An internal flow measurement test device for an aerojet nozzle model

Abstract

The application discloses an internal flow measuring test device for an aero nozzle model, wherein both ends of a nozzle body along the direction of high-pressure airflow are respectively provided with a nozzle inlet and a nozzle outlet, the nozzle outlet is provided with an outlet plate for simulating a wing trailing edge on one side in the radial direction of the nozzle outlet, the outlet plate is located on the top or bottom of the nozzle outlet and extends along the direction of high-pressure airflow, a plurality of guide rods are arranged on the outlet plate and located on the side of the nozzle outlet, the guide rods extend along the height direction of the nozzle outlet, a pressure measuring rake movable along the extension direction of the guide rods is connected to the guide rods, the pressure measuring rake is provided with a driving mechanism for driving the movement of the pressure measuring rake, a plurality of first probes for detecting the total pressure of the nozzle outlet are arranged on the pressure measuring rake and are equally spaced along the width direction of the nozzle outlet, and the outlet plate is arranged at the nozzle outlet to simulate the real environment of the nozzle outlet, and the pressure measuring rake and the first probes are arranged to sweep along the vertical direction of the nozzle outlet to measure the outlet total pressure at different positions of the nozzle outlet.

Description

Technical Field

[0001] This invention relates to the field of aero-engine flow field testing equipment, and in particular to an internal flow measurement test device for an aero-engine nozzle model. Background Technology

[0002] The nozzle is a crucial component of an engine, providing power. The S-shaped bend in the nozzle effectively shields high-temperature components and increases the number of reflections of incident electromagnetic waves within the bend. Simultaneously, the rectangular nozzle enhances mixing, shortens the length of the high-temperature core region, and significantly reduces the infrared radiation intensity and electromagnetic scattering signal of the aero-engine exhaust system. Therefore, it has received considerable attention from research institutions both domestically and internationally, becoming a key technology for stealth fighters. Currently, there is considerable research on nozzles. Domestic researchers such as Zhang Ruilin and Liu Changchun have conducted multifaceted studies on nozzle noise, aerodynamic characteristics, and infrared characteristics. Analysis of the layout of currently operational stealth aircraft abroad shows that using a two-dimensional nozzle can suppress the infrared radiation of the jet. Zhang Bo et al. experimentally studied the infrared radiation characteristics of a large aspect ratio rectangular nozzle with visible tail-end flames, concluding that the infrared suppression effect increases with increasing aspect ratio, with a good infrared suppression effect at an aspect ratio of 8. When studying different characteristics of nozzles, it is necessary to combine the experimental data of the nozzle, such as the total inlet pressure, the internal pressure of the nozzle, and the total outlet pressure. In current nozzle experiments, the experimental equipment is generally relatively simple, the accuracy of the measured data is not accurate enough, and systematic pressure measurement schemes are rarely used in nozzle experiments. Summary of the Invention

[0003] The purpose of this invention is to provide an internal flow measurement test device for aircraft nozzle models to solve the problems existing in the prior art. An exit plate is installed at the nozzle exit to simulate the real environment of the nozzle exit. At the same time, a pressure measuring rake and a first probe that sweep along the vertical direction of the nozzle exit are provided to measure the total pressure at different positions of the nozzle exit. The total pressure at the nozzle exit is then output as the pressure distribution at the nozzle exit, making the experimental data more comprehensive and reliable.

[0004] To achieve the above objectives, the present invention provides the following solution: The present invention provides an internal flow measurement test device for an aircraft nozzle model, comprising a nozzle body, wherein the nozzle body has a nozzle inlet and a nozzle outlet at both ends along the high-pressure gas flow direction, the nozzle inlet is supplied with high-pressure gas, and the nozzle outlet has an outlet plate for simulating the trailing edge of an airfoil along one side of its radial direction, the outlet plate is located at the top or bottom of the nozzle outlet and extends along the direction of high-pressure gas ejection, and the outlet plate is provided with a plurality of guide rods located on the nozzle outlet side, the guide rods extending along the height direction of the nozzle outlet, the guide rods being connected to pressure measuring rakes movable along their extension direction, and the pressure measuring rakes being equipped with a driving mechanism for driving their movement, the pressure measuring rakes being provided with a plurality of first probes for detecting the total pressure of the nozzle outlet, each of the first probes being close to the nozzle outlet and equally spaced along the width direction of the nozzle outlet.

