) is provided with multiple circular holes evenly distributed on the same annular surface.

4. The aircraft bleed air online adjustment device according to claim 3, characterized in that, The expansion angle of the rectifier intake expansion section (311) is 10°; the area of ​​all the circular holes on the rectifier grid plate (312) is 70% of the area of ​​the inner circle of the rectifier straight section (313), and the length of the rectifier straight section (313) is equal to its inner diameter.

5. The aircraft bleed air online adjustment device according to claim 2, characterized in that, The flow measurement device (320) includes a first straight section (321) for flow measurement, a second straight section (326) for flow measurement, a constriction section (322) for flow measurement, a throat section (323) for flow measurement, a first expansion section (324) for flow measurement, and a second expansion section (325) for flow measurement connected in sequence. The first straight section (321) for flow measurement is connected to the rectifier (310), and the second expansion section (325) for flow measurement is connected to the bleed air flow control valve (330) through the flow measurement outlet flange (327). The second gas temperature and pressure measurement point (5) includes a first measuring ring (328) set at the axial middle position of the first straight section (321) of the flow measurement and a second measuring ring (329) set at the axial middle position of the throat section (323) of the flow measurement.

6. The aircraft bleed air online adjustment device according to claim 5, characterized in that, The first measuring ring (328) and the first straight section (321) of the flow measurement are respectively provided with a first static pressure point (502) and a second static pressure point (503) of the first measuring ring. The first measuring ring (328) has an outlet (501) in the middle of its ring body. The wall static pressure of the second straight section (326) of the flow measurement is obtained through the outlet (501). The second measuring ring (329) and the throat section (323) of the flow measurement are respectively provided with a first static pressure point (502) and a second static pressure point (503) of the first measuring ring (328). There is a first static pressure point (504) of the second measuring ring and a second static pressure point (505) of the second measuring ring. The second measuring ring (329) has a second measuring ring outlet (506) at the middle position of the ring body. The wall static pressure of the flow measurement throat section (323) is obtained through the second measuring ring outlet (506). The bleed gas flow rate is calculated by the wall static pressure of the flow measurement second straight section (326), the wall static pressure of the flow measurement throat section (323), and the test results of the first gas temperature and pressure measurement point (4).

7. The aircraft bleed air online adjustment device according to claim 5, characterized in that, The length of the first straight section (321) of the flow measurement is 3 times the inner diameter. The inner diameter of the front end of the flow measurement contraction section (322) is the same as the inner diameter of the first straight section (321) of the flow measurement. The inner diameter of the rear end of the flow measurement contraction section (322) is half the inner diameter of the front end of the flow measurement contraction section (322). The contraction angle of the flow measurement contraction section (322) is 14°.

8. The aircraft bleed air online adjustment device according to claim 2, characterized in that, The bleed air flow control valve (330) includes a control valve body, a drive mechanism, and a fixed frame. The drive mechanism is located on both sides of the control valve body. The control valve body includes a control valve inlet (801), a control valve body (802), and a control valve outlet (803). The control valve inlet (801) is connected to the flow measurement device (320), and the control valve outlet (803) is connected to the outlet pipeline (370) of the measurement and control device. A control valve core (804) is connected inside the control valve body (802), and the end of the control valve core (804) is connected to... A control valve core drive rod (808) is connected. The end of the control valve core drive rod (808) away from the control valve core (804) is connected to the drive mechanism. The drive mechanism is fixed to the outside of the fixed frame. A control valve radiator (806) is sleeved on the outside of the control valve core drive rod (808). The two ends of the control valve radiator (806) are fixed to the inside of the fixed frame by the first control valve mounting seat (805) and the second control valve mounting seat (807), respectively. The first control valve mounting seat (805) is fixed to the upper part of the control valve body (802).

9. The aircraft bleed air online adjustment device according to claim 8, characterized in that, The drive mechanism comprises two sets, which are respectively set on both sides of the fixed frame. Each set of drive mechanisms includes a cylinder pusher base, a cylinder pusher motor, a cylinder pusher actuator, a cylinder pusher mounting seat, and a cylinder pusher force transmission rod. The cylinder pusher motor and the cylinder pusher actuator are connected side by side on the cylinder pusher base. One end of the cylinder pusher force transmission rod is fixed to the upper end of the cylinder pusher actuator, and the other end of the cylinder pusher force transmission rod passes through the cylinder pusher mounting seat and is connected to the force transmission beam (835) on the fixed frame. The end of the control valve core drive rod (808) away from the control valve core (804) is fixed at the middle position of the force transmission beam (835). The fixed frame also includes The device includes a bottom adapter (831), a left adapter (832), a right adapter (833), and a top adapter (834). The bottom adapter (831), left adapter (832), right adapter (833), top adapter (834), and control valve first mounting seat (805) form an annular structure for mounting the drive mechanism. The bottom adapter (831), left adapter (832), and right adapter (833) are fixed on the control valve first mounting seat (805), and the top adapter (834) is fixed on the control valve second mounting seat (807).

10. The aircraft bleed air online adjustment device according to claim 1, characterized in that, The cockpit simulator (7) includes a cockpit shell (702) and a cockpit partition (703) disposed inside the cockpit shell (702). The cockpit shell (702) has a cockpit inlet (701) and a cockpit outlet (707) on both sides. The cockpit inlet (701) is connected to the outlet of the bleed air flow measurement and control device (3), and the cockpit outlet (707) is connected to the inlet of the cockpit pressure control valve (8). The cockpit partition (703) is provided with multiple cockpit flow guide holes, and the lines connecting the cockpit flow guide holes to the cockpit inlet (701) and the cockpit outlet (707) are located at different positions.

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