[0005] Preferably, the inner circumferential surface of the nozzle body is provided with three pressure measuring lines, two of which are located at the top and bottom of the nozzle body, respectively, and the other pressure measuring line is located at the middle position of the nozzle body. Each pressure measuring line extends from the nozzle inlet to the nozzle outlet. Several pressure measuring points are equally spaced along the extension direction of the pressure measuring line. Each pressure measuring point is provided with a pressure measuring hole. A second probe for monitoring the internal static pressure of the nozzle body is provided in the pressure measuring hole.

[0006] Preferably, the nozzle inlet is coaxially connected to a straight rectifier cylinder for introducing high-pressure gas, and the flow cross-sectional structure of the straight rectifier cylinder matches the flow cross-sectional structure of the nozzle inlet.

[0007] Preferably, the inner circumferential side of the straight cylinder is provided with a straight cone coaxial with it. There is an annular gap between the straight cone and the inner circumferential wall of the straight cylinder for high-pressure gas to flow. The two ends of the straight cone along the high-pressure gas flow direction are respectively conical. The cross section of the inlet end gradually decreases in the opposite direction to the high-pressure gas flow, and the cross section of the outlet end gradually decreases in the same direction as the high-pressure gas flow, and extends into the nozzle inlet.

[0008] Preferably, a third probe for measuring the total inlet pressure is provided at the axial center of the rectifier cone corresponding to the intake side end.

[0009] Preferably, the inner wall of the rectifier cylinder is provided with a connecting plate for fixing the rectifier cone. The connecting plate is connected to the middle position of the rectifier cone, and the third probe extends out of the rectifier cylinder through the connecting plate.

[0010] Preferably, the nozzle outlet has a rectangular structure, and the ratio of its width to its height is greater than 1.

[0011] Preferably, each of the guide rods is symmetrically connected to both sides of the pressure measuring rake along the width direction of the nozzle outlet.

[0012] Preferably, the driving mechanism includes a drive motor and a rotating screw rotatably connected to the outlet plate. One end of the rotating screw extends out of the outlet plate near the nozzle outlet and extends in the same direction as the guide rod. The pressure measuring rake has a threaded hole threaded to the rotating screw. The other end of the rotating screw extends out of the outlet plate away from the nozzle outlet and is drively connected to the output shaft of the drive motor.

[0013] Preferably, the screw hole is opened at the center position of the pressure measuring rake.

[0014] The present invention achieves the following technical effects compared to the prior art:

[0015] First, by setting an exit plate to simulate the actual wall conditions of the wing trailing edge, the realism of the nozzle exit environment is improved. Then, by setting a guide rod on the side of the exit plate corresponding to the nozzle exit, and a pressure measuring rake is movably mounted on the guide rod, the pressure measuring rake can sweep back and forth along the nozzle exit height direction because the guide rod extends along the nozzle exit height. The pressure measuring rake is equipped with several first probes evenly distributed along the width direction of the nozzle exit. Each first probe moves back and forth along the nozzle exit height direction with the pressure measuring rake to measure the total exit pressure at different positions of the nozzle exit. The total exit pressure is then output as the pressure distribution of the nozzle exit, making the experimental data more comprehensive and reliable.

[0016] Second, three pressure measuring lines are provided on the inner circumferential surface of the nozzle body. Two of the pressure measuring lines are located at the top and bottom of the nozzle body, respectively, and the third pressure measuring line is located in the middle of the nozzle body. Each pressure measuring line extends from the nozzle inlet to the nozzle outlet. Several pressure measuring points are evenly spaced along the extension direction of the pressure measuring line. Each pressure measuring point has a pressure measuring hole. A second probe for monitoring the static pressure inside the nozzle body is provided in the pressure measuring hole. Since the three pressure measuring lines are distributed at the top, bottom and middle of the nozzle respectively, the static pressure at the top, bottom and middle of the nozzle body cavity can be obtained. Moreover, since the pressure measuring lines extend from the nozzle inlet to the nozzle outlet, each second probe can measure the static pressure along the nozzle body, which improves the accuracy of the experimental data.

[0017] Third, the nozzle inlet is coaxially connected to a straight rectifier cylinder for introducing high-pressure gas, and the flow cross-sectional structure of the straight rectifier cylinder matches the flow cross-sectional structure of the nozzle inlet to guide and rectify the high-pressure gas. This allows the high-pressure gas to enter the interior of the nozzle body along the nozzle inlet axially after passing through the straight rectifier cylinder, thereby effectively ensuring the pressure increase and flow rate of the high-pressure gas and reducing pressure loss.

[0018] Fourth, a rectifier cone is provided on the inner circumference of the rectifier cylinder, which is coaxial with it. There is an annular gap between the rectifier cone and the inner circumferential wall of the rectifier cylinder for high-pressure gas to flow. The two ends of the rectifier cone along the high-pressure gas flow direction are respectively conical. The cross section of its inlet end gradually decreases in the opposite direction to the high-pressure gas flow, and the cross section of its outlet end gradually decreases in the same direction as the high-pressure gas flow, and extends into the nozzle inlet. On the one hand, after passing through the rectifier cone, the velocity of the high-pressure gas will increase slightly, and the pressure and temperature will decrease slightly. The high-pressure gas can flow into the nozzle body more evenly. On the other hand, by setting the rectifier cone and extending its outlet end into the nozzle inlet, the annular inlet of the actual nozzle is simulated more realistically. Attached Figure Description

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

[0020] Figure 1 This is a perspective view of the overall structure of the present invention;

[0021] Figure 2 This is a schematic diagram of the rectifier cone structure of the present invention;

[0022] Figure 3 Axonometric view of the overall structure of this invention Figure 1 ;

[0023] Figure 4 Axonometric view of the overall structure of this invention Figure 2 ;

[0024] Figure 5 This is a schematic diagram of the pressure measuring line and its measuring point inside the nozzle body of the present invention;

[0025] Among them, 1-rectifier cylinder, 2-rectifier cone, 3-connecting plate, 4-nozzle body, 5-third probe, 6-rib plate, 7-exit plate, 8-pressure measuring rake, 9-drive motor, 10-rotating screw, 11-nozzle outlet, 12-jointing plate. Detailed Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] The purpose of this invention is to provide an internal flow measurement test device for aircraft nozzle models to solve the problems existing in the prior art. An exit plate is installed at the nozzle exit to simulate the real environment of the nozzle exit. At the same time, a pressure measuring rake and a first probe that sweep along the vertical direction of the nozzle exit are provided to measure the total pressure at different positions of the nozzle exit. The total pressure at the nozzle exit is then output as the pressure distribution at the nozzle exit, making the experimental data more comprehensive and reliable.

[0028] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0029] like Figures 1 to 5 As shown, this embodiment provides an internal flow measurement test device for an aircraft nozzle model, including a nozzle body 4. The nozzle body 4 has a nozzle inlet and a nozzle outlet 11 at both ends along the high-pressure gas flow direction. High-pressure gas is introduced into the nozzle inlet, and the nozzle outlet 11 has a Mach number Ma = 0.5-0.7. An outlet plate 7 for simulating the trailing edge of an airfoil is provided on one side of the nozzle outlet 11 along its radial direction. The outlet plate 7 is located at the top or bottom of the nozzle outlet 11 and extends along the direction of high-pressure gas ejection. The outlet plate 7 has several... A guide rod is located on the nozzle outlet 11 side. The guide rod extends along the height direction of the nozzle outlet 11. The guide rod is connected to a pressure measuring rake 8 that can move along its extension direction. It should be noted that the guide rod is spaced apart from the nozzle outlet 11 along the high-pressure gas flow direction to reserve installation space for the pressure measuring rake 8. The pressure measuring rake 8 is equipped with a drive mechanism to drive its movement. The pressure measuring rake 8 is provided with several first probes for detecting the total pressure of the nozzle outlet 11. Each first probe is close to the nozzle outlet 11 and is evenly distributed along the width direction of the nozzle outlet 11. By setting an exit plate 7 to simulate the actual wall conditions of the wing trailing edge, the realism of the environment at the nozzle exit 11 is improved. Furthermore, a guide rod is installed on one side of the exit plate 7 corresponding to the nozzle exit 11, and a pressure measuring rake 8 is movably mounted on the guide rod. Since the guide rod extends along the height of the nozzle exit 11, the pressure measuring rake 8 can reciprocate along the height direction of the nozzle exit 11. Several first probes are evenly distributed along the width direction of the nozzle exit 11 on the pressure measuring rake 8. Each first probe moves reciprocally along the height direction of the nozzle exit 11 with the pressure measuring rake 8 to measure the total exit pressure at different positions of the nozzle exit 11. The total exit pressure is then output as the pressure distribution of the nozzle exit 11, making the experimental data more comprehensive and reliable. Preferably, the span of the area where all the first probes are located along the width direction of the nozzle exit 11 matches the width of the nozzle exit 11. Preferably, 21 pressure measuring points are evenly arranged on the pressure measuring rake 8, and each pressure measuring point is equipped with a single first probe to perform longitudinal scanning of the nozzle exit 11.

[0030] Preferably, the inner circumferential surface of the nozzle body 4 is provided with three pressure measuring lines. Two of the pressure measuring lines are located at the top and bottom of the nozzle body 4, respectively, and the third pressure measuring line is located at the middle position of the nozzle body 4. Each pressure measuring line extends from the nozzle inlet to the nozzle outlet 11. Several pressure measuring points are evenly spaced along the extension direction of the pressure measuring line. Each pressure measuring point has a pressure measuring hole, and a second probe for monitoring the static pressure inside the nozzle body 4 is provided in the pressure measuring hole. Since the three pressure measuring lines are distributed at the top, bottom, and middle positions of the nozzle, the static pressure at the top, bottom, and middle positions of the nozzle body 4 can be obtained. Moreover, since the pressure measuring lines extend from the nozzle inlet to the nozzle outlet 11, each second probe can measure the friction static pressure inside the nozzle body 4, improving the accuracy of the experimental data. Preferably, there are a total of 98 pressure measuring points on the three pressure measuring lines. The adjacent pressure measuring points on each pressure measuring line are arranged at 10 mm intervals. A pressure measuring hole is arranged at each pressure measuring point to measure the friction static pressure.

[0031] Furthermore, the nozzle inlet is coaxially connected to a straight rectifier cylinder 1 for introducing high-pressure gas, and the flow cross-sectional structure of the straight rectifier cylinder 1 matches the flow cross-sectional structure of the nozzle inlet to guide and rectify the high-pressure gas, so that after passing through the straight rectifier cylinder 1, the high-pressure gas can enter the interior of the nozzle body 4 along the nozzle inlet axis, thereby effectively ensuring the pressure increase and flow rate of the high-pressure gas and reducing pressure loss.

[0032] In a preferred embodiment of the present invention, a rectifier cone 2 coaxially arranged on the inner circumference of the rectifier cylinder 1 is provided. An annular gap for high-pressure gas flow exists between the rectifier cone 2 and the inner circumferential wall of the rectifier cylinder 1. The two ends of the rectifier cone 2 along the high-pressure gas flow direction are conical. The cross-section of its inlet end gradually decreases in the opposite direction to the high-pressure gas flow, while the cross-section of its outlet end gradually decreases in the same direction as the high-pressure gas flow, extending into the nozzle inlet. On the one hand, after passing through the rectifier cone 2, the velocity of the high-pressure gas will increase slightly, and the pressure and temperature will decrease slightly, allowing the high-pressure gas to flow into the nozzle body 4 more evenly. On the other hand, by setting the rectifier cone 2 and extending its outlet end into the nozzle inlet, the annular inlet of the actual nozzle is simulated more realistically. By setting the rectifier cone 2 between the rectifier cylinder 1 and the nozzle inlet, the present invention can simulate different forms of inflow while ensuring the stability of the inflow, thereby ensuring experimental diversity.

[0033] Furthermore, a third probe 5 for measuring the total inlet pressure is provided at the axial center of the rectifier cone 2 corresponding to the intake side end, in order to obtain the total inlet pressure data of the nozzle. Specifically, a pressure measuring tube is installed at the axial center of the rectifier cone 2 corresponding to the intake side end, the third probe 5 is installed inside the pressure measuring tube, and the third probe 5 is electrically connected to the outside of the nozzle body 4 through a lead wire to measure the total inlet pressure.

[0034] Furthermore, the inner wall of the rectifier cylinder 1 is provided with a connecting plate 3 for fixing the rectifier cone 2. The connecting plate 3 is connected at the middle position of the rectifier cone 2, and the third probe 5 extends out of the rectifier cylinder 1 through the connecting plate 3. By passing the third probe 5 through the connecting plate 3, it is not only convenient to electrically connect the third probe 5 through the connection between the connecting plate 3 and the rectifier cylinder 1, and then connect it to the pressure scanning valve, but also avoids placing the third probe 5 and its lead wire alone in the rectifier cylinder 1, which is easily blown by high-pressure gas and thus damaged.

[0035] Currently, there are many designs for nozzle shapes, resulting in numerous experiments related to nozzles. However, current experimental setups are relatively simple, involving pressure measuring tubes installed at the nozzle inlet and outlet, with pressure measuring holes arranged along the nozzle path to obtain static pressure at different locations. However, most nozzle outlets 11 are circular, making it impossible to measure them using the pressure measuring rake 8. In a preferred embodiment of this invention, the nozzle outlet 11 has a rectangular structure with a width-to-height ratio greater than 1. This allows it to function as an engine nozzle for stealth aircraft. The preferred nozzle outlet 11 has a width-to-height ratio much greater than 1. This large outlet aspect ratio is advantageous for application in flying wing configurations, enabling distributed power arrangement and overall stealth design of the aircraft. Furthermore, it facilitates compatibility with the pressure measuring rake 8 structure, allowing for the arrangement of various first probes to perform longitudinal scanning of the nozzle outlet 11, obtaining comprehensive and accurate data at different times and locations.

[0036] Preferably, each guide rod is symmetrically connected to both sides of the pressure measuring rake 8 along the width direction of the nozzle outlet 11. On the one hand, this avoids the nozzle outlet 11 and prevents the air from the nozzle from affecting the stability of the guide rod. On the other hand, the symmetrical design of the guide rod facilitates stable support for the pressure measuring rake 8 and ensures the accuracy of the total pressure data measured by the pressure measuring rake 8 at the outlet.

[0037] Furthermore, the drive mechanism includes a drive motor 9 and a rotating screw 10 rotatably connected to the outlet plate 7. One end of the rotating screw 10 extends out of the outlet plate 7 near the nozzle outlet 11 and extends in the same direction as the guide rod. A threaded hole is provided on the pressure measuring rake 8, which is threadedly connected to the rotating screw 10. The other end of the rotating screw 10 extends out of the outlet plate 7 away from the nozzle outlet 11 and is driveably connected to the output shaft of the drive motor 9. The drive motor 9 drives the pressure measuring rake 8, causing it to automatically sweep at the outlet and measure the total pressure at different positions of the nozzle outlet 11. To ensure stable movement of the pressure measuring rake 8, the threaded hole is preferably located at the center of the pressure measuring rake 8.

[0038] In a preferred embodiment of the present invention, the nozzle body 4 includes two nozzle half-molds symmetrically spliced ​​along the horizontal direction. Ribs 6 are provided at the splicing positions of the two nozzle half-molds. The ribs 6 are arranged in parallel to each other, which facilitates the connection of the two ribs 6 by means of connectors to complete the splicing of the two nozzle half-molds. Preferably, splicing plates 12 are provided at the nozzle outlet 11 corresponding to each nozzle half-mold. Each splicing plate 12 is located at the bottom of the nozzle half-mold corresponding to the outlet end. The outlet plate 7 is installed on the two splicing plates 12. Preferably, the end of the outlet plate 7 near the nozzle outlet 11 is provided with a mounting plate parallel to the splicing plate 12. The mounting plate is connected to the two splicing plates 12 to complete the connection between the outlet plate 7 and the nozzle body 4.

[0039] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0040] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0041] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. An internal flow measurement test device for an aircraft nozzle model, characterized in that, The device includes a nozzle body, with a nozzle inlet and a nozzle outlet at both ends along the high-pressure gas flow direction. High-pressure gas is introduced into the nozzle inlet. An outlet plate for simulating the trailing edge of an airfoil is provided on one side of the nozzle outlet along its radial direction. The outlet plate is located at the top or bottom of the nozzle outlet and extends along the direction of high-pressure gas ejection. The outlet plate is provided with several guide rods located on the nozzle outlet side. The guide rods extend along the height direction of the nozzle outlet. The guide rods are connected to pressure measuring rakes that are movable along their extension direction. The pressure measuring rakes are equipped with a drive mechanism to drive their movement. The pressure measuring rakes are provided with several first probes for detecting the total pressure at the nozzle outlet. Each first probe is close to the nozzle outlet and is evenly distributed along the width direction of the nozzle outlet. The inner circumferential surface of the nozzle body is provided with three pressure measuring lines, two of which are located at the top and bottom of the nozzle body, respectively, and the third pressure measuring line is located at the middle position of the nozzle body. Each pressure measuring line extends from the nozzle inlet to the nozzle outlet. Several pressure measuring points are equally spaced along the extension direction of the pressure measuring line. Each pressure measuring point is provided with a pressure measuring hole. A second probe for monitoring the static pressure inside the nozzle body is provided in the pressure measuring hole. The nozzle inlet is coaxially connected to a straight rectifier cylinder for introducing high-pressure gas, and the flow cross-sectional structure of the straight rectifier cylinder matches the flow cross-sectional structure of the nozzle inlet. The inner circumference of the straight cylinder is provided with a straight cone coaxial with it. There is an annular gap between the straight cone and the inner circumferential wall of the straight cylinder for high-pressure gas to flow. The two ends of the straight cone along the high-pressure gas flow direction are respectively conical. The cross section of the inlet end gradually decreases in the opposite direction to the high-pressure gas flow, and the cross section of the outlet end gradually decreases in the same direction as the high-pressure gas flow, and extends into the nozzle inlet.

2. The internal flow measurement test device for an aircraft nozzle model according to claim 1, characterized in that, The rectifier cone is equipped with a third probe at the axial center of the end corresponding to the intake side for measuring the total inlet pressure.

3. The internal flow measurement test device for an aircraft nozzle model according to claim 2, characterized in that, The inner wall of the straight rectifier cylinder is provided with a connecting plate for fixing the rectifier cone. The connecting plate is connected to the middle position of the rectifier cone, and the third probe extends out of the straight rectifier cylinder through the connecting plate.

4. The internal flow measurement test device for an aircraft nozzle model according to claim 3, characterized in that, The nozzle outlet has a rectangular structure, and the ratio of its width to its height is greater than 1.

5. The internal flow measurement test device for an aircraft nozzle model according to claim 4, characterized in that, Each of the guide rods is symmetrically connected to both sides of the pressure measuring rake along the width direction of the nozzle outlet.

6. The internal flow measurement test apparatus for an aircraft nozzle model according to claim 5, characterized in that, The driving mechanism includes a drive motor and a rotating screw rotatably connected to the outlet plate. One end of the rotating screw extends out of the outlet plate near the nozzle outlet and extends in the same direction as the guide rod. The pressure measuring rake has a threaded hole that is threaded to the rotating screw. The other end of the rotating screw extends out of the outlet plate away from the nozzle outlet and is drively connected to the output shaft of the drive motor.

7. The internal flow measurement test apparatus for an aircraft nozzle model according to claim 6, characterized in that, The screw hole is correspondingly opened at the center position of the pressure measuring rake.

